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Aircraft Maintenance Manual - Landing Gear Effective Pages
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C AIRCRAFT MAINTENANCE MANUAL LANDING GEAR LIST OF EFFECTIVE PAGES Chapter Section Subject Config 32 − Effective Pages 32 − Contents Master EFFECTIVITY: ALL Page Date 1 * Dec 10/2005 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 * * * * * * * * * * * * * * * * * Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Aug 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 * * * * Apr 20/2004 Mar 15/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Chapter Section Subject 32−00−00 Config Page Date 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Dec 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 * * Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−Effective Page 1 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config Page Date 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 601 602 603 604 605 606 607 608 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 701 702 703 704 Mar 15/2005 Mar 15/2005 Mar 15/2005 Mar 15/2005 32−10−00 1 2 Apr 20/2004 Apr 20/2004 32−10−00 601 602 603 604 605 606 607 Aug 10/2005 Apr 20/2004 Aug 10/2005 Aug 10/2005 Mar 15/2005 Mar 15/2005 Aug 10/2005 32−00−00 32−00−00 Master EFFECTIVITY: ALL Chapter Section Subject Page Date 608 609 610 611 612 Aug 10/2005 Mar 15/2005 Mar 15/2005 Mar 15/2005 Mar 15/2005 32−11−00 1 2 3 4 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−11−00 401 402 403 404 405 406 407 408 409 410 411 412 413 414 Aug 10/2005 Apr 20/2004 Aug 10/2005 Aug 10/2005 Apr 20/2004 Apr 20/2004 Aug 10/2005 Mar 15/2005 Dec 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Mar 15/2005 Mar 15/2005 32−11−05 Config 401 402 403 404 405 406 407 408 409 410 411 412 413 414 415 416 417 * * * * Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 32−Effective Page 2 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config Page 418 419 420 421 422 423 424 425 426 427 428 429 32−11−05 Date * * * * Dec 10/2005 Dec 10/2005 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 501 502 503 504 Dec 15/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 32−11−05 601 602 Apr 20/2004 Apr 20/2004 32−11−10 401 402 403 404 405 406 407 408 409 410 411 412 413 414 32−11−15 Master EFFECTIVITY: ALL 401 402 403 404 405 406 * * * * * * * Apr 20/2004 Dec 10/2005 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Chapter Section Subject Config Page Date 32−11−15 601 602 603 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−11−20 401 402 403 404 405 406 407 408 409 410 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 32−11−25 401 402 403 404 405 406 407 408 409 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−12−00 1 2 3 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−12−00 201 202 203 204 205 Apr 20/2004 Aug 10/2005 Aug 10/2005 Apr 20/2004 Apr 20/2004 32−12−01 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Dec 15/2004 Apr 20/2004 Apr 20/2004 32−Effective Page 3 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config Page Date 501 502 503 504 505 506 507 508 509 510 511 512 513 514 515 516 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−12−05 401 402 403 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−12−10 401 402 403 404 405 406 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−12−15 401 402 403 404 405 406 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−12−17 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−12−01 Master EFFECTIVITY: ALL Chapter Section Subject Config Page Date 32−12−20 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−20−00 1 2 Apr 20/2004 Apr 20/2004 32−20−00 601 602 603 604 605 606 607 608 609 610 611 612 Apr 20/2004 Apr 20/2004 Aug 10/2005 Aug 10/2005 Mar 15/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Mar 15/2005 Mar 15/2005 Mar 15/2005 Mar 15/2005 32−21−00 1 2 3 4 32−21−01 401 402 403 404 405 406 407 408 409 410 411 412 413 * * * * Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Sep 10/2004 Sep 10/2004 Aug 10/2005 Apr 20/2004 Apr 20/2004 Sep 10/2004 Dec 15/2004 Aug 10/2005 Sep 10/2004 Sep 10/2004 Sep 10/2004 32−Effective Page 4 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config Page Date 32−21−01 501 502 503 504 Dec 15/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 32−21−01 601 602 Apr 20/2004 Apr 20/2004 401 402 403 404 405 406 407 408 409 410 411 412 413 414 415 416 32−21−05 32−21−10 201 202 32−21−10 401 402 403 404 405 406 407 408 409 410 411 412 413 Master EFFECTIVITY: ALL * * * * Chapter Section Subject Page Date 32−21−10 501 502 503 504 505 506 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−21−15 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 401 402 403 404 405 406 407 408 409 410 411 412 413 414 415 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−21−15 601 602 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 32−21−20 201 202 203 204 205 206 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−21−20 401 402 403 404 405 406 407 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Config 32−Effective Page 5 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config 32−21−25 32−21−30 Master EFFECTIVITY: ALL Page Date 401 402 403 404 405 406 407 408 409 410 411 412 413 414 415 416 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 401 402 403 404 405 406 407 408 409 410 411 412 413 414 415 416 417 418 419 420 421 422 423 424 425 426 427 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Dec 10/2005 Apr 20/2004 * * * * Chapter Section Subject Config Page Date 428 429 430 431 432 433 434 435 436 437 438 439 440 441 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 * * 32−22−00 1 2 3 4 5 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−22−01 201 202 203 204 205 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−22−01 401 402 403 404 405 406 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−22−01 501 502 503 504 505 506 507 508 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Dec 10/2005 Dec 10/2005 Sep 10/2004 Apr 20/2004 * * * 32−Effective Page 6 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config 32−22−01 Page Date 601 602 603 604 605 606 607 608 Apr 20/2004 Apr 20/2004 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Apr 20/2004 * * * * * 32−22−05 401 402 403 404 405 406 407 408 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−22−05 501 502 503 504 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−22−05 601 602 603 604 605 606 607 608 Apr 20/2004 Apr 20/2004 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Apr 20/2004 Apr 20/2004 32−22−10 Master EFFECTIVITY: ALL 401 402 403 404 405 406 407 408 409 410 411 * * * * * * * * * Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Sep 10/2004 Apr 20/2004 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Sep 10/2004 Chapter Section Subject Config Page 412 413 414 415 Date * Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−22−10 501 502 503 504 505 506 507 508 509 510 511 512 513 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−22−15 401 402 403 404 405 406 407 408 409 410 411 412 413 414 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−22−20 401 402 403 404 405 406 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−Effective Page 7 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config Page Date 32−22−25 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−22−30 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−30−00 1 2 3 4 32−30−00 201 202 203 32−30−00 501 502 503 504 505 506 507 508 509 510 511 512 513 32−31−00 Master EFFECTIVITY: ALL 1 2 3 4 * * * * * * * * * Chapter Section Subject Page Date 32−31−01 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−31−01 501 502 503 Dec 15/2004 Dec 15/2004 Dec 15/2004 32−31−01 601 602 603 604 605 606 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−32−00 1 2 3 4 5 6 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−32−01 401 402 403 404 405 406 Apr 20/2004 Apr 20/2004 Apr 20/2004 Sep 10/2004 Sep 10/2004 Sep 10/2004 32−32−05 401 402 403 404 405 406 407 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−32−10 401 402 403 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Dec 10/2005 Apr 20/2004 Config 32−Effective Page 8 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config 32−32−15 Page Date 404 405 406 407 408 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 401 402 403 404 405 406 407 408 409 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Dec 10/2005 Apr 20/2004 * * * 32−32−15 501 502 503 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−32−20 401 402 403 404 405 406 407 408 409 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Dec 10/2005 Apr 20/2004 32−32−25 32−32−30 Master EFFECTIVITY: ALL * * * 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Chapter Section Subject Config Page Date 32−33−00 1 2 3 4 5 6 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−33−00 201 202 203 204 205 206 207 208 209 210 211 212 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 * 32−33−01 401 402 403 404 405 406 407 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−33−05 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−33−05 501 502 503 504 505 506 507 508 509 * * * * * * Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Mar 15/2005 Dec 10/2005 Mar 15/2005 Mar 15/2005 32−Effective Page 9 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config 32−33−10 Page Date 510 511 512 513 514 515 516 517 518 519 520 521 522 523 Mar 15/2005 Mar 15/2005 Mar 15/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Mar 15/2005 Dec 10/2005 Mar 15/2005 Mar 15/2005 Mar 15/2005 Mar 15/2005 Mar 15/2005 401 402 403 404 405 406 407 408 409 410 411 412 * * * * * * * * * * * Apr 20/2004 Dec 10/2005 Dec 10/2005 Apr 20/2004 Dec 10/2005 Apr 20/2004 Dec 10/2005 Dec 10/2005 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 32−33−15 401 402 403 404 405 406 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−34−00 1 2 3 4 5 6 Dec 15/2004 Dec 15/2004 Dec 15/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Master EFFECTIVITY: ALL Chapter Section Subject 32−34−00 Config Page 501 502 503 504 505 506 507 508 509 510 511 512 513 514 515 516 517 518 519 520 521 522 523 524 525 526 527 528 529 530 531 532 533 534 535 536 537 538 539 540 541 542 543 544 545 Date * * * * * * * * * * * * * Apr 20/2004 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 15/2004 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 15/2004 Dec 10/2005 Dec 15/2004 Dec 15/2004 Apr 20/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Dec 15/2004 Apr 20/2004 Dec 15/2004 Apr 20/2004 Dec 10/2005 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 15/2004 Dec 15/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−Effective Page 10 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config 32−34−00 32−34−01 32−34−05 32−34−15 Master EFFECTIVITY: ALL Page Date 546 547 548 549 550 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 601 602 603 604 605 606 607 608 609 610 611 612 613 614 615 616 617 Mar 15/2005 Aug 10/2005 Aug 10/2005 Apr 20/2004 Dec 10/2005 Aug 10/2005 Mar 15/2005 Mar 15/2005 Mar 15/2005 Dec 10/2005 Dec 10/2005 Mar 15/2005 Mar 15/2005 Mar 15/2005 Mar 15/2005 Mar 15/2005 Mar 15/2005 401 402 403 404 405 406 407 408 * * * * * * * * * Dec 10/2005 Dec 10/2005 Apr 20/2004 Apr 20/2004 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 401 402 403 404 405 406 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 401 402 403 Apr 20/2004 Apr 20/2004 Apr 20/2004 Chapter Section Subject 32−34−20 Config Page Date 404 405 406 407 408 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 401 402 403 404 405 406 407 408 409 410 411 412 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 * * * 32−34−25 401 402 403 404 405 406 407 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−34−30 401 402 403 404 405 406 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−34−35 401 402 403 404 405 406 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−Effective Page 11 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config Page Date 32−34−40 401 402 403 404 405 406 407 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−34−45 401 402 403 404 405 406 407 408 409 410 411 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−40−00 1 2 3 4 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−41−00 1 2 3 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−41−01 401 402 403 404 405 406 407 408 409 410 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 Master EFFECTIVITY: ALL Chapter Section Subject 32−41−01 Config Page 601 602 603 604 605 606 607 608 609 610 611 612 613 614 615 616 617 618 619 620 621 622 623 624 625 626 627 628 629 630 631 632 633 634 635 636 637 638 639 640 641 642 643 644 645 Date * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 Dec 10/2005 32−Effective Page 12 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config Page Date 32−41−06 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−42−00 1 2 3 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−42−01 401 402 403 404 405 406 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−42−01 601 602 603 604 605 606 607 608 609 610 611 612 613 614 615 616 617 618 619 620 621 622 623 624 625 626 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Master EFFECTIVITY: ALL Chapter Section Subject Config Page Date 627 628 629 630 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−42−06 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−43−00 1 2 3 4 5 6 7 8 9 10 11 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−43−00 301 302 303 304 305 306 307 308 309 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−43−00 401 402 Apr 20/2004 Apr 20/2004 32−43−00 501 502 503 504 505 506 Apr 20/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 32−Effective Page 13 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config Page Date 507 508 509 510 511 512 513 514 515 516 517 518 Dec 15/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 Aug 10/2005 Aug 10/2005 Dec 15/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 601 602 603 604 605 606 607 608 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 401 402 403 404 405 406 407 408 409 410 411 412 413 414 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−43−06 601 602 Apr 20/2004 Apr 20/2004 32−43−11 401 402 403 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−43−00 32−43−06 Master EFFECTIVITY: ALL Chapter Section Subject Config Page Date 404 405 406 407 408 409 410 411 412 413 414 415 416 417 418 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−43−11 601 Apr 20/2004 32−43−13 401 402 403 404 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−43−13 501 502 503 504 505 506 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−43−14 401 402 403 404 405 406 407 408 409 * * * * Dec 10/2005 Mar 15/2005 Dec 10/2005 Apr 20/2004 Apr 20/2004 Dec 10/2005 Dec 10/2005 Apr 20/2004 Apr 20/2004 32−Effective Page 14 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config Page Date 401 402 403 404 405 406 407 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−43−16 501 502 503 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−43−17 401 402 403 404 405 406 407 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−43−16 32−43−21 401 402 403 404 405 406 407 * * Apr 20/2004 Dec 10/2005 Dec 15/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Dec 15/2004 32−43−21 501 502 503 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−43−26 401 402 403 404 405 406 407 408 409 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Aug 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Jun 22/2004 Master EFFECTIVITY: ALL Chapter Section Subject Config Page Date 410 411 Apr 20/2004 Apr 20/2004 32−43−26 601 602 603 604 605 606 607 608 609 610 611 612 613 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Dec 15/2004 Aug 10/2005 Dec 15/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 32−44−00 1 2 3 4 5 6 7 8 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−44−00 501 502 503 504 505 506 507 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−44−01 401 402 403 404 405 406 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 15/2004 Dec 15/2004 Dec 15/2004 32−Effective Page 15 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config Page Date 501 502 503 Apr 20/2004 Apr 20/2004 Apr 20/2004 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−44−06 501 502 503 504 505 506 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−44−11 401 402 403 404 405 406 407 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 401 402 403 404 Apr 20/2004 Apr 20/2004 Dec 15/2004 Dec 15/2004 32−45−00 1 2 3 4 5 6 7 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−45−00 201 202 203 Aug 10/2005 Apr 20/2004 Aug 10/2005 32−44−01 32−44−06 32−44−16 Master EFFECTIVITY: ALL Chapter Section Subject 32−45−00 Config Page Date 501 502 503 504 505 506 507 508 509 510 511 512 513 514 515 516 517 518 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Dec 15/2004 Apr 20/2004 Jun 22/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 * * 32−45−00 601 Apr 20/2004 32−45−01 401 402 403 404 405 406 407 408 409 410 411 412 413 414 415 416 417 418 419 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Dec 10/2005 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 * * * 32−Effective Page 16 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config 32−45−01 32−45−11 Page 501 502 503 504 505 506 507 401 402 403 404 405 406 407 Date * * Dec 10/2005 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−45−11 501 502 503 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−45−16 501 502 503 504 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−46−00 1 2 3 4 5 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−46−00 501 Apr 20/2004 32−46−01 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 401 402 403 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−46−06 Master EFFECTIVITY: ALL Chapter Section Subject Config Page Date 404 405 Apr 20/2004 Apr 20/2004 32−46−06 501 502 Apr 20/2004 Apr 20/2004 32−47−00 1 2 3 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−47−00 501 502 503 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−47−01 401 402 403 404 405 406 407 408 409 410 411 412 413 414 415 416 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−50−00 1 2 3 4 32−50−00 501 502 503 504 505 506 * * Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−Effective Page 17 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config 32−51−00 32−51−00 Master EFFECTIVITY: ALL Page Date 507 508 Apr 20/2004 Apr 20/2004 1 2 3 4 5 6 7 8 9 10 11 12 13 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 501 502 503 504 505 506 507 508 509 510 511 512 513 514 515 516 517 518 519 520 521 522 523 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Dec 10/2005 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 * * * * * * Chapter Section Subject Page Date 32−51−01 201 202 203 204 205 206 207 208 209 210 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−51−01 401 402 403 404 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−51−05 201 202 203 204 205 206 207 208 209 210 211 212 213 214 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 15/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Dec 10/2005 Dec 10/2005 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−51−05 Config 401 402 403 404 405 406 407 408 409 * * * * * * Dec 15/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Dec 15/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−Effective Page 18 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config 32−51−10 32−51−10 32−51−10 32−51−15 Master EFFECTIVITY: ALL Page Date 201 202 203 204 205 206 207 208 209 210 211 212 213 214 215 216 217 218 219 220 221 222 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 15/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 501 502 503 504 505 506 507 508 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Chapter Section Subject Config Page Date 406 407 408 409 410 411 412 413 414 415 416 417 418 419 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−51−20 201 202 203 204 205 206 207 208 209 210 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−51−20 401 402 403 404 405 406 407 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−51−25 401 402 403 404 405 406 407 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−Effective Page 19 Aug 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config 32−51−30 32−51−35 32−51−40 Page Date 401 402 403 404 405 406 407 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 401 402 403 404 405 406 407 408 409 410 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 * * 401 402 403 404 405 406 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 401 402 403 404 405 406 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−52−00 1 2 Apr 20/2004 Apr 20/2004 32−52−01 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−51−45 Master EFFECTIVITY: ALL Chapter Section Subject Config Page Date 406 407 Apr 20/2004 Apr 20/2004 32−52−01 601 Apr 20/2004 32−52−05 401 402 403 404 405 406 407 408 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−52−10 401 402 403 404 405 406 407 408 409 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−52−10 601 602 603 604 605 606 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−60−00 1 Apr 20/2004 32−61−00 1 2 3 4 5 6 7 8 9 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−Effective Page 20 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config Page Date 10 11 12 13 14 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−61−00 201 202 203 204 205 206 207 208 209 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−61−00 501 502 503 504 505 506 507 508 509 510 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 15/2004 32−61−01 201 202 203 204 205 206 207 208 209 210 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−61−01 401 402 403 404 405 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Master EFFECTIVITY: ALL Chapter Section Subject 32−61−05 Config Page Date 401 402 403 404 405 406 407 408 409 410 411 412 413 414 415 416 417 418 419 420 421 422 423 424 425 426 427 428 429 430 431 432 433 434 435 436 437 438 439 440 441 442 443 444 445 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 * 32−Effective Page 21 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config 32−61−05 Master EFFECTIVITY: ALL Page Date 446 447 448 449 450 451 452 453 454 455 456 457 458 459 460 461 462 463 464 465 466 467 468 469 470 471 472 473 474 475 476 477 478 479 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 501 502 503 504 505 506 507 508 509 * * * * Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Chapter Section Subject 32−61−05 Config Page Date 510 511 512 513 514 515 516 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 601 602 603 604 605 606 607 608 609 610 611 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 * 32−61−15 401 402 403 404 405 406 407 408 409 410 411 412 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−61−20 401 402 403 404 405 406 407 408 409 410 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−Effective Page 22 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Config 32−61−25 Master EFFECTIVITY: ALL Page Date 411 412 413 414 415 416 417 418 419 420 421 422 423 424 425 426 427 428 429 430 431 432 433 434 435 436 437 438 439 440 441 442 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Aug 10/2005 Aug 10/2005 Aug 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Aug 10/2005 Dec 10/2005 Dec 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Dec 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 Aug 10/2005 401 402 403 404 405 406 407 408 409 410 411 * * * * Chapter Section Subject Config Page 412 413 414 415 Date * Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 32−71−01 401 402 403 404 405 406 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−71−05 401 402 403 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−71−10 401 402 403 404 405 406 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−71−15 401 402 403 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Dec 10/2005 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 Apr 20/2004 32−Effective Page 23 Dec 10/2005 Pages C AIRCRAFT MAINTENANCE MANUAL LANDING GEAR TABLE OF CONTENTS Subject Chapter Section Subject LANDING GEAR SYSTEM 32−00−00 Description and Operation Page 1 Effectivity: ON A/C ALL General Description Main Landing Gear Nose Landing Gear Extension/Retraction System 2 Wheel and Brake System Steering System 4 Indicating and Warning System Support System Inspection/Check 601 Effectivity: ON A/C ALL General External Leak Check of the Landing Gear Cleaning 701 Effectivity: ON A/C ALL General Landing Gear Structure Cleaning Procedure (Non−Pressure Wash) MAIN LANDING GEAR AND DOORS 32−10−00 Description and Operation 1 Effectivity: ON A/C ALL General Description Main Landing Gear Main Door and Mechanism System Operation Master EFFECTIVITY: ALL 32−Contents Page 1 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Inspection/Check Page 601 Effectivity: ON A/C ALL General Visual Inspection of the Main Landing Gear and Door Detailed Inspection of the Main Landing Gear and 603 Doors Detailed Inspection of the Main Landing Gear 607 (MLG) Components Detailed Inspection of the Main Landing Gear 611 (MLG) Doors MAIN LANDING GEAR (MLG) SYSTEM 32−11−00 Description and Operation 1 Effectivity: ON A/C ALL General Component Details Main Fitting Assembly MLG Shock Strut Trailing Arm 2 MLG Axle Swivel Coupling Assembly 3 Operation Component Location Index Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the MLG Installation of the MLG Master EFFECTIVITY: ALL 406 32−Contents Page 2 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject SHOCK STRUT, MAIN LANDING GEAR (MLG) 32−11−05 Page Removal/Installation Effectivity: ON A/C ALL General Removal of the MLG Shock Strut Installation of the MLG Shock Strut 417 Adjustment/Test 501 Effectivity: ON A/C ALL General Functional Test of the Main Landing Gear (MLG) Shock Strut Extension Inspection/Check 601 Effectivity: ON A/C ALL General Detailed Inspection of the MLG Shock Strut Extension TRAILING ARM 32−11−10 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Trailing Arm Installation of the Trailing Arm MAIN LANDING GEAR (MLG) AXLE Removal/Installation 407 32−11−15 401 Effectivity: ON A/C ALL General Removal of the MLG Axle Installation of the MLG Axle Inspection/Check 404 601 Effectivity: ON A/C ALL Master EFFECTIVITY: ALL Page 3 32−Contents Aug 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject General Page 601 Detailed Inspection of the MLG Axle Assembly SWIVEL VALVE 32−11−20 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Upper Brake Swivel Assembly Installation of the Upper Brake Swivel Assembly SWIVEL COUPLING ASSEMBLY, MAIN LANDING 406 32−11−25 GEAR (MLG) Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Swivel Coupling Assembly Installation of the Swivel Coupling Assembly MAIN DOOR AND MECHANISM SYSTEM Description and Operation 405 32−12−00 1 Effectivity: ON A/C ALL General Component Details MLG Door Assembly Door Brush Push/Pull Rod Bellcrank Assembly End Rod Operation Component Location Index Maintenance Practices 2 201 Effectivity: ON A/C ALL Master EFFECTIVITY: ALL Page 4 32−Contents Aug 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject General Page 201 Disconnect the MLG Door for Maintenance Access Connect the MLG Door after Maintenance DOORS, MAIN LANDING GEAR 204 32−12−01 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Main Landing Gear Doors Installation of the Main Landing Gear Doors 404 Adjustment/Test 501 Effectivity: ON A/C ALL General Operational Test of the Main Landing Gear Doors Adjustment of the Main Landing Gear Doors DOOR BRUSH 503 32−12−05 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Door Brush Installation of the Door Brush PUSH/PULL ROD Removal/Installation 403 32−12−10 401 Effectivity: ON A/C ALL General Removal of the Push/Pull Rod Installation of the Push/Pull Rod Master EFFECTIVITY: ALL 404 Page 5 32−Contents Aug 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject BELLCRANK ASSEMBLY 32−12−15 Page Removal/Installation Effectivity: ON A/C ALL General Removal of the Bellcrank Assembly Installation of the Bellcrank Assembly STAY−STUD, DOOR 404 32−12−17 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Door Stay Stud Installation of the Door Stay Stud DOOR STRUT 404 32−12−20 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Door Strut Installation of the Door Strut NOSE LANDING GEAR AND DOORS Description and Operation 404 32−20−00 1 Effectivity: ON A/C ALL General Description Nose Landing Gear Nose Landing−Gear Doors Operation Inspection/Check 601 Effectivity: ON A/C ALL General Master EFFECTIVITY: ALL Page 6 32−Contents Aug 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Page Visual Inspection of the Nose Landing Gear and Doors Detailed Inspection of the Nose Landing Gear 603 Components and Doors Detailed Inspection of the Nose Landing Gear 606 (NLG) Components Detailed Inspection of the Nose Landing Gear 610 (NLG) Doors NOSE LANDING GEAR (NLG) 32−21−00 Description and Operation 1 Effectivity: ON A/C ALL General Component Details NLG Shock−Strut Assembly Drag Brace 2 Torque Link Assembly Torque Link Assembly NLG Axle NLG Seals 3 Operation Component Location Index SHOCK STRUT, NOSE LANDING GEAR (NLG) Removal/Installation 32−21−01 401 Effectivity: ON A/C ALL General Removal of the NLG Shock Strut Installation of the NLG Shock Strut Adjustment/Test 407 501 Effectivity: ON A/C ALL General Master EFFECTIVITY: ALL Page 7 32−Contents Aug 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Page Functional Test of the Nose Landing Gear (NLG) Shock Strut Extension Inspection/Check 601 Effectivity: ON A/C ALL General Detailed Inspection of the NLG Shock Strut Extension DRAG BRACE, NOSE LANDING GEAR (NLG) 32−21−05 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the NLG Drag Brace Installation of the NLG Drag Brace ASSEMBLY, TORQUE LINK Maintenance Practices 409 32−21−10 201 Effectivity: ON A/C ALL General Operational Test of the Torque Link Assembly Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Torque Link Assembly Installation of the Torque Link Assembly Adjustment/Test 408 501 Effectivity: ON A/C ALL General Alignment of the NLG Shock Strut Torque Links. Master EFFECTIVITY: ALL Page 8 32−Contents Aug 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject AXLE ASSEMBLY, NOSE LANDING GEAR (NLG) 32−21−15 Removal/Installation Page 401 Effectivity: ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED General Removal of the NLG Axle Assembly Installation of the NLG Axle Assembly 407 Inspection/Check 601 Effectivity: ON A/C ALL General Detailed Inspection of the NLG Axle Assembly SEALS, NOSE LANDING GEAR 32−21−20 Maintenance Practices 201 Effectivity: ON A/C ALL General Replacement of the Tee Seal with the Spare Tee Seal Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Lower Bearing Seals of the NLG Shock Strut Installation of the Lower Bearing Seals of the NLG 405 Shock Strut SEALS, NLG FLOATING PISTON Removal/Installation 32−21−25 401 Effectivity: ON A/C ALL General Master EFFECTIVITY: ALL Page 9 32−Contents Aug 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Page Removal of the Floating Piston Seals of the NLG Shock Strut Installation of the Floating Piston Seals of the NLG 408 Shock Strut ASSEMBLY, NLG SLIDING MEMBER 32−21−30 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the NLG Sliding Member Installation of the NLG Sliding Member NOSE GEAR DOOR SYSTEM 420 32−22−00 Description and Operation 1 Effectivity: ON A/C ALL General Component Details Forward Doors Rear Door Door Actuator Door Link Assembly Door Selector Valve Check Valve 2 Maintenance Access Switch Operation Component Location Index FORWARD DOORS, NOSE LANDING GEAR Maintenance Practices 32−22−01 201 Effectivity: ON A/C ALL General Master EFFECTIVITY: ALL 10 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Page Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors 204 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Forward Doors of the Nose Landing Gear Installation of the Forward Doors of the Nose 404 Landing Gear Adjustment/Test 501 Effectivity: ON A/C ALL General Functional Test of the Nose−Landing−Gear Forward Doors Rigging of the Forward Doors of the Nose Landing 502 Gear Inspection/Check 601 Effectivity: ON A/C ALL General Clearance Check of the NLG Forward Doors REAR DOOR, NOSE LANDING GEAR (NLG) Removal/Installation 32−22−05 401 Effectivity: ON A/C ALL General Removal of the Nose−Landing−Gear Rear Door Installation of the Rear Door of the Nose Landing 404 Gear Adjustment/Test 501 Effectivity: ON A/C ALL General Master EFFECTIVITY: ALL 11 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Page Adjustment of the NLG Rear Door Inspection/Check 601 Effectivity: ON A/C ALL General Clearance Check of the NLG Rear Door DOOR ACTUATOR, NOSE LANDING GEAR 32−22−10 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the NLG Door Actuator Installation of the NLG Door Actuator 406 Adjustment/Test 501 Effectivity: ON A/C ALL General Adjustment of the NLG Door Actuator and Mechanism DOOR MECHANISM ASSEMBLY 32−22−15 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Door Mechanism Assembly Installation of the Door Mechanism Assembly VALVE, DOOR SELECTOR Removal/Installation 408 32−22−20 401 Effectivity: ON A/C ALL General Removal of the Door Selector Valve Installation of the Door Selector Valve Master EFFECTIVITY: ALL 404 12 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject CHECK VALVE, NOSE GEAR DOOR SYSTEM 32−22−25 Page Removal/Installation Effectivity: ON A/C ALL General Removal of the Check Valve Installation of the Check Valve SWITCH, MAINTENANCE ACCESS (NLG DOOR) 404 32−22−30 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Maintenance Access Switch Installation of the Maintenance Access Switch EXTENSION AND RETRACTION Description and Operation 404 32−30−00 1 Effectivity: ON A/C ALL General Description Operation Maintenance Practices 2 201 Effectivity: ON A/C ALL General Landing Gear Extension and Retraction − Maintenance Practices Adjustment/Test 501 Effectivity: ON A/C ALL General Functional Test of the Landing Gear Extension/Retraction System Master EFFECTIVITY: ALL 13 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Landing Gear Extension/Retraction Gear Disagree Page 507 Test System Test of the Landing Gear Priority Valves LANDING GEAR CONTROL 511 32−31−00 Description and Operation 1 Effectivity: ON A/C ALL General Component Details Control Panel Assembly Operation Landing Gear Aural Warning Component Location Index CONTROL PANEL, LANDING GEAR Removal/Installation 3 32−31−01 401 Effectivity: ON A/C ALL General Removal of the Landing Gear Control Handle Installation of the Landing Gear Control Handle Adjustment/Test 404 501 Effectivity: ON A/C ALL General Operational Test of the Switch/Light (MUTE HORN) Inspection/Check 601 Effectivity: ON A/C ALL General Detailed Inspection of the Slider in the Landing Gear Control Handle Master EFFECTIVITY: ALL 14 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject MAIN LANDING GEAR EXTENSION/RETRACTION 32−32−00 Description and Operation Page 1 Effectivity: ON A/C ALL General Component Details MLG Side Stay Actuator MLG Uplock Assembly MLG Selector Valve 2 MLG Priority Valve MLG Runaround and Bypass Valve Operation MLG Extension MLG Retraction 3 Component Location Index ACTUATOR, MAIN LANDING GEAR (MLG) 32−32−01 EXTENSION/RETRACTION Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the MLG Side Stay Actuator Installation of the MLG Side Stay Actuator UPLOCK ASSEMBLY, MLG Removal/Installation 404 32−32−05 401 Effectivity: ON A/C ALL General Removal of the MLG Uplock Assembly Installation of the MLG Uplock Assembly Master EFFECTIVITY: ALL 405 15 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject VALVE, MAIN LANDING GEAR SELECTOR 32−32−10 Page Removal/Installation Effectivity: ON A/C ALL General Removal of the Main Landing Gear Selector Valve Installation of the Main Landing Gear Selector 405 Valve VALVE, MLG PRIORITY 32−32−15 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the MLG Priority Valve Installation of the MLG Priority Valve 406 Adjustment/Test 501 Effectivity: ON A/C ALL General Functional Test of the MLG Priority Valve VALVE, RUNAROUND AND BYPASS 32−32−20 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Runaround and Bypass Valve Installation of the Runaround and Bypass Valve CHECK VALVE, MLG SELECTOR VALVE Removal/Installation 406 32−32−25 401 Effectivity: ON A/C ALL General Removal of the Return Check Valve Installation of the Return Check Valve Master EFFECTIVITY: ALL 404 16 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject RESTRICTOR (C1 PORT), MLG SELECTOR VALVE 32−32−30 Page Removal/Installation Effectivity: ON A/C ALL General Removal of the Restrictor Installation of the Restrictor NOSE LANDING GEAR EXTENSION/RETRACTION Description and Operation 404 32−33−00 1 Effectivity: ON A/C ALL General Component Details NLG Retraction Actuator NLG Uplock Assembly NLG Selector Valve 2 NLG Priority Valve Operation NLG Extension NLG Retraction Component Location Index Maintenance Practices 3 201 Effectivity: ON A/C ALL General Nose Landing Gear Extension and Retraction − Maintenance Practices Installation of the Support Equipment for NLG 205 Extension and Retraction Removal of the Support Equipment for NLG 209 Extension and Retraction Master EFFECTIVITY: ALL 17 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject ACTUATOR, NLG EXTENSION/RETRACTION 32−33−01 Removal/Installation Page 401 Effectivity: ON A/C ALL General Removal of the NLG Extension/Retraction Actuator Installation of the NLG Extension/Retraction 404 Actuator UPLOCK ASSEMBLY, NLG 32−33−05 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the NLG Uplock Assembly Installation of the NLG Uplock Assembly 404 Adjustment/Test 501 Effectivity: ON A/C ALL General Alignment of the NLG Uplock Pin with the NLG Uplock Assembly (Hydraulic Test Stand Method) Alignment of the NLG Uplock Pin with the NLG 513 Uplock Assembly (ACMP 3A Method) VALVE, NOSE LANDING GEAR SELECTOR Removal/Installation 32−33−10 401 Effectivity: ON A/C ALL General Removal of the Nose Landing Gear Selector Valve Installation of the Nose Landing Gear Selector 407 Valve Master EFFECTIVITY: ALL 18 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject VALVE, PRIORITY 32−33−15 Page Removal/Installation Effectivity: ON A/C ALL General Removal of the NLG Priority Valve Installation of the NLG Priority Valve MANUAL RELEASE, LANDING GEAR Description and Operation 404 32−34−00 1 Effectivity: ON A/C ALL General Component Details Manual Release Handle Downlock Assist Actuator Operating Lever 2 NLG Release Mechanism MLG Release Mechanism Downlock Assist Valve NLG Runaround and Bypass Valve NLG Bypass Valve NLG Door Bypass−Valve 3 Operation Component Location Index Adjustment/Test 501 Effectivity: ON A/C ALL General Operational Test of the Landing Gear Manual− Release−System Functional Test of the Landing Gear Manual− 508 Release−System Rigging of the Manual Release Mechanism 516 Adjustment of the NLG Manual Release System 537 Master EFFECTIVITY: ALL 19 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Inspection/Check Page 601 Effectivity: ON A/C ALL General Inspection of the NLG Manual Release System Inspection of the MLG Manual Release 603 Detailed Inspection of the Landing Gear Manual 605 Release Components Detailed Inspection of the Landing Gear Manual 610 Release Components (Forward and Main Avionics Compartment and Wheel Wells) Detailed Inspection of the Landing Gear Manual 615 Release Components (Mid−Fuselage Under Floor) HANDLE, MANUAL RELEASE 32−34−01 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Manual Release Handle Installation of the Manual Release Handle ACTUATOR, DOWNLOCK ASSIST 405 32−34−05 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Downlock Assist Actuator Installation of the Downlock Assist Actuator RELEASE MECHANISM, NLG EMERGENCY 404 32−34−15 (ALTERNATE) Removal/Installation 401 Effectivity: ON A/C ALL Master EFFECTIVITY: ALL 20 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject General Page 401 Removal of the NLG Manual Release Mechanism Installation of the NLG Manual Release 406 Mechanism RELEASE MECHANISM, MLG EMERGENCY 32−34−20 (ALTERNATE) Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the MLG Manual Release Mechanism Installation of the MLG Manual Release 407 Mechanism VALVE, MLG EMERGENCY (ALTERNATE) 32−34−25 EXTENSION Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Emergency Extension Valve Installation of the Emergency Extension Valve RELIEF VALVE, MLG ALTERNATE EXTENSION Removal/Installation 405 32−34−30 401 Effectivity: ON A/C ALL General Removal of the Relief Valve Installation of the Relief Valve Master EFFECTIVITY: ALL 404 21 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject BYPASS VALVE, NOSE LANDING GEAR (NLG) 32−34−35 Page Removal/Installation Effectivity: ON A/C ALL General Removal of the NLG Bypass Valve Installation of the NLG Bypass Valve BYPASS VALVE, NOSE LANDING GEAR (NLG) 404 32−34−40 DOOR Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the NLG Door Bypass Valve Installation of the NLG Door Bypass Valve CABLES, MANUAL RELEASE SYSTEM 405 32−34−45 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Manual Release Cables Installation of the Manual Release Cables WHEELS AND BRAKES Description and Operation 407 32−40−00 1 Effectivity: ON A/C ALL General Description Main Gear Wheels and Tires Nose Gear Wheels and Tires Main Gear Brake System Antiskid Control System Parking Brake System Master EFFECTIVITY: ALL 22 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Page Brake Temperature Monitoring System Brake Pressure Monitoring System 2 Operation Main Wheel/Tire Assembly Nosewheel/Tire Assembly Main Gear Brake System Antiskid Control System Parking Brake System Brake Temperature Monitoring System Brake Pressure Monitoring System MAIN LANDING GEAR WHEEL AND TIRE 3 32−41−00 ASSEMBLY Description and Operation 1 Effectivity: ON A/C ALL General Component Details Wheel and Tire Assembly Component Location Index MAIN WHEEL/TIRE ASSEMBLY Removal/Installation 2 32−41−01 401 Effectivity: ON A/C ALL General Removal of the Main Wheel/Tire Assembly Installation of the Main Wheel/Tire Assembly Inspection/Check 406 601 Effectivity: ON A/C ALL General Visual Inspection of the Main Tire − Retreadable Goodyear Tires Master EFFECTIVITY: ALL 23 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Visual Inspection of the Main Tire − Non− Page 615 Retreadable Michelin Tires Visual Inspection of the Main Tire − Retreadable 628 Michelin Tires 32−41−06 PRESSURE INDICATOR, MAIN LANDING GEAR (MLG) TIRE Removal/Installation 401 Effectivity: ON A/C 7006−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7032−7033, 7036, 7039, 7041, 7052, 7059, 7061, 7063−7064, 7073, 7075, 7086, 7089−7090, 7093−7094, 7099, 7103−7104, 7110, 7113−7114, 7119, 7121−7122, 7125, 7128, 7130, 7133, 7135−7136, 7140, 7142, 7148, 7152, 7165, 7167, 7176, 7190, 7200, 7205, 7220, 7266, 7282, 7298, 7351, 7365, 7371, 7378, 7391, 7394, 7403, 7407, 7413, 7419, 7431, 7439, 7449, 7455, 7464, 7478, 7480, 7486, 7494, 7499, 7567, 7570, 7573, 7583, 7605, 7607, 7619, 7625, 7629−7630, 7639, 7738, 7846, 7862, 7864, 7901−7902, 7910 General Removal of the MLG Tire Pressure Indicator Installation of the MLG Tire Pressure Indicator NOSE LANDING GEAR WHEEL AND TIRE 404 32−42−00 ASSEMBLY Description and Operation 1 Effectivity: ON A/C ALL General Component Details Wheel and Tire Assembly Component Location Index NOSEWHEEL/TIRE ASSEMBLY Removal/Installation 32−42−01 401 Effectivity: ON A/C ALL General Master EFFECTIVITY: ALL 24 32−Contents Dec Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Page Removal of the Nosewheel/Tire Assembly Installation of the Nosewheel/Tire Assembly 404 Inspection/Check 601 Effectivity: ON A/C ALL General Visual Inspection of the Nose Wheel/Tire − Retreadable Goodyear Tires Visual Inspection of the Nose Wheel/Tire − 614 Retreadable Michelin Tires 32−42−06 PRESSURE−INDICATOR, NOSE LANDING GEAR (NLG) TIRE Removal/Installation 401 Effectivity: ON A/C 7006−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7032−7033, 7036, 7039, 7041, 7052, 7059, 7061, 7063−7064, 7073, 7075, 7086, 7089−7090, 7093−7094, 7099, 7103−7104, 7110, 7113−7114, 7119, 7121−7122, 7125, 7128, 7130, 7133, 7135−7136, 7140, 7142, 7148, 7152, 7165, 7167, 7176, 7190, 7200, 7205, 7220, 7266, 7282, 7298, 7351, 7365, 7371, 7378, 7391, 7394, 7403, 7407, 7413, 7419, 7431, 7439, 7449, 7455, 7464, 7478, 7480, 7486, 7494, 7499, 7567, 7570, 7573, 7583, 7605, 7607, 7619, 7625, 7629−7630, 7639, 7738, 7846, 7862, 7864, 7901−7902, 7910 General Removal of the NLG Tire Pressure Indicator Installation of the NLG Tire Pressure Indicator MAIN LANDING GEAR BRAKE SYSTEM Description and Operation 404 32−43−00 1 Effectivity: ON A/C ALL General Component Details Brake Pedals Brake Control Valve Assembly Brake−Control Push/Pull Mechanism Master EFFECTIVITY: ALL 25 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Page Brake Accumulator Volumetric Fuse 2 Brake Unit Check Valve Operation Component Location Index Servicing 3 301 Effectivity: ON A/C ALL General Bleeding of the Brakes Flushing of the Brakes Removal/Installation 307 401 Effectivity: ON A/C ALL General Deactivation of the Brake Accumulator Pressure Gauge Adjustment/Test 501 Effectivity: ON A/C ALL General Operational Test of the Brake System Pressure Test of the Brake System 504 Spindown Pressure Check 510 Adjustment of the Brake−System Pressure 513 Inspection/Check 601 Effectivity: ON A/C ALL General General Visual Inspection of the Brake System Hydraulic Lines and Components Sample Check of the Brake Fluid Master EFFECTIVITY: ALL 604 26 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject VALVE, DUAL BRAKE CONTROL 32−43−06 Removal/Installation Page 401 Effectivity: ON A/C ALL General Removal of the Brake Control Mechanism Assembly Installation of the Brake Control Mechanism 408 Assembly Inspection/Check 601 Effectivity: ON A/C ALL General Brake Pressure Decay Check of the Brake Control Mechanism Assembly CABLE ASSEMBLIES, BRAKE CONTROL 32−43−11 PUSH/PULL Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Pilot’s Brake Control Push/Pull Cable Assemblies Installation of the Pilot’s Brake Control Push/Pull 405 Cable Assemblies Removal of the Co−pilot’s Brake Control Push/Pull 410 Cable Assemblies Installation of the Co−Pilot’s Brake Control 414 Push/Pull Cable Assemblies Inspection/Check 601 Effectivity: ON A/C ALL General Visual Inspection of the Brake Control Push/Pull Mechanism Master EFFECTIVITY: ALL 27 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject RODS, RUDDER PEDAL BRAKE CONTROL 32−43−13 Removal/Installation Page 401 Effectivity: ON A/C ALL General Removal of the Brake Control Rods Installation of the Brake Control Rods 403 Adjustment/Test 501 Effectivity: ON A/C ALL General Adjustment of the Brake Control Rods LEVERS, RUDDER PEDAL BRAKE CONTROL 32−43−14 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Brake Control Levers Installation of the Brake Control Levers ACCUMULATOR, BRAKE Removal/Installation 406 32−43−16 401 Effectivity: ON A/C ALL General Removal of the Brake Accumulator Installation of the Brake Accumulator Adjustment/Test 405 501 Effectivity: ON A/C ALL General Operational Test of the Brake Accumulator Master EFFECTIVITY: ALL 28 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject PRESSURE GAUGE, BRAKE ACCUMULATOR 32−43−17 Removal/Installation Page 401 Effectivity: ON A/C ALL General Removal of the Brake Accumulator Pressure Gauge Installation of the Brake Accumulator Pressure 405 Gauge FUSE, VOLUMETRIC 32−43−21 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Volumetric Fuse Installation of the Volumetric Fuse 405 Adjustment/Test 501 Effectivity: ON A/C ALL General Functional Test of the Volumetric Fuse BRAKE UNIT Removal/Installation 32−43−26 401 Effectivity: ON A/C ALL General Removal of the Brake Unit Installation of the Brake Unit Inspection/Check 406 601 Effectivity: ON A/C ALL General Visual Inspection of the Brake Unit Wear− Indicator−Pin Master EFFECTIVITY: ALL 29 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Detailed Inspection of the Brake Unit Wear− Page 604 Indicator−Pin Leakage Check of the Brake Unit 607 In−Service Leakage Limits − Brake Unit Piston 611 ANTISKID CONTROL SYSTEM 32−44−00 Description and Operation 1 Effectivity: ON A/C ALL General Component Details Wheel Speed Transducer Antiskid Control Unit Antiskid Control Valve 2 Drive Cap Antiskid Relay 3 Operation Component Location Index 4 Adjustment/Test 501 Effectivity: ON A/C ALL General Operational Test of the Antiskid System Functional Test of the Antiskid System TRANSDUCER, WHEEL SPEED Removal/Installation 503 32−44−01 401 Effectivity: ON A/C ALL General Removal of the Wheel Speed Transducer Installation of the Wheel Speed Transducer Adjustment/Test 404 501 Effectivity: ON A/C ALL Master EFFECTIVITY: ALL 30 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Page General Turn Test of the Wheel Speed Transducer UNIT, ANTISKID CONTROL 32−44−06 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Antiskid Control Unit Installation of the Antiskid Control Unit 404 Adjustment/Test 501 Effectivity: ON A/C ALL General Antiskid−Control−Unit (ASCU) System BITE−Test VALVE, ANTISKID CONTROL 32−44−11 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Antiskid Control Valve Installation of the Antiskid Control Valve DRIVE CAP 405 32−44−16 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Drive Cap Installation of the Drive Cap PARKING BRAKE SYSTEM Description and Operation 403 32−45−00 1 Effectivity: ON A/C ALL General Master EFFECTIVITY: ALL 31 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Page Component Details Parking Brake Handle Parking−Brake Push/Pull Cable Parking−Brake Shutoff Valve Parking Brake Microswitch Operation Component Location Index 3 Maintenance Practices 201 Effectivity: ON A/C ALL General Set the Parking Brake Release the Parking Brake 203 Adjustment/Test 501 Effectivity: ON A/C ALL General Operational Test of the Parking Brake System Functional Test of the Parking Brake System 503 Adjustment of the Parking Brake System 514 Inspection/Check 601 Effectivity: ON A/C ALL General Detailed Inspection of the Parking Brake System HANDLE/CABLE ASSEMBLY, PARKING BRAKE Removal/Installation 32−45−01 401 Effectivity: ON A/C ALL General Removal of the Parking Brake Handle and Cable Installation of the Parking Brake Handle and 405 Cable Removal of the Handle Body 408 Installation of the Handle Body 412 Master EFFECTIVITY: ALL 32 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Page Removal of the Bulkhead Fitting 415 Installation of the Bulkhead Fitting 418 Adjustment/Test 501 Effectivity: ON A/C ALL General Adjustment of the Parking Brake Cable SHUTOFF VALVE, PARKING BRAKE 32−45−11 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Parking Brake Shutoff Valve Installation of the Parking Brake Shutoff Valve 405 Adjustment/Test 501 Effectivity: ON A/C ALL General Operational Test of the Parking Brake Shutoff Valve MICROSWITCH, PARKING BRAKE 32−45−16 Adjustment/Test 501 Effectivity: ON A/C ALL General Adjustment of the Parking Brake Microswitch BRAKE TEMPERATURE MONITORING SYSTEM 32−46−00 (BTMS) Description and Operation 1 Effectivity: ON A/C ALL General Component Details Brake Temperature Monitoring Unit Master EFFECTIVITY: ALL 33 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Page Thermocouple Sensor Operation Component Location Index 3 Adjustment/Test 501 Effectivity: ON A/C ALL General Operational Test of the Brake Temperature Monitoring System SENSOR, THERMOCOUPLE 32−46−01 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Thermocouple Sensor Installation of the Thermocouple Sensor UNIT, BRAKE TEMPERATURE MONITORING Removal/Installation 404 32−46−06 401 Effectivity: ON A/C ALL General Removal of the Brake Temperature Monitoring Unit Installation of the Brake Temperature Monitoring 404 Unit Adjustment/Test 501 Effectivity: ON A/C ALL General BITE Test of the Brake Temperature Monitoring Unit Master EFFECTIVITY: ALL 34 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject BRAKE PRESSURE MONITORING SYSTEM 32−47−00 Description and Operation Page 1 Effectivity: ON A/C ALL General Component Details Pressure Transducer Operation Component Location Index Adjustment/Test 501 Effectivity: ON A/C ALL General Operational Test of the Brake Pressure Monitoring System PRESSURE TRANSDUCER 32−47−01 Removal/Installation 401 Effectivity: ON A/C ALL Removal of the Brake System Pressure Transducer Installation of the Brake System Pressure 405 Transducer Removal of the Brake Application Pressure 409 Transducer Installation of the Brake Application Pressure 413 Transducer STEERING SYSTEM Description and Operation 32−50−00 1 Effectivity: ON A/C ALL General Description 2 Nosewheel Steering Master EFFECTIVITY: ALL 35 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Page Actuating Mechanism Operation Adjustment/Test 501 Effectivity: ON A/C ALL General BITE Test of the Steering System STEERING, NOSEWHEEL Description and Operation 32−51−00 1 Effectivity: ON A/C ALL General Component Details Steering−Handwheel Control Module Rotary Variable Differential Transducer Electronic Control Module Electrohydraulic Module 2 Position Feedback Sensor 3 Solenoid Selector Valve Hydraulic Compensator Pressure Switch No. 1 Pressure Switch No. 2 Swivel Valve/Banjo Piping Assembly Operation SBW Mode 4 Free Castoring Mode Component Location Index Adjustment/Test 501 Effectivity: ON A/C ALL General Operational Test of the Nosewheel Steering − Torque Link Assembly Connected Master EFFECTIVITY: ALL 36 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Operational Test of the Nosewheel Steering − Page 506 Torque Link Assembly Disconnected Functional Test of the Nosewheel Steering UNIT, STEERING HANDWHEEL CONTROL 511 32−51−01 Maintenance Practices 201 Effectivity: ON A/C ALL General Calibration Check of the Steering Handwheel− Control−Unit Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Steering Handwheel−Control−Unit Installation of the Steering Handwheel−Control− 403 Unit MODULE, RUDDER PEDAL INPUT COMMAND 32−51−05 Maintenance Practices 201 Effectivity: ON A/C ALL General Adjustment of the Rudder−Pedal−Input RVDT Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Rudder−Pedal−Input RVDT Installation of the Rudder−Pedal−Input RVDT UNIT, ELECTRONIC CONTROL Maintenance Practices 405 32−51−10 201 Effectivity: ON A/C ALL General Master EFFECTIVITY: ALL 37 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Page Interrogation of the Non−Volatile Memory of the Nosewheel Steering ECU Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the ECU Installation of the ECU 404 Adjustment/Test 501 Effectivity: ON A/C ALL General Operational Test of the Electronic Control Unit MODULE, ELECTROHYDRAULIC 32−51−15 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Electrohydraulic Module Installation of the Electrohydraulic Module 407 Removal of the Electrohydraulic Servo Valve 412 Installation of the Electrohydraulic Servo Valve 416 SENSOR, POSITION FEEDBACK Maintenance Practices 32−51−20 201 Effectivity: ON A/C ALL General Adjustment of the Left and Right Feedback RVDTs Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Left and Right Feedback RVDTs Installation of the Left and Right Feedback RVDT Master EFFECTIVITY: ALL 405 38 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject VALVE, SOLENOID SELECTOR 32−51−25 Page Removal/Installation Effectivity: ON A/C ALL General Removal of the Solenoid Selector Valve Installation of the Solenoid Selector Valve COMPENSATOR, HYDRAULIC 405 32−51−30 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Hydraulic Compensator Installation of the Hydraulic Compensator PRESSURE SWITCH 405 32−51−35 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the NWS Pressure Switch Installation of the NWS Pressure Switch SWIVEL ASSEMBLY 407 32−51−40 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Swivel Assembly Installation of the Swivel Assembly CHECK VALVE Removal/Installation 404 32−51−45 401 Effectivity: ON A/C ALL General Master EFFECTIVITY: ALL 39 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Page Removal of the Check Valve Installation of the Check Valve STEERING ACTUATING MECHANISM 404 32−52−00 Description and Operation 1 Effectivity: ON A/C ALL General Component Details Steering Actuator Actuator Piping Assembly Operation Component Location Index ACTUATOR, STEERING 32−52−01 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Steering Actuator Installation of the Steering Actuator 404 Inspection/Check 601 Effectivity: ON A/C ALL General Visual Inspection of the Steering Actuator ACTUATOR PIPING ASSEMBLY Removal/Installation 32−52−05 401 Effectivity: ON A/C ALL General Removal of the Actuator Piping Assembly Installation of the Actuator Piping Assembly Master EFFECTIVITY: ALL 406 40 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject SWIVEL VALVE, STEERING ACTUATOR 32−52−10 Page Removal/Installation Effectivity: ON A/C ALL General Removal of the Steering Actuator Swivel−Valve Installation of the Steering Actuator Swivel Valve 406 Inspection/Check 601 Effectivity: ON A/C ALL General External Leak Check of the Steering Actuator Swivel−Valve POSITION AND WARNING 32−60−00 Description and Operation 1 Effectivity: ON A/C ALL General Description Proximity Sensor System Operation Proximity Sensor System PROXIMITY SENSOR SYSTEM (PSS) Description and Operation 32−61−00 1 Effectivity: ON A/C ALL General Component Details Proximity Sensor Electronic Unit Proximity Sensor 2 Proximity Switch Microswitch Operation Component Location Index Master EFFECTIVITY: ALL 4 41 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Maintenance Practices Page 201 Effectivity: ON A/C ALL General Put the Aircraft in a Weight−Off−Wheels Configuration With the Aircraft on the Ground Remove the Aircraft from the Weight−Off−Wheels 206 Configuration with the Aircraft on the Ground Put the Aircraft in a Weight−On−Wheels 208 Configuration With the Aircraft on Jacks Remove the Aircraft from the Weight−On−Wheels 209 Configuration with the Aircraft on Jacks Adjustment/Test 501 Effectivity: ON A/C ALL General Operational Test of the PSS Functional Test of the Proximity Sensor 504 Electronics Unit (PSEU) Power−Up Test of the PSS 506 Functional Test of the Proximity Sensors 508 Testing the Proximity Sensors with Calibrated 510 Targets UNIT, PROXIMITY SENSOR ELECTRONIC (PSEU) Maintenance Practices 32−61−01 201 Effectivity: ON A/C ALL General PSEU System Test Initiation and Fault Codes List Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the PSEU Installation of the PSEU Master EFFECTIVITY: ALL 404 42 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject PROXIMITY SENSOR 32−61−05 Page Removal/Installation Effectivity: ON A/C ALL General Removal of the Proximity Sensor − MLG Uplock Installation of the Proximity Sensor − MLG Uplock 405 Removal of the Proximity Sensor − MLG 408 Downlock Installation of the Proximity Sensor − MLG 413 Downlock Removal of the Proximity Sensor − MLG WOW 417 Installation of the Proximity Sensor − MLG WOW 422 Removal of the Proximity Sensor − NLG Downlock 426 Installation of the Proximity Sensor − NLG 430 Downlock Removal of the Proximity Sensor − NLG WOFFW 433 Installation of the Proximity Sensor − NLG 437 WOFFW Removal of the Proximity Sensor − NLG Oleo 440 Centered/Extended Installation of the Proximity Sensor − NLG Oleo 447 Centered/Extended Removal of the Proximity Sensor − NLG Uplock 454 Installation of the Proximity Sensor − NLG Uplock 458 Removal of the Closed−Position Proximity Sensor 461 − NLG Forward Door Installation of the Closed−Position Proximity 466 Sensor − NLG Forward Door Removal of the Proximity Sensor − NLG Forward 471 Door Uplock Installation of the Proximity Sensor − NLG 475 Forward Door Uplock Master EFFECTIVITY: ALL 43 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Chapter Section Subject Subject Adjustment/Test Page 501 Effectivity: ON A/C ALL General Adjustment of the Landing Gear Proximity Sensors Inspection/Check 601 Effectivity: ON A/C ALL General Clearance Check of the Landing Gear Proximity Sensors HARNESS ASSEMBLY, MICROSWITCH 32−61−15 Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the Microswitch Harness Assembly Installation of the Microswitch Harness Assembly ELECTRICAL HARNESS, MAIN LANDING GEAR 406 32−61−20 (MLG) Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the MLG Electrical Harness − Outboard Installation of the MLG Electrical Harness − 411 Outboard Removal of the MLG Electrical Harness − Inboard 422 Installation of the MLG Electrical Harness − 433 Inboard Master EFFECTIVITY: ALL 44 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject ELECTRICAL HARNESS, NOSE LANDING GEAR 32−61−25 Page (NLG) Removal/Installation 401 Effectivity: ON A/C ALL General Removal of the NLG Electrical Harness Installation of the NLG Electrical Harness STRUT, TAIL BUMPER 408 32−71−01 Removal/Installation 401 Effectivity: ON A/C 7004−7017 General Removal of the Tail Bumper Strut Installation of the Tail Bumper Strut WEAR PAD 404 32−71−05 Removal/Installation 401 Effectivity: ON A/C 7004−7017 General Removal of the Wear Pad Installation of the Wear Pad SHOE FITTING Removal/Installation 403 32−71−10 401 Effectivity: ON A/C 7004−7017 General Removal of the Shoe Fitting Installation of the Shoe Fitting Master EFFECTIVITY: ALL 404 45 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subject Chapter Section Subject BRUSH SEALS 32−71−15 Page Removal/Installation Effectivity: ON A/C 7004−7017 General Removal of the Brush Seals Installation of the Brush Seals Master EFFECTIVITY: ALL 403 46 32−Contents Aug Page 10/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL LANDING GEAR SYSTEM − DESCRIPTION AND OPERATION 1. General A. The aircraft is equipped with a tricycle−type landing gear system with direct action shock struts. The landing gear system is electrically activated and hydraulically operated by hydraulic systems No. 2 and No. 3. The landing gear system includes the systems that follow: **ON A/C 7004−7017 ± Main landing gear (MLG) (32−10−00) ± Nose landing gear (NLG) (32−20−00) ± Extension/retraction system (32−30−00) ± Wheel and brake system (32−40−00) ± Steering system (32−50−00) ± Indicating and warning system (32−60−00) ± Support system (32−70−00). **ON A/C 7003, 7018−7067, 7069−7990, 8000−8064, 8066−8068 ± Main landing gear (MLG) (32−10−00) ± Nose landing gear (NLG) (32−20−00) ± Extension/retraction system (32−30−00) ± Wheel and brake system (32−40−00) ± Steering system (32−50−00) ± Indicating and warning system (32−60−00). **ON A/C ALL 2. Description A. Main Landing Gear Refer to Figure 1. (1) The MLG is a double−wheel, inboard−retracting, and lever−suspension type. The MLG system is mechanically locked in the extended position by the MLG side stay actuator and is held in the retracted position by a mechanical uplock assembly (32−30−00). The MLG retracts into the main wheel well. Each MLG has a main fitting assembly, a MLG shock strut, a trailing arm, a MLG axle, and two swivel coupling assemblies. (2) When the MLG is retracted, it is covered by the MLG doors. The MLG doors are mechanically linked to the MLG. The MLG door opens or closes when the MLG extends or retracts. Each MLG door has a MLG door assembly, a door brush, a push/pull rod, a bellcrank assembly, and a rod end. B. Nose Landing Gear Refer to Figure 2. (1) The NLG is a double−wheel and forward−retracting type. It retracts into the nosewheel well. The NLG is mechanically locked in the extended position and is held in the retracted position by a mechanical uplock assembly. The NLG has a Master EFFECTIVITY: See Pageblock 32−00−00 page 1 Page 1 32−00−00 Dec 10/2005 C AIRCRAFT MAINTENANCE MANUAL C. D. shock strut assembly, a drag brace, a torque link assembly, a NLG axle, and seals. (2) When the NLG is retracted, it is enclosed by two forward doors and one rear door. The forward doors operate hydraulically. The rear door is mechanically linked to the NLG and operates in conjunction with the NLG extension/retraction. During a normal extension operation, the forward doors open a few seconds before the NLG is released from the uplock assembly. The forward doors close when the NLG is fully extended. During the retraction, the forward doors open before the NLG starts its retraction. Extension/Retraction System (1) The extension/retraction system is separated into four subsystems: ± The MLG extension/retraction ± The NLG extension/retraction ± The manual release system. The normal extension/retraction uses hydraulic pressure from system No. 3 to extend and retract the NLG and the MLG. (2) In abnormal situations, the NLG is extended manually by gravity and the MLG is extended with gravity assisted by the dowlock assist actuator. The downlock actuator is hydraulically operated by system No. 2. The forward doors are pushed open by the weight of the NLG. (3) The control system has a landing−gear control panel installed on the center pedestal. The control panel has an operating handle which sends extension and retraction signals to the proximity sensor electronic−unit which operates the selector valves for the extension or retraction. (4) The NLG extension/retraction has an extension/retraction actuator, an uplock assembly, a selector valve, a priority valve, restrictors, and check valves. (5) The MLG extension/retraction has two MLG side stay actuators, one for each MLG. It has a selector valve, an uplock assembly for each gear, a priority valve, a runaround and bypass valve, restrictors, and check valves. Wheel and Brake System Refer to Figure 3. (1) The wheel and brake system has: ± Two nosewheel/tire assemblies ± Four main wheel/tire assemblies ± The inboard and outboard brakes and their mechanisms ± The antiskid system ± The parking brake system ± The brake−temperature monitoring system ± The brake−pressure monitoring system. (2) Each nosewheel/tire assembly has a tire and a wheel assembly. The nosewheel/tire assemblies give the aircraft directional control and support on the ground. Each nosewheel/tire assembly is installed on each side of the NLG axle. The wheel assembly is composed of the inboard and outboard halves which are bolted together. Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 2 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (3) Each main wheel/tire assembly has a tire and a wheel assembly. The main wheel/tire assemblies hold the aircraft during landing and taxiing. Each main wheel/tire assembly has a tire and a wheel assembly. The wheel assembly is composed of the wheel, the removable flange, the retaining ring, the heat shield, the fusible plugs, and the tire pressure indicator. Refer to Figure 4. (4) The brake system is used to stop the aircraft during ground operations. There are two brake units installed on each MLG. The hydraulic components of the main−gear brake system are installed in the main wheel well and the nose hydraulics compartment. (5) The brake system has: ± The pilot’s and copilot’s brake pedals ± A brake control mechanism assembly (that includes two brake control valves) ± Two brake−control push/pull cable−mechanisms ± Two brake accumulators ± Four volumetric fuses ± Four brake units ± Check valves. These components are installed in the flight compartment, the nose hydraulic compartment, the main wheel well, and on the the MLG. Refer to Figure 5. (6) The antiskid control system prevents skids during the operation of the brakes on landings and taxis. The components of the antiskid system are installed in the main avionics compartment, the main wheel well, and on the MLG. The antiskid control system reads the speed of each wheel and finds if it is started a skid. When one of the wheels is stopped, it releases the hydraulic brake pressure from the applicable brake unit which lets the wheel turn. (7) The antiskid control system has four wheel speed transducers, one antiskid control unit, two antiskid control valves, four drivecaps, and two antiskid relays. Refer to Figure 6. (8) The parking brake system locks the brakes and prevents movement of the aircraft when parked. The brake pedals, the inboard brake units, and hydraulic system No. 3 are interfaced with the parking brake system. (9) The parking brake system has a parking brake handle, push/pull cables, a parking−brake shutoff valve, and a parking brake microswitch. The parking brake is applied when you push on the brake pedals, pull and turn the parking brake handle and apply the parking brake. The hydraulic pressure applied by the brake pedals is locked by the parking−brake shutoff valve which keeps the inboard brakes applied. Refer to Figure 7. (10) The brake−temperature monitoring system gives the pilot brake temperature information and shows it on the engine indication and crew alerting system (EICAS). The thermocouple sensors installed in the brake units send an electrical signal which is decoded by the brake−temperature monitoring unit. The brake−temperature monitoring unit sends the data to the data control unit and then to the EICAS. Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 3 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Refer to Figure 8. (11) The brake−pressure monitoring system gives brake pressure information of the inboard and outboard brake systems. The brake−pressure monitoring system has two pressure transducers, one for the inboard brake system and one for the outboard brake system. The two pressure transducers are installed in the nose hydraulics compartment. E. Steering System Refer to Figure 9. (1) The steering system has: ± A handwheel control module ± A rudder pedal rotary−variable−differential−transformer ± An electronic control unit ± An electrohydraulic module ± Two position feedback sensors ± A solenoid selector valve ± A hydraulic compensator ± A pressure switch ± Two steering actuators ± Swivel−valve banjo−piping assemblies. (2) The steering system is a steer−by−wire system, electrically controlled and hydraulically operated. The steering system has a range of 70 degrees left and right of the center line. The torque link assembly has to be disconnected during towing procedures. The rudder give a steering motion to the aircraft of 7 degrees left and right of the center line. (3) The components of the steering system are installed in the nose hydraulics compartment and on the NLG. The steering system operates with hydraulic system No. 3. F. Indicating and Warning System Refer to Figure 10. (1) The indicating and warning system gives information on the position of some aircraft components during flight or ground operations. The position and warning information is used by other systems in the aircraft. (2) The proximity sensor system is interfaced with 38 other aircraft systems. Each of the systems uses the outputs or give inputs to the proximity sensor system. (3) The proximity sensor system finds the position of the targets. This position is decoded and then the system gives command signals, this lets the other aircraft systems operate correctly in the air or ground mode. The proximity sensor system has the proximity sensor electronic−unit, multiple proximity sensors, and switches and microswitches installed at different locations in the aircraft. **ON A/C 7004−7017 G. Support System Refer to Figure 11. Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 4 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (1) The support system has the tail bumper assembly. The tail bumper assembly is installed on the tail cone of the aircraft. The tail bumper assembly is used during landing. The tail bumper assembly has a tail bumper strut, a shoe fitting, a wear pad, and brush seals. Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 5 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL MAIN DOOR AND MECHANISM SYSTEM MAIN LANDING GEAR ram3210000_001(1).dc, mb/pb, 01/12/93 FWD MLG System Figure 1 Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 6 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL DOOR MECHANISM FORWARD DOORS ram3220000_001(1).dc, jp/pm, 09/11/95 REAR DOOR NOSE LANDING GEAR NLG System Figure 2 Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 7 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TIRE PREFORMED PACKING INFLATION VALVE WHEEL A RETAINING RING B REMOVABLE FLANGE TAPERED ROLLER BEARING TAPERED ROLLER BEARING FUSEABLE PLUG INSTALLATION PROVISION FOR A TIRE PRESSURE INDICATOR TIRE RETAINING RING HEAT SHIELD REMOVABLE FLANGE RETAINING RING RETAINING RING OVERINFLATION PLUG (OPTIONAL) OR INSTALLATION PROVISION FOR A TIRE PRESSURE INDICATOR B PLUG ram3241000_001.dc, jp/pb, 24/08/92 REMOVABLE FLANGE TIRE Wheel/Tire Assemblies Figure 3 (Sheet 1 of 2) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 8 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TIRE INNER HALF OF THE WHEEL PREFORMED PACKING OUTER HALF OF THE WHEEL HIGH TENSILE BOLT INSTALLATION PROVISION FOR A TIRE PRESSURE INDICATOR ROLLER BEARING INFLATION VALVE ram3242000_001.dc, jp/pb, 24/08/92 ROLLER BEARING Wheel/Tire Assemblies Figure 3 (Sheet 2 of 2) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 9 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL ram3243000_003.dc, gm/sb, 24/08/92 121 AL DUAL BRAKE CONTROL VALVE Brake System Figure 4 (Sheet 1 of 6) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 10 Apr 20/2004 C FORWARD PRESSURE BULKHEAD BRAKE CONTROL PUSH/PULL MECHANISM ram3243000_008.dc, cr/ks, 24/08/92 AIRCRAFT MAINTENANCE MANUAL Brake System Figure 4 (Sheet 2 of 6) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 11 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL BRAKE ACCUMULATOR ram3243000_004.dc, ss/ks, 24/08/92 121AL Brake System Figure 4 (Sheet 3 of 6) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 12 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL R DE LIN CY EM ram3243000_005.dc, ss/ks, 24/08/92 ST SY VOLUMETRIC FUSE Brake System Figure 4 (Sheet 4 of 6) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 13 Apr 20/2004 C ram3243000_007.dc, ks, 24/08/92 AIRCRAFT MAINTENANCE MANUAL BRAKE UNIT Brake System Figure 4 (Sheet 5 of 6) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 14 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL B 121 AL A B DUAL−BRAKE CONTROL VALVE B CHECK VALVE ram3243000_006.dc, MB, 18/07/91 A Brake System Figure 4 (Sheet 6 of 6) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 15 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL WHEEL SPEED TRANSDUCER ram3244000_003.dc, JP, 08/07/91 DRIVE CAP Antiskid Control System Figure 5 (Sheet 1 of 3) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 16 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL B A B ANTI−SKID CONTROL VALVE ASCU ram3244000_004.dc, JP, 09/07/91 A Antiskid Control System Figure 5 (Sheet 2 of 3) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 17 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A ram3244000_005.dc, DB/GG, 08/08/91 JB11 ANTISKID RELAY A Antiskid Control System Figure 5 (Sheet 3 of 3) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 18 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL B 832 A 121 AL (REF.) CENTER PEDESTAL B PARKING BRAKE HANDLE ASSEMBLY ram3245000_004.dc, jp, 24/08/92 A Parking Brake System Figure 6 (Sheet 1 of 3) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 19 Apr 20/2004 C ram3245000_001.dc, jh/jp, 24/08/92 AIRCRAFT MAINTENANCE MANUAL PARKING BRAKE SHUTOFF VALVE Parking Brake System Figure 6 (Sheet 2 of 3) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 20 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A B B DUAL−BRAKE CONTROL VALVE ram3245000_002.dc, KS, 16/06/91 A MICROSWITCH Parking Brake System Figure 6 (Sheet 3 of 3) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 21 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A A THERMOCOUPLE SENSOR B BTMU ram3246000_003.dc, JP, 08/08/91 B Brake Temperature Monitoring System Figure 7 Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 22 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL PRESSURE TRANSDUCER ram3247000_001.dc, KS, 16/06/91 121 AL Brake Pressure Monitoring System Figure 8 Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 23 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL C A B C RUDDER PEDAL RVDT B HANDWHEEL STEERING CONTROL MODULE ram3251000_003.dc, JP, 11/07/91 A ECU Steering System Figure 9 (Sheet 1 of 5) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 24 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL C A B PRESSURE SWITCH B C SOLENOID SELECTOR VALVE HYDRAULIC COMPENSATOR ram3251000_002.dc, JP,10/07/91 A Steering System Figure 9 (Sheet 2 of 5) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 25 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A B FW D NOSE LANDING GEAR B ELECTROHYDRAULIC MODULE ram3251000_006(1).dc, pj/pb, 22/12/92 A Steering System Figure 9 (Sheet 3 of 5) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 26 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A B B POSITION FEEDBACK SENSOR ram3251000_004.dc, jp, 24/08/92 A Steering System Figure 9 (Sheet 4 of 5) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 27 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REF. ELECTRO HYDRAULIC MODULE CYLINDER A PIPING ASSEMBLY ram3252000_001.dc, jp, 24/08/92 PISTON ROD SWIVEL JOINT A STEERING ACTUATOR GREASE FITTING Steering System Figure 9 (Sheet 5 of 5) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 28 Apr 20/2004 C ram3261000_006.dc, SS/SS, 30/07/91 AIRCRAFT MAINTENANCE MANUAL Indicating and Warning System Figure 10 (Sheet 1 of 5) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 29 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A ram3261000_002.dc, jp, 24/08/92 A A PROXIMITY SENSOR Indicating and Warning System Figure 10 (Sheet 2 of 5) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 30 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A ram3261000_001.dc, jp, 24/08/92 A A PROXIMITY SENSOR Indicating and Warning System Figure 10 (Sheet 3 of 5) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 31 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A A A PROXIMITY SWITCH ram3261000_003.dc, gm/ks, 24/08/92 A Indicating and Warning System Figure 10 (Sheet 4 of 5) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 32 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A ram3261000_007.dc, RF, JP, 19/08/91 A A MICRO SWITCH Indicating and Warning System Figure 10 (Sheet 5 of 5) Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 33 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TAIL BUMPER STRUT BRUSH SEALS WEAR PAD ram3271000_001.dc, JP, 27/04/92 SHOE FITTING Support System Figure 11 Master EFFECTIVITY: See Pageblock 32−00−00 page 1 32−00−00 Page 34 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL LANDING GEAR SYSTEM − INSPECTION/CHECK 1. General A. The maintenance procedures that follow are for the static and dynamic leakage checks of the landing gear system components. The static leakage check is done to make sure that there is not excessive leakage of hydraulic fluid through the seals of a landing gear system component when it is pressurized. The dynamic leakage check is done to make sure that there is not excessive leakage through the seals of a landing gear system component when it is pressurized and operated. B. These procedures apply to components that have static seals (seals that are not against components that can move) and dynamic seals (seals that are adjacent to component surfaces that can move). NOTE: A static check can be done for components with dynamic seals (with the related component/seal not operated). These seals are referred to as "Static−Dynamic" seals inTable 601 and in Table 602. TASK 32−00−00−790−801 External Leak Check of the Landing Gear 1. Job Set−Up Information Subtask 32−00−00−943−001 A. Tools and Equipment REFERENCE G601R101223−1/2 None specified DESIGNATION Cover − MLG wheels Flat pan Subtask 32−00−00−944−001 B. Consumable Materials REFERENCE 05−001 11−009 DESIGNATION Cloths, cleaning, low lint Alcohol, denatured ethyl (ethanol) Subtask 32−00−00−946−001 C. Reference Information REFERENCE TASK 12−00−06−863−801 TASK 12−00−06−863−802 TASK 12−00−06−863−803 TASK 12−00−06−863−804 DESIGNATION Pressurize Hydraulic Systems No. 1 and No. 2 Release Hydraulic Pressure − Systems No. 1 and No. 2 Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 Master EFFECTIVITY: See Pageblock 32−00−00 page 601 32−00−00 Page 601 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REFERENCE TASK 12−12−32−610−802 TASK 12−12−32−610−803 TASK 29−00−00−910−801 TASK 32−22−01−980−801 TASK 32−22−01−980−802 TASK 32−30−00−710−802 TASK 32−43−26−790−801 TASK 32−43−26−790−802 TASK 32−51−00−710−802 TASK 32−52−10−790−801 TASK 51−26−00−110−802 TASK 53−83−01−000−801 TASK 53−83−01−400−801 DESIGNATION Servicing (Oil and Nitrogen) of the MLG Shock Strut Servicing (Oil and Nitrogen) of the NLG Shock Strut Hydraulic Safety Precautions Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors Landing Gear Extension and Retraction − Maintenance Practices Leakage Check of the Brake Unit Brake Unit Piston Leakage In−Service Limits Operational Test of the Nosewheel Steering − Torque Link Assembly Disconnected External Leak Check of the Steering Actuator Swivel−Valve Detergent (Alkaline) Cleaning Removal of the MLG Wheel Bin Installation of the MLG Wheel Bin 2. Job Set−Up Subtask 32−00−00−010−001 A. Remove the MLG wheel bin if necessary for access to the inspection area (Ref. TASK 53−83−01−000−801). WARNING: IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. B. If the component to be checked is in the NLG bay, open and isolate the NLG forward doors if necessary, for access to the inspection area (Ref. TASK 32−22−01−980−801). Master EFFECTIVITY: See Pageblock 32−00−00 page 601 32−00−00 Page 602 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−00−00−910−002 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND /OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND /OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: C. Subtask 32−00−00−280−001 DO NOT LET HYDRAULIC FLUID GET ON THE BRAKE UNITS OR THE TIRES. HYDRAULIC FLUID CAN CAUSE DAMAGE TO THE BRAKE UNITS AND THE TIRES. D. Make sure that the aircraft tires in the inspection area are not contaminated with hydraulic fluid. If hydraulic fluid contamination of a tire is suspected, do the steps that follow: NOTE: If the rubber surface of the contaminated aircraft tire has deteriorated or feels soft or spongy, remove the tire from service. (1) Wash the contaminated area on the tire with denatured alcohol. (2) Clean the contaminated tire with soap (alkaline detergent) and water (Ref. TASK 51−26−00−110−802). (3) If hydraulic leakage is suspected and the aircraft will not be in service for an extended period of time, protective covers should be installed on the tires to avoid hydraulic fluid contamination. CAUTION: DO NOT LET HYDRAULIC FLUID GET ON THE BRAKE UNITS OR THE TIRES. HYDRAULIC FLUID CAN CAUSE DAMAGE TO THE BRAKE UNITS AND THE TIRES. E. If the component to be inspected is located in the MLG bay or on the MLG, make sure that the rotors/stators of the applicable brake unit are not contaminated with hydraulic fluid. CAUTION: 3. Procedure Subtask 32−00−00−790−001 Refer to Table 601. A. Do the static leakage check of the suspect landing gear component as follows: NOTE: This check applies to leakage rates for static seals and "static−dynamic" seals and is measured in drops in relation to time. NOTE: The steps that follow are the same for all landing gear components that are externally pressurized except for brake units. Refer to TASK 32−43−26−790−801 and TASK 32−43−26−790−802 for the brake unit leakage test and the brake unit leakage rates. NOTE: Leakage rates for the steering actuator swivel−valves are given for the mounting faces only. Refer to TASK 32−52−10−790−801 for other steering actuator swivel−valve leakage rates. Master EFFECTIVITY: See Pageblock 32−00−00 page 601 32−00−00 Page 603 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL COMPONENT Actuating Cylinder SEAL SEAL FUNCTION Rod Seal Rod Seal End Cap Low Pressure Swivel High Pressure High Pressure Static seal−mating surfaces Valves Fittings Manual Stem Manual Stem Flared or Flareless Boss Seal LEAKAGE RATE NOTES [1] AND [2] TYPE OF SEAL Dynamic NOTE [3] 1 drop /5 cycles Static−Dynamic NOTE 1 drop/15 minutes [4] Static Wetting (insufficient to form a drop/30 minutes Static 1 drop/15 minutes NOTE [5] Static 1 drop/15 minutes NOTE [5] Dynamic 1 drop /5 cycles NOTE [5] Static Wetting (insufficient to form a drop/30 minutes) Dynamic 1 drop/5 cycles Static−Dynamic 1 drop/15 minutes Static None Static 1 drop/30 minutes (lower rate if fitting is accessible) NOTE [6] Brake Unit All brake units seals NOTE [1]: 20 drops = 1 ml (1 cc) NOTE [2]: The leakage rates given are at a component temperature of 100 °F (38 °C) NOTE [3]: Dynamic − refers to leakage through a dynamic seal as the component is operated through a number of cycles. NOTE [4]: Static−Dynamic − refers to static leakage through a dynamic seal. NOTE [5]: Refer to TASK 32−52−10−790−801 for other steering actuator swivel−valve leakage rates. NOTE [6]: Refer to TASK 32−43−26−790−801 and to TASK 32−43−26−790−802 for the brake unit leakage test and the bracke unit leakage rates. Allowable Static and Dynamic Leakage Rates for Landing Gear Components Table 601 (1) Do one of the steps that follows, as necessary, to operate the applicable component: (a) Pressurize hydraulic system No. 3 (Ref. TASK 12−00−06−863−803), if the component to be checked is related to one of the systems that follows: ± The NLG or MLG extension/retraction system ± The nose−wheel steering system ± The actuation system for the NLG forward doors. Master EFFECTIVITY: See Pageblock 32−00−00 page 601 32−00−00 Page 604 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (2) (3) (4) (5) (6) (7) (8) (9) (b) If the component to be checked is related to the MLG downlock assist actuator, pressurize hydraulic system No. 2 (Ref. TASK 12−00−06−863−801). If the component is related to the nosewheel steering system, do the operational test of the nosewheel steering (with the torque link disconnected) to operate the nosewheel steering system through five complete full stroke cycles to seat the seals in that component (Ref. TASK 32−51−00−710−802). If the component is related to the landing gear extension/retraction system, operate the landing gear through five cycles to seat the seals in that component (Ref. TASK 32−30−00−710−802). NOTE: In order to avoid unnecessary grounding of an aircraft, the requirement to operate the landing gear extension/retraction system (or the MLG downlock assist system) through five cycles can be ignored if you do the static leakage check again immediatly after the last flight of the day. It is not necessary to operate these systems through five cycles as normal operation of these systems during the day is equivalent to these systems being operated. Use a clean lint free cloth to remove dirt and hydraulic fluid from the areas adjacent to the hydraulic seals for the landing gear component. Put a flat pan in position below the applicable component. Measure the leak for the specified time shown in Table 601 as follows: (a) Start timing when the first drop falls and begin count at the next drop. (b) Observe the component for the time specified in Table 601. NOTE: Make sure that the leakage rates are measured from one leak source only. If pressurized, release the hydraulic pressure from systems No. 2 (Ref. TASK 12−00−06−863−802). If pressurized, release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). If leakage was more than the maximum given in Table 601, replace the applicable component with a serviceable one. Subtask 32−00−00−790−002 Refer to Table 601. B. Do a dynamic leakage check of the applicable landing gear component as follows: NOTE: This check applies to leakage rates for both static seals and dynamic seals and is measured in drops in relation to cycles. (1) Do one of the steps that follows, as necessary, to operate the applicable component: (a) If the component to be checked is related to the MLG downlock assist actuator, pressurize hydraulic system No. 2 (Ref. TASK 12−00−06−863−801). (b) Pressurize hydraulic system No. 3 (Ref. TASK 12−00−06−863−803), if the component to be checked is related to one of the systems that follows: ± The NLG or MLG extension/retraction system ± The nosewheel steering system Master EFFECTIVITY: See Pageblock 32−00−00 page 601 32−00−00 Page 605 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL ± The actuation system for the NLG forward doors. (2) If the component is related to the nosewheel steering system, operate the nosewheel steering system through five complete full stroke cycles to seat the seals in that component (Ref. TASK 32−51−00−710−802). (3) If the component is related to the landing gear extension/retraction system (or the MLG downlock assist system), operate the landing gear through five cycles to seat the seals in that component (Ref. TASK 32−30−00−710−802). (4) Use a clean lint free cloth to remove dirt and hydraulic fluid from the areas adjacent to the hydraulic seals for the landing gear component. (5) Put a flat pan in position below the applicable component. (6) If the component is related to the nosewheel steering system, operate the nosewheel steering system through 10 cycles (Ref. TASK 32−51−00−710−802). At the same time, measure the leak for the specified number of cycles shown in Table 601 as follows: (a) Start the count of cycles when the first drop falls (if the first drop falls before the 10 cycles are complete). (b) Observe the component for the number of cycles specified in Table 601. (c) Stop the count at the end of the last cycle. NOTE: Make sure that the leakage rates are measured from one leak source only. (7) If the component is related to the landing gear extension/retraction system (or the MLG downlock assist system), operate the landing gear through 10 cycles (Ref. TASK 32−30−00−710−802). At the same time, measure the leak for the specified number of cycles shown in Table 601 as follows: (a) Start the count of cycles when the first drop falls. (b) Observe the component for the number of cycles specified in Table 601. (c) Stop the count at the end of the last cycle. NOTE: Make sure that the leakage rates are measured from one leak source only. (8) Do one of the steps that follow to stop the operation of the applicable component: ± Release hydraulic pressure from systems No. 2 (Ref. TASK 12−00−06−863−802) ± Release hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). (9) If leakage was more than the maximum given in Table 601, replace the applicable component with a serviceable one. Master EFFECTIVITY: See Pageblock 32−00−00 page 601 32−00−00 Page 606 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−00−00−790−003 C. Do a static leakage check for a MLG shock strut or for the NLG shock strut as follows: NOTE: This check applies to leakage rates for "static−dynamic" seals and is measured in drops in relation to time. NOTE: The steps that follow are for the NLG and MLG shock struts. These components are internally pressurized. Do a check to make sure that the applicable shock strut is serviced satisfactorily (Ref. TASK 12−12−32−610−802 or TASK 12−12−32−610−803) before you do this procedure. NOTE: The procedure for the dynamic leakage test does not apply to the NLG and the MLG shock struts. It is not necessary to cycle the shock strut during this procedure. COMPONENT SEAL NLG or MLG Shock Struts SEAL FUNCTION TYPE OF SEAL Piston Seal (Tee Static−Dynamic seal) NOTE [3] LEAKAGE RATE NOTES [1] and [2] 2 drops/day seepage is acceptable. NOTE [4] NOTE [1]: NOTE [2]: 20 drops=1 ml (1 cc). The leakage rates given are at a component temperature of 100 °F (38 °C). NOTE [3]: Static−Dynamic − refers to static leakage through a dynamic seal. NOTE [4]: Refer to the leak check procedure for an alternate leak rate if a leak is seen within 10 days of the initial pressurization of a the shock strut. Allowable Static Leakage Rate for Landing Gear Shock Struts Table 602 (1) Use a clean lint free cloth to remove dirt and hydraulic fluid from the areas adjacent to the hydraulic leak. (2) Put a flat pan in position below the applicable shock strut. (3) Do the steps that follow if the shock strut has been in service for more than 10 days: ± Since it was initially pressurized at initial installation ± After an internal seal replacement in service ± Or since it was completely depressurized for maintenance. (a) Measure the leak for the specified time shown in Table 602 as follows: NOTE: Make sure that the leakage rates are measured from one leak source only. 1 Start timing when the first drop falls and begin the count at the next drop. 2 Observe the component for the time specified in Table 602. (b) If leakage was more than the maximum given in Table 602, replace the applicable shock strut with a serviceable one. Master EFFECTIVITY: See Pageblock 32−00−00 page 601 32−00−00 Page 607 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (4) Do the steps that follow if the shock strut has been in service for less than 10 days: ± Since it was initially pressurized at initial installation ± After an internal seal replacement in service ± Or if it was completely depressurized for maintenance. NOTE: These steps do not apply after the initial 10 day period. (a) Measure the amount of leakage the occurs in one day as follows: NOTE: Make sure that the leakage rates are measured from one leak source only. 1 Start timing when the first drop falls and begin the count at the next drop. 2 Observe the component for one day. If the leakage rate does not exceed three drops/day, this seepage is acceptable. 3 Use a clean lint free cloth to wipe out the oil seepage. 4 Monitor the shock strut each day during the initial 10 day period to make sure that the shock strut remains correctly serviced (Ref. TASK 12−12−32−610−802 or TASK 12−12−32−610−803). 4. Close Out Subtask 32−00−00−863−001 A. B. Remove the hydraulic pressure from systems No. 2 as necessary (Ref. TASK 12−00−06−863−802). Remove the hydraulic pressure from system No. 3 as necessary (Ref. TASK 12−00−06−863−804). Subtask 32−00−00−410−001 C. D. Install the MLG wheel bin if it was removed (Ref. TASK 53−83−01−400−801). Close the NLG forward doors (Ref. TASK 32−22−01−980−801) if they were opened in this task. Subtask 32−00−00−941−001 E. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−00−00 page 601 32−00−00 Page 608 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL LANDING GEAR SYSTEM − CLEANING/PAINTING 1. General CAUTION: A. DO NOT USE HIGH PRESSURE WASHING EQUIPMENT ON LANDING GEAR COMPONENTS. HIGH PRESSURE JETS CAN PUSH CLEANING COMPOUND OR WATER INTO BEARINGS, JOINTS, BRAKES, SEALS, ELECTRICAL CONNECTORS, AND OTHER SEALED COMPONENTS. LIQUIDS THAT GET INTO THESE AREAS CAN CAUSE CORROSION AND CAN FREEZE DURING AIRCRAFT FLIGHT. The maintenance procedure that follows is for the non−pressure hand wash of the landing gear components installed on the aircraft. The non−pressure hand wash is the only procedure permitted to clean landing gear components. NOTE: High pressure washing is considered harmful to certain areas of the landing gear, especially at dynamic joint locations where the cleaning solution and water can be forced into cavities. This trapped moisture can increase corrosion which could greatly decrease the life of some components. TASK 32−00−00−100−801 Landing Gear Structure Cleaning Procedure (Non−Pressure Wash) 1. Job Set−Up Information Subtask 32−00−00−943−002 A. Tools and Equipment REFERENCE None specified None specified None specified None specified DESIGNATION Lint−free cloth − Commercial Sponge − Commercial Soft bristle brushes − Commercial Spray Equipment Subtask 32−00−00−944−002 B. Consumable Materials REFERENCE MIL−C−85570, Type I MIL−C−85570, Type 1A MIL−C−85570, Type II 06−013 DESIGNATION Cleaning compound, general use, (aromatic) Cleaning compound, general use, aerosol Cleaning compound, general use, (non−aromatic) Water−displacing, corrosion preventive compound Master EFFECTIVITY: See Pageblock 32−00−00 page 701 32−00−00 Page 701 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−00−00−946−002 C. Reference Information REFERENCE TASK 10−11−00−869−801 TASK 12−20−32−640−801 TASK 12−20−32−640−802 TASK 51−26−00−910−801 DESIGNATION Grounding of the Aircraft Lubrication of the Nose Landing Gear Lubrication of the Main Landing Gear Cleaning Safety Precautions 2. JOB SET−UP Subtask 32−00−00−910−001 A. B. C. D. E. Obey all the cleaning safety precautions (Ref.TASK 51−26−00−910−801). Do the grounding of the aircraft (Ref.TASK 10−11−00−869−801). If necessary, lubricate the nose landing gear (Ref.TASK 12−20−32−640−801). If necessary, lubricate the main landing gear (Ref.TASK 12−20−32−640−802). Examine the sealant around all the static joints. If the sealant is cracked, do the steps that follow: (1) Clean the adjacent area. (2) Spray 06−013 water−displacing, corrosion preventive compound around the area. (3) Dry the area with a clean cloth. 3. Procedure Subtask 32−00−00−110−001 A. Prepare the landing gear to be cleaned as follows: (1) Examine the landing gear to be cleaned to find the necessary mixture proportions. (2) Make sure that all the drain holes are free of blockages. (3) Install the nose landing gear and main landing gear covers. CAUTION: MAKE SURE THAT THE AIRCRAFT CLEANING SOLUTION WILL NOT COME IN CONTACT WITH THE MLG BRAKE UNITS. CONTAMINATION CAN CAUSE DAMAGE AND REDUCED PERFORMANCE OF THE BRAKES. CAUTION: DO NOT USE HIGH PRESSURE WASHING EQUIPMENT ON LANDING GEAR COMPONENTS. HIGH PRESSURE JETS CAN PUSH CLEANING COMPOUND OR WATER INTO BEARINGS, JOINTS, BRAKES, SEALS, ELECTRICAL CONNECTORS, AND OTHER SEALED COMPONENTS. LIQUIDS THAT GET INTO THESE AREAS CAN CAUSE CORROSION AND CAN FREEZE DURING AIRCRAFT FLIGHT. B. If you use MIL−C−85570 Type I Cleaning compound, general use, (aromatic), mix the cleaning compound as follows: (1) Use the ratio that follows to clean lightly dirty areas: Master EFFECTIVITY: See Pageblock 32−00−00 page 701 32−00−00 Page 702 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL C. D. (a) Add one part of the cleaning compound to sixteen parts of water. (b) Mix fully. (2) Use the ratio that follows to clean moderately dirty areas: (a) Add one part of the cleaning compound to nine parts of water. (b) Mix fully. (3) Use the ratio that follows to clean heavily dirty areas: (a) Add one part of the cleaning compound to four parts of water. (b) Mix fully. (4) Clean the landing gear as follows: (a) Flush the landing gear with clean water. (b) Put the MIL−C−85570 Type I cleaning compound on the landing gear. Apply it with a foam generator, soft bristle brush, or low pressure spray (maximum 25 psi). Fully cover the dirty area with the cleaning solution. (c) Use the applicator or a soft bristle brush to clean the area that is wet with the cleaning solution NOTE: Do not scrub along sealed joints. Always scrub across the sealed joints. (d) Flush the landing gear fully with a large quantity of clean water at low pressure (maximum 25 psi). (e) Dry the landing gear with clean cloths. If you use MIL−C−85570 Type IA Cleaning compound, general use, aerosol, do the steps that follow: (1) Spray the cleaning compound on the surface to be cleaned. Fully cover the dirty area with the cleaning solution. NOTE: Let the cleaning compound stay on the surface of the landing gear for a maximum of three minutes. (2) Scrub with a soft bristle brush or rub with a clean cloth. NOTE: Do not scrub along sealed joints. Always scrub across the sealed joints. (3) Flush the landing gear fully with a large quantity of clean water at low pressure (maximum 25 psi). (4) Dry the landing gear with clean cloths. If you use MIL−C−85570 Type II Cleaning compound, general use, (non−aromatic), mix the cleaning compound as follows: (1) Use the ratio that follows to clean lightly dirty areas: (a) Add one part of the cleaning compound to nine parts of water. (b) Mix fully. (2) Use the ratio that follows to clean moderately dirty areas: (a) Add one part of the cleaning compound to four parts of water. (b) Mix fully. (3) Use the ratio that follows to clean heavily dirty areas: Master EFFECTIVITY: See Pageblock 32−00−00 page 701 32−00−00 Page 703 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL (a) Add one part of the cleaning compound to one part of water. (b) Mix fully. (4) Clean the landing gear as follows: (a) Flush the landing gear with clean water. (b) Put the MIL−C−85570 Type II cleaning compound on the landing gear. Apply it with a foam generator, soft bristle brush, or low pressure spray (maximum 25 psi). Fully cover the dirty area with the cleaning solution. (c) Use the applicator or a soft bristle brush to clean the area that is wet with the cleaning solution NOTE: Do not scrub along sealed joints. Always scrub across the sealed joints. (d) Flush the landing gear fully with a large quantity of clean water at low pressure (maximum 25 psi). (e) Dry the landing gear with clean cloths. 4. Close Out Subtask 32−00−00−640−003 A. If necessary, lubricate the components that follow if detergent cleaning was done on the components: NOTE: Cleaning solutions and pressurized water will remove or contaminate lubricants that are applied to wear surfaces and can cause corrosion and component wear. (1) Lubricate the applicable landing gear components that follow, if cleaning solutions or a direct spray of water was used to clean the components: (a) Main landing gear (Ref.TASK 12−20−32−640−802). (b) Nose landing gear (Ref.TASK 12−20−32−640−801). Subtask 32−00−00−941−002 B. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−00−00 page 701 32−00−00 Page 704 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL MAIN LANDING GEAR AND DOORS − DESCRIPTION AND OPERATION 1. 2. 3. General A. During landing and taxiing, the aircraft is supported by the main landing gear (MLG). The MLG doors make a smooth surface on the aircraft when the MLG are retracted. The MLG and the MLG doors have the components that follow: ± Two MLG assemblies (32−11−00) ± Two main door and mechanism systems (32−12−00). Description Refer to Figure 1. A. Main Landing Gear (1) Each MLG is a double−wheel, inboard−retracting, lever−suspension type. The MLG is mechanically locked in the extended position by the pawls in the MLG side stay actuator. It is held in the retracted position by a mechanical uplock assembly (32−30−00). The MLG retracts into two MLG wheel bins that are located in the main wheel well. B. Main Door and Mechanism System (1) Each main door and mechanism system is attached through the linkage to the main landing gear and is hinged to the wing structure. The main door operates mechanically when the MLG is retracted or extended. Operation A. Each MLG uses the MLG side stay actuator of the extension/retraction system to extend and retract (32−30−00) the gear. The main door is mechanically attached to the MLG. It opens or closes at the same time that the MLG extends or retracts. Master EFFECTIVITY: See Pageblock 32−10−00 page 1 32−10−00 Page 1 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL MAIN DOOR AND MECHANISM SYSTEM MAIN LANDING GEAR ram3210000_001(1).dc, mb/pb, 01/12/93 FWD Main Landing Gear and Doors Figure 1 Master EFFECTIVITY: See Pageblock 32−10−00 page 1 32−10−00 Page 2 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL MAIN LANDING GEAR AND DOORS − INSPECTION/CHECK 1. General A. The maintenance procedures that follow are for the visual inspection and the detailed inspection of the main landing gear assemblies and doors. TASK 32−10−00−210−801 Visual Inspection of the Main Landing Gear and Door 1. Procedure Subtask 32−10−00−210−001 Refer to Figure 601. A. Do an inspection of each main landing gear and door for the items that follow: ± The downlock assist−actuator selector−valve for condition and leakage ± The relief valve for condition and leakage ± The uplock assembly for condition, leakage, and safety of installation ± The gear main fitting for condition and corrosion ± The wheel bin and brushes for condition, cracks, and safety of installation ± The door and brushes for condition ± The door connecting rods and operating mechanism for condition, and safety of installation ± The door roller for condition and safety of installation ± The door hinge for wear and condition ± The applicable hydraulic lines and fittings for condition and leakage. ± The four brake quick disconnect couplings for condition and safety of installation. Master EFFECTIVITY: See Pageblock 32−10−00 page 601 601 32−10−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 4 2 1 11 3 10 9 5 1. Downlock assist actuator selector valve. 2. Downlock assist actuator relief valve. 3. Downlock assist actuator 4. Uplock. 5. Gear main fitting. 6. Trailing arm. 7. Door and brushes. 8. Door connecting rod and operating mechanism. 9. Shock absorber. 10. Door hinge. 11. Hydraulic line and fitting (typical). 12. Quick disconnect (four locations). 7 8 6 12 FW D D TB OU ram3210006_001.dg, mb/gw, 24/10/02 LEGEND Main Landing Gear and Door − Inspection/Check Figure 601 Master EFFECTIVITY: See Pageblock 32−10−00 page 601 32−10−00 Page 602 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−10−00−220−801 Detailed Inspection of the Main Landing Gear and Doors 1. Job Set−Up Information Subtask 32−10−00−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Light Subtask 32−10−00−946−002 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 53−83−01−000−801 TASK 53−83−01−400−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Removal of the MLG Wheel Bins Installation of the MLG Wheel Bins 2. Job Set−up Subtask 32−10−00−947−001 A. Remove the MLG wheel bins (Ref. TASK 53−83−01−000−801). Subtask 32−10−00−941−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: B. 3. Procedure Subtask 32−10−00−220−001 Refer to Figure 602 A. Inspect each door and main landing gear component for signs of fluid leakage, general condition, and safety of installation. (1) Do the detailed inspection of the landing gear components that follow: ± The MLG side stay actuator ± The MLG uplock assemblies ± The MLG selector valve ± The priority valve Master EFFECTIVITY: See Pageblock 32−10−00 page 601 603 32−10−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL ± The runaround and bypass valve ± The downlock assist actuator ± All hydraulic lines and hoses. 4. Close Out Subtask 32−10−00−410−001 A. Install the MLG wheel bins (Ref. TASK 53−83−01−400−801). Subtask 32−10−00−943−002 B. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−10−00 page 601 604 32−10−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL LEGEND 6. Door mechanism and connecting rods. 7. Hydraulic lines (typical). 1. Actuator. 2. Selector valve. 3. Uplock. 4. Brushes. 5. Door. 7 1 5 3 4 4 2 ram3210006_005.dg, rm, 01/12/04 6 Main Landing Gear (MLG) Components and Door − Inspection / Check Figure 602 (Sheet 1 of 2) Master EFFECTIVITY: See Pageblock 32−10−00 page 601 32−10−00 Page 605 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL 7 1 5 4 6 4 9 3 7. Hydraulic lines. 1. Actuator. (typical). 3. Uplock. 4. Brushes. 8. Priority valve. 5. Door. 9. Bypass valve. 6. Door mechanism and connecting rods. ram3210006_006.dg, rm, 01/12/04 LEGEND 8 Main Landing Gear (MLG) Components and Door − Inspection / Check Figure 602 (Sheet 2 of 2) Master EFFECTIVITY: See Pageblock 32−10−00 page 601 32−10−00 Page 606 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL TASK 32−10−00−220−802 Detailed Inspection of the Main Landing Gear (MLG) Components 1. Reason for the Job Refer to MRB 32−00−00−19. 2. Job Set−Up Information Subtask 32−10−00−943−003 A. Tools and Equipment REFERENCE None specified DESIGNATION Light Subtask 32−10−00−946−003 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 53−83−01−000−801 TASK 53−83−01−400−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Removal of the MLG Wheel Bins Installation of the MLG Wheel Bins 3. Job Set−up Subtask 32−10−00−947−002 A. Remove the MLG wheel bins (Ref. TASK 53−83−01−000−801). Subtask 32−10−00−941−002 WARNING: B. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). 4. Procedure Subtask 32−10−00−220−002 Refer to Figure 603 and Figure 604. A. Do a detailed inpsection of the left and right MLG components that follow for signs of fluid leakage, condition, and safety of installation. ± The MLG side stay actuator ± The MLG uplock assemblies ± The MLG selector valve Master EFFECTIVITY: See Pageblock 32−10−00 page 601 607 32−10−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL ± The priority valve ± The runaround and bypass valve ± The downlock assist actuator ± All hydraulic lines and hoses. 5. Close Out Subtask 32−10−00−410−002 A. Install the MLG wheel bins (Ref. TASK 53−83−01−400−801). Subtask 32−10−00−943−004 B. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−10−00 page 601 608 32−10−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Actuator. 2. Selector valve. 3. Uplock. 4. Brushes. 5. Door. 6. Door mechanism and connecting rods. 7. Hydraulic lines (typical). 7 1 5 3 4 4 2 ram3210006_003.dg, rm, 25/11/04 6 Left MLG Components − Detailed Inspection Figure 603 Master EFFECTIVITY: See Pageblock 32−10−00 page 601 32−10−00 Page 609 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL 8 1 6 5 7 5 3 LEGEND 1. Main landing gear actuator. 2. Priority valve. 3. Bypass valve. 4. Uplock. 5. Brushes. 6. Door. 7. Door mechanism and connecting rods. 8. Hydraulic lines. (typical). 2 ram3210006_004.dg, rm, 25/11/04 4 Right MLG Components − Detailed Inspection Figure 604 Master EFFECTIVITY: See Pageblock 32−10−00 page 601 32−10−00 Page 610 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL TASK 32−10−00−220−803 Detailed Inspection of the Main Landing Gear (MLG) Doors 1. Reason for the Job Refer to MRB 32−00−00−20. 2. Job Set−Up Information Subtask 32−10−00−943−005 A. Tools and Equipment REFERENCE None specified DESIGNATION Light Subtask 32−10−00−946−004 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins 3. Job Set−up Subtask 32−10−00−941−003 WARNING: A. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). 4. Procedure Subtask 32−10−00−220−003 Refer to Figure 605 A. Do a detailed inspection of the left MLG door for condition and safety of installation. B. Do a detailed inspection of the right MLG door for condition and safety of installation. 5. Close Out Subtask 32−10−00−943−006 A. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−10−00 page 601 32−10−00 Page 611 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL B 1 A 2 A LEGEND B ram3210006_002.dg, lr, 28/09/04 1. Left MLG door (732). 2. Right MLG door (742). MLG Door − Detailed Inspection Figure 605 Master EFFECTIVITY: See Pageblock 32−10−00 page 601 32−10−00 Page 612 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL MAIN LANDING GEAR (MLG) SYSTEM − DESCRIPTION AND OPERATION 1. 2. General A. The main landing gear (MLG) system has two MLGs. Each MLG is a double−wheel, inboard−retracting, lever−suspension type. The MLG system is mechanically locked in the extended position by the MLG side stay actuator and is held in the retracted position by a mechanical uplock assembly (32−30−00). The MLG system retracts into the main wheel well. Each MLG system has the components that follow: ± One main fitting assembly ± One MLG shock strut ± One trailing arm ± One MLG axle ± Two swivel coupling assemblies. Component Details Refer to Figure 1. A. Main Fitting Assembly (1) The main fitting assembly is a hand−forged and machined−steel hollow cylinder with a crossbeam at its top and an integral fork at its lower end. The hollow crossbeam has a pintle pin and pintle nut that attach the main gear to the center wing fuselage. (2) The main fitting assembly has an integral lug fitted with a spherical bearing which is used to attach the shock strut. The integral lug is located below the crossbeam, on the rear of the main fitting assembly. (3) The main fitting assembly has an integral socket with a pin installed in it. The pin is used to attach the MLG side stay actuator (32−32−00). The pin is installed along the vertical axis of the main fitting assembly. Below this pin is installed an uplock bracket and pin assembly. The uplock bracket and pin assembly is used to keep the MLG in the uplocked position. (4) The main fitting assembly has a stud which is used to attach the MLG door assembly. The stud is installed adjacent to the uplock bracket and pin assembly. (5) The main fitting assembly has a bracket which is used for the installation of the weight−on−wheels (WOW) proximity switch (32−61−00). The main fitting assembly has attachment provisions for hydraulic lines and electrical harnesses. (6) The integral fork of the main fitting assembly is made of two lugs which are bored and have bushings. The two lugs are used for the installation of the trailing arm and the hydraulic swivel joints. B. MLG Shock Strut (1) The shock strut is of a mixed gas/oil type. The shock strut has a cylinder subassembly and a piston subassembly. The annular space made by the difference between the internal and external diameters of the cylinder and piston makes the recoil damping chamber. The recoil damping is done hydraulically. (2) The head of the cylinder subassembly has a clevis at the top. The clevis has two lugs which are bored and have bushings. The cylinder is made of steel. The gas Master EFFECTIVITY: See Pageblock 32−11−00 page 1 32−11−00 Page 1 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL C. D. charge valve is installed on this end of the cylinder. A support tube is attached through the filler tube with the cylinder and has a fixed orifice on its free end. The support tube has transfer holes which let oil go through during the compression. (3) The piston subassembly has a steel piston with a chromed, external, dynamic diameter. The piston end has a lug fitted with a lubricated, self−aligning bearing, and has the oil charge valve. A metering pin is installed to the axis of the piston subassembly and goes through a fixed orifice. When the piston is compressed into the cylinder, the annular gap between the fixed orifice and the metering pin is slowly adjusted. This controls the flow of hydraulic fluid from the piston into the cylinder and keeps a controlled damping rate. (4) The top end of the piston has a bearing and a rebound ring. The bearing lets hydraulic fluid go to and from the rebound chamber during the compression or extension. The rebound ring lets the hydraulic fluid flow. This action makes the necessary recoil damping force. (5) The lower bearing is installed in the cylinder. It is teflon lined and holds the static, dynamic, and spare seals. The dynamic seal is protected by a scraper installed in the locking collar. Trailing Arm (1) The trailing arm is a cylindrical steel member with a hollow crossbeam attached at each end. The cylindrical steel member is sealed at its top with a cap. This cap keeps dirt out. Two integral bushed lugs which are located on the rear and top side of the cylinder are used to attach one end of the shock strut.The front crossbeam is attached to the lower main fitting assembly with a hinge pin. (2) The front crossbeam has two bushings which are used to attach the main fitting assembly. A transverse bolt attaches the crossbeam to the main fitting assembly. The hinge pin has at its ends the WOW targets. The front crossbeam has a sealing cap which does not let dirt in and two vent/drainage holes. The rear crossbeam holds the axle. Attached to each side of the rear crossbeam is a flange that attaches the brake assembly (32−43−00). (3) The rear crossbeam holds the axle which is attached with a transverse bolt. On each of its sides there is a mounting flange which is used to attach the brake units. Each mounting flange has five bushed holes, and a melting plug which is used during a brake overheat situation. The melting plug is in contact with the brake torque tube, it melts and leaves a hole in the mounting flange when the brake unit has an overheat condition. The mounting flange is also used as a brake torque transfer−point. The rear crossbeam holds the jacking pad which is attached with two bolts. MLG Axle (1) The MLG axle is hollow and is installed in the rear crossbeam of the trailing arm. The axle is attached to the trailing arm with a transverse bolt. The wheels are retained on the axle by a collar, a lockwasher, and an axle nut which is double locked with two bolts. The wheel retention device also retains a wheel speed transducer fitted in each axle. The MLG axle has two holes in the center which are used to install the harnesses of the wheel speed transducers. Master EFFECTIVITY: See Pageblock 32−11−00 page 1 32−11−00 Page 2 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL E. 3. 4. Swivel Coupling Assembly (1) The swivel coupling assembly is installed between the main fitting assembly and the trailing arm. The swivel coupling assembly makes a flexible hydraulic−fluid connection which is used during the extension or retraction of the MLG. Operation A. The aircraft weight on the ground is supported and absorbed by the MLG system. During the extension, the uplock assemblies release the MLG. The MLG side stay actuator causes the MLG system to extend. When the MLG is extended, the shock strut is fully extended. B. During the landing and the taxiing, the shock strut is compressed and absorbs all the shocks. The shock strut is installed between the main fitting assembly and the trailing arm. The trailing arm moves up or down in proportion to the movement of the shock strut. The main fitting assembly moves only during the extension and retraction of the MLG. The main fitting assembly does not move when the MLG is downlocked. At all times, the swivel coupling assembly gives continuous hydraulic connection between the aircraft and the MLG. Component Location Index Refer to Figure 1. COMPONENT NAME Axle Main fitting assembly Shock strut Swivel coupling assembly Trailing arm QTY 2 2 2 2 2 Master EFFECTIVITY: See Pageblock 32−11−00 page 1 ACCESS/ZONE 731/741 731/741 731/741 731/741 731/741 REFERENCE 32−11−15 32−11−01 32−11−05 32−11−20 32−11−10 32−11−00 Page 3 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL PINTLE PIN A BEAM ASSEMBLY MLG SHOCK STRUT PIN FOR INSTALLATION OF THE MLG SIDE STAY ACTUATOR (REF 32−32−01) UPLOCK BRACKET AND PIN ASSEMBLY HYDRAULIC LINE ELECTRICAL HARNESSES SWIVEL JOINT MLG AXLE JACKING PAD A MAIN LANDING GEAR ram3211000_001.dg, sm, 16/10/01 TRAILING ARM MLG System Figure 1 Master EFFECTIVITY: See Pageblock 32−11−00 page 1 32−11−00 Page 4 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL MAIN LANDING GEAR (MLG) − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the main landing gear (MLG). TASK 32−11−00−000−801 Removal of the MLG 1. Job Set−Up Information Subtask 32−11−00−943−001 A. Tools and Equipment REFERENCE G601R321005−1 G601R321006−1 G601R321101−1 G601R321102−1 None specified DESIGNATION Extractor, MLG pintle pin Dolly, MLG and NLG removal/installation Wrench, MLG pintle pin nut Adapter, MLG pintle pin nut Container, hydraulic fluid resistant Subtask 32−11−00−946−001 B. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 12−00−06−863−802 TASK 12−00−06−863−804 TASK 27−54−00−866−801 TASK 29−00−00−910−801 TASK 32−11−20−000−801 TASK 32−12−00−800−801 TASK 32−12−10−000−801 TASK 32−12−15−000−801 TASK 32−41−01−000−801 TASK 32−43−26−000−801 TASK 32−44−01−000−801 TASK 32−61−20−000−801 TASK 53−83−01−000−801 DESIGNATION Put the Aircraft on Jacks Release Hydraulic Pressure − Systems No. 1 and No. 2 Release Hydraulic Pressure − System No. 3 Electrical Extension of the Flaps Hydraulic Safety Precautions Removal of the Upper Brake Swivel Assembly Disconnect the MLG Door for Maintenance Access Removal of the Push/Pull Rod Removal of the Bellcrank Assembly Removal of the Main Wheel/Tire Assembly Removal of the Brake Unit Removal of the Wheel Speed Transducer Removal of the MLG Electrical Harness Removal of the MLG Wheel Bin Master EFFECTIVITY: See Pageblock 32−11−00 page 401 401 32−11−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 2. Job Set−Up Subtask 32−11−00−866−001 A. Electrically extend the flaps to get access to the work area (Ref. TASK 27−54−00−866−801). Subtask 32−11−00−910−001 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: B. Subtask 32−11−00−863−001 C. D. Release the hydraulic pressure from system No. 2 (Ref. TASK 12−00−06−863−802). Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−11−00−865−001 E. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−1 CBP−1 CBP−1 CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−4 CB NO. A2 A5 F6 F7 G3 G4 G11 G14 A2 F9 G4 G15 P2 P3 B13 NAME HYD PUMP 3B HYD PUMP 2 LGC/D1 WOW 1 BRAKE TEMP MON ANTI SKID HYD SYST AC PUMP CONT 3B HYD SYST AC PUMP CONT 2 HYD PUMP 3A PROX SENS WOW 2 ANTI SKID HYD SYST AC PUMP CONT 3A LGC/D1 LGC/D2 WOW 1 + 2 LGC/D2 ZONE 221 221 221 221 221 221 221 221 222 222 222 222 222 222 222 Subtask 32−11−00−582−001 F. Put the aircraft on jacks (Ref. TASK 07−11−01−582−801). Master EFFECTIVITY: See Pageblock 32−11−00 page 401 32−11−00 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−11−00−010−001 G. For the applicable MLG, remove the components as follows: NOTE: The removal procedure for the left MLG is given. The removal procedure for the right MLG is similar. Differences are identified in parenthesis. (1) Disconnect the MLG doors from the MLG (Ref. TASK 32−12−00−800−801). (2) Remove the applicable wheel bin (Ref. TASK 53−83−01−000−801). (3) Remove the two main wheel/tire assemblies (Ref. TASK 32−41−01−000−801). (4) Remove the inboard and outboard brake units (Ref. TASK 32−43−26−000−801). (5) Remove the inboard and outboard wheel−speed transducers (Ref. TASK 32−44−01−000−801). (6) Release the pressure from the MLG shock strut. (7) Remove the upper brake swivel−assembly (Ref. TASK 32−11−20−000−801). (8) Remove the electrical harnesses (Ref. TASK 32−61−20−000−801). (9) If necessary remove the push/pull rod (Ref. TASK 32−12−10−000−801). (10) If necessary remove the bellcrank assembly (Ref. TASK 32−12−15−000−801). 3. Procedure Subtask 32−11−00−020−001 Refer to Figure 401. A. Remove the MLG as follows: (1) Disconnect the side stay actuator (28) from the MLG (29) as follows: (a) Remove and discard the cotter pin (1). (b) Remove the nut (2), the washers (3) and (4), and the bolt (5). (c) Remove the side stay nut (6). (d) Disconnect the side stay actuator (28) from the side stay pin (31). (2) Disconnect the downlock assist actuator (30) from the MLG (29) as follows: (a) Remove and discard the cotter pin (7). (b) Remove the nut (8), the washer (9), and the pin (10). (c) Disconnect the downlock assist actuator (30) from the MLG (29). (3) Put the dolly in position below the MLG (29). Adjust the dolly until it correctly holds the MLG. (4) Remove and discard the cotter pin (11). (5) Remove the nut (12), the washer (13), and the pin (14). (6) Remove the retaining ring (15). (7) Remove the pintle nut (16) with the pintle pin nut−wrench and adapter. (8) Remove and discard the cotter pin (17). (9) Remove the nut (18), the washers (19) and (20), the end caps (21) and (22), and the bolt (23). Master EFFECTIVITY: See Pageblock 32−11−00 page 401 403 32−11−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (10) (11) (12) (13) (14) Remove the cross pin (24) from the MLG (29). Use a suitable tool to remove the end cap (26) from the pintle pin (25). Remove the preformed packing (27) from the end cap (26). Hold the MLG (29) and remove the pintle pin (25) with the pintle pin extractor. Remove the MLG (29). Master EFFECTIVITY: See Pageblock 32−11−00 page 401 404 32−11−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 23 22 25 10 9 24 30 9 7 8 14 A 15 13 12 16 11 28 5 21 4 20 6 3 19 2 18 31 29 LEGEND 1. Cotter pin. 2. Nut. 3. Washer. 4. Washer. 5. Bolt. 6. Side stay nut. 7. Cotter pin. 8. Nut. 9. Washer. 10. Pin. 11. Cotter pin. 12. Nut. 13. Washer. 14. Pin. 15. Retaining ring. 16. Pintle nut. 17. Cotter pin. 18. Nut. 19. Washer. 20. Washer. 21. End cap. 22. End cap. 23. Bolt. 24. Cross pin. 25. Pintle pin. 26. End cap. 27. Preformed packing. 28. Side stay actuator. 29. Main landing gear (MLG). 30. Downlock assist actuator. 31. Side stay pin. 1 25 (REF) 27 26 AUXILIARY REAR SPAR (REF) A ram3211004_001.dg, kms/rm, 04/10/01 17 Main Landing Gear − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−11−00 page 401 32−11−00 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−11−00−400−801 Installation of the MLG 1. Job Set−Up Information Subtask 32−11−00−943−002 A. Tools and Equipment REFERENCE G601R321006−1 G601R321101−1 G601R321102−1 None specified None specified None specified DESIGNATION Dolly, MLG and NLG removal/installation Wrench, MLG pintle pin nut Adapter, MLG pintle pin nut Torque wrench, torque range 0 to 50 pound−inches (0 to 5.65 N·m) Torque wrench, torque range 0 to 150 pound−inches (0 to 16.95 N·m) Torque wrench, torque range 0 to 1500 pound−inches (0 to 169.5 N·m) Subtask 32−11−00−944−001 B. Consumable Materials REFERENCE 06−002 04−005 DESIGNATION Petrolatum Grease Subtask 32−11−00−945−001 C. Parts REF 1 2 3 4 5 6 7 8 9 10 11 12 13 14 NAME OF PART Cotter pin Nut Washer Washer Bolt Side stay nut Cotter pin Nut Washer Pin Cotter pin Nut Washer Pin Master EFFECTIVITY: See Pageblock 32−11−00 page 401 QTY 1 1 1 1 1 1 1 1 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−32−01−01−060 IPC 32−32−01−01−070 IPC 32−32−01−01−055 IPC 32−32−01−01−055 IPC 32−32−01−01−045 IPC 32−32−01−01−050 IPC 32−34−05−01−075 IPC 32−34−05−01−070 IPC 32−34−05−01−065 IPC 32−34−05−01−060 IPC 32−11−00−03−075 IPC 32−11−00−03−070 IPC 32−11−00−03−065 IPC 32−11−00−03−060 32−11−00 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REF 15 16 17 18 19 20 21 22 23 24 25 26 27 NAME OF PART Retaining ring Pintle nut Cotter pin Nut Washer Washer End cap End cap Bolt Cross pin Pintle pin End cap, Pintle pin Preformed Packing QTY 1 1 1 1 2 2 1 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−11−00−03−115 IPC 32−11−00−03−055 IPC 32−11−00−03−110 IPC 32−11−00−03−105 IPC 32−11−00−03−100 IPC 32−11−00−03−095 IPC 32−11−00−03−090 IPC 32−11−00−03−090 IPC 32−11−00−03−085 IPC 32−11−00−03−080 IPC 32−11−00−03−050 IPC 32−11−00−03−120 IPC 32−11−11−01−047 Subtask 32−11−00−946−002 D. Reference Information REFERENCE TASK 07−11−01−582−804 TASK 12−12−32−610−802 TASK 12−20−32−640−802 TASK 27−54−00−866−802 TASK 29−10−00−870−802 TASK 29−10−00−870−803 TASK 32−00−00−790−801 TASK 32−11−20−400−801 TASK 32−12−00−800−802 TASK 32−12−10−400−801 TASK 32−12−15−400−801 TASK 32−30−00−720−801 TASK 32−34−00−710−801 TASK 32−41−01−400−801 TASK 32−43−00−710−801 TASK 32−43−00−870−801 TASK 32−43−26−400−801 TASK 32−44−01−400−801 TASK 32−61−20−400−801 TASK 53−83−01−400−801 DESIGNATION Removal of the Aircraft from Jacks Servicing of the MLG Shock Strut With Jacks Lubrication of the Main Landing Gear Electrical Retraction of the Flaps Bleed Hydraulic System No. 2 Bleed Hydraulic System No. 3 External Leak Check of the Landing Gear Installation of the Upper Brake Swivel Assembly Connect the MLG Door after Maintenance Installation of the Push/Pull Rod Installation of the Bellcrank Assembly Functional Test of the Landing Gear Extension/ Retraction System Operational Test of the Landing Gear Manual−Release−System Installation of the Main Wheel/Tire Assembly Operational Test of the Brake System Bleeding of the Brakes Installation of the Brake Unit Installation of the Wheel Speed Transducer Installation of the MLG Electrical Harness Installation of the MLG Wheel Bin Master EFFECTIVITY: See Pageblock 32−11−00 page 401 407 32−11−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 2. Job Set−Up Refer to Figure 402. Subtask 32−11−00−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Subtask 32−11−00−220−003 B. C. Inspect the bushings (2), (3), and (6) in the MLG trunnion and the bushings (4) and (5) in the main fitting of the MLG for correct installation and for damage. Make sure that the check dimension for the MLG trunnion bushings (3) and (4) is correct. Subtask 32−11−00−640−003 D. E. Lightly lubricate the visible surfaces of the MLG trunnion bushings (2) and (3), the trunnion bushing (6), and also the bushings (4) and (5) in the main fitting of the MLG with 04−005 grease. Refer to Figure 401. Lightly lubricate the bore of the spherical bearing in the side stay actuator (28) and the sidestay pin (31) with 04−005 grease. 3. Procedure Subtask 32−11−00−420−001 Refer to Figure 401. A. Install the MLG as follows: NOTE: The installation procedure is applicable to the left MLG. The installation of the right MLG is the same. (1) With the dolly, put the MLG (29) in position between the attachment lugs of the MLG trunnion (that is located between the wing rear spar and the wing auxiliary rear spar). NOTE: Make sure that the rod of the downlock assist actuator (30) is correctly aligned between its related lugs on the MLG main fitting as the MLG (29) is moved into position. (2) Align the attachment holes in the main fitting of the MLG (29) with the attachment holes in the MLG trunnion. (3) Lightly lubricate the pintle pin (25) with 04−005 grease. (4) Install the pintle pin (25). (5) Lightly lubricate a serviceable preformed packing (27) with 06−002 petrolatum. (6) Install the preformed packing (27) on the end cap (26). (7) Install the end cap (26) in the pintle pin (25). Make sure that the attachment holes in the end cap (26), the pintle pin (25), and the MLG (29) are aligned correctly. (8) Install the cross pin (24) and the two end caps (21) and (22). (9) Install the bolt (23), the washers (20) and (19), and the nut (18). Master EFFECTIVITY: See Pageblock 32−11−00 page 401 32−11−00 Page 408 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL (10) Install the pintle pin nut (16) on the pintle pin (25) with the pintle pin nut−wrench and adapter. (11) Torque the pintle pin nut (16) to 20 pound−feet (27.12 N·m). (12) Continue to torque the pintle pin nut (16) to a maximum of 150 pound−feet (203.4 N·m) until the slot in the pintle pin nut (16) is aligned with the hole in the pintle pin (25). **ON A/C 7003−7067, 7069−7990, 8000−8017 Subtask 32−11−00−220−002 Refer to Figure 402. B. Do a check of the MLG gaps for correct MLG installation as follows: (1) At the forward lug of the MLG trunnion (approximately at the wing rear spar), measure the gap at the MLG trunnion bushings (2) and (3) as follows: (a) Measure the gap between the MLG trunnion bushing (2) and the pintle pin nut (1). (b) Measure the gap between the MLG trunnion bushing (3) and the bushing (4) in the forward end of the MLG main fitting. (c) Add the two dimensions together. Make sure that the total measurement of the gaps does not exceed a dimension of 0.012 to 0.028 inch (0.30 to 0.71 mm). (2) At the aft trunnion lug (approximately at the wing auxiliary rear spar), measure the gap between the trunnion bushing (6) and the bushing (5) in the aft end of the MLG main fitting. Make sure that the measured dimension of the gap is between 0.040 and 0.098 inch (1.02 and 2.49 mm). **ON A/C 8018−8064, 8066−8068 Subtask 32−11−00−220−004 Refer to Figure 402. C. Do a check of the MLG gaps for correct MLG installation as follows: (1) At the forward lug of the MLG trunnion (approximately at the wing rear spar), measure the gap at the MLG trunnion bushings (2) and (3) as follows: (a) Measure the gap between the MLG trunnion bushing (2) and the pintle pin nut (1). (b) Measure the gap between the MLG trunnion bushing (3) and the bushing (4) in the forward end of the MLG main fitting. (c) Add the two dimensions together. Make sure that the total measurement of the gaps does not exceed a dimension of 0.007 to 0.023 inch (0.18 to 0.58 mm). (2) At the aft trunnion lug (approximately at the wing auxiliary rear spar), measure the gap between the trunnion bushing (6) and the bushing (5) in the aft end of the MLG main fitting. Master EFFECTIVITY: See Pageblock 32−11−00 page 401 409 32−11−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL Make sure that the measured dimension of the gap is between 0.040 and 0.098 inch (1.02 and 2.49 mm). **ON A/C ALL Subtask 32−11−00−420−002 Refer to Figure 401. D. If the measured gaps are satisfactory, do the steps that follow to continue the installation of the MLG (29): (1) Install the retaining ring (15) for the swivel valve assembly on the pintle pin (25). (2) Install the pin (14), the washer (13), and the nut (12). (3) Safety the nut (12) with the cotter pin (11). (4) Safety the nut (18) with the cotter pin (17). (5) Connect the rod of the downlock assist actuator (30) to the MLG (29) as follows: (a) Attach the downlock assist actuator (30) to the MLG (29) with the pin (10), the washer (9), and the nut (8). NOTE: Make sure that the pin (10) is installed with its head is on the aft side of the attachment lug on the MLG (29). (b) Torque the nut (8) from 5 to 10 pound−inches (0.57 to 1.13 N·m) and loosen the nut to the nearest lock position. Make sure that the pin (10) turns freely. (c) Safety the nut (8) with the cotter pin (7). (6) Connect the side stay actuator (28) to the MLG (29) as follows: (a) Attach the side stay actuator (28) to the side stay pin (31) with the side stay nut (6). (b) Torque the side stay nut (6) from 1100 to 1200 pound−inches (124.3 to 135.6 N·m). NOTE: If the slot in the side stay pin nut (6) does not align with the hole in the side stay pin (31) in the required torque range, back off the side stay pin nut (6) to the nearest hole. (c) Install the bolt (5), the washers (4) and (3), and the nut (2). (d) Torque the nut (2) from 30 to 35 pound−inches (3.39 to 3.96 N·m). (e) Safety the nut (2) with the cotter pin (1). 4. Close Out Subtask 32−11−00−410−001 A. For the applicable MLG (29), install the components that follow: (1) Connect the MLG door to the MLG (Ref. TASK 32−12−00−800−802). (2) If removed install the push/pull rod (Ref. TASK 32−12−10−400−801). (3) If removed install the bellcrank assembly (Ref. TASK 32−12−15−400−801). (4) The electrical harnesses (Ref. TASK 32−61−20−400−801). Master EFFECTIVITY: See Pageblock 32−11−00 page 401 410 32−11−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL B. (5) The inboard and outboard wheel−speed transducers (Ref. TASK 32−44−01−400−801). (6) The upper brake swivel−assembly (Ref. TASK 32−11−20−400−801). (7) The inboard and outboard brake units (Ref. TASK 32−43−26−400−801). (8) The two main wheel/tire assemblies (Ref. TASK 32−41−01−400−801). (9) The applicable wheel bin (Ref. TASK 53−83−01−400−801). Connect the MLG doors to the MLG. Subtask 32−11−00−640−002 C. Lubricate the MLG (Ref. TASK 12−20−32−640−802). Subtask 32−11−00−866−002 D. Electrically retract the flaps (Ref. TASK 27−54−00−866−802). Subtask 32−11−00−610−001 E. Pressurize the MLG shock strut (Ref. TASK 12−12−32−610−802). Subtask 32−11−00−865−002 F. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−1 CBP−1 CBP−1 CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−4 CB NO. A2 A5 F6 F7 G3 G4 G11 G14 A2 F9 G4 G15 P2 P3 B13 NAME HYD PUMP 3B HYD PUMP 2 LGC/D1 WOW 1 BRAKE TEMP MON ANTI SKID HYD SYST AC PUMP CONT 3B HYD SYST AC PUMP CONT 2 HYD PUMP 3A PROX SENS WOW 2 ANTI SKID HYD SYST AC PUMP CONT 3A LGC/D1 LGC/D2 WOW 1 + 2 LGC/D2 ZONE 221 221 221 221 221 221 221 221 222 222 222 222 222 222 222 Subtask 32−11−00−870−001 G. H. I. Bleed hydraulic system No. 2 (Ref. TASK 29−10−00−870−802). Bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Bleed the inboard and outboard brakes (Ref. TASK 32−43−00−870−801). Master EFFECTIVITY: See Pageblock 32−11−00 page 401 411 32−11−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−11−00−720−001 J. Do a functional test of the extension and retraction system (Ref. TASK 32−30−00−720−801). Subtask 32−11−00−710−001 K. L. Do an operational test of the manual release system (Ref. TASK 32−34−00−710−801). Do an operational test of the brake system (Ref. TASK 32−43−00−710−801). Subtask 32−11−00−210−001 M. Examine the work area for hydraulic leaks (Ref. TASK 32−00−00−790−801). Subtask 32−11−00−586−001 N. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−11−00−941−002 O. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−11−00 page 401 412 32−11−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL A NOTE 1. Left side shown, right side opposite. LEGEND 1. Pintle pin nut. END CAP 1 FW D MLG MAIN FITTING A ram3211004_002.dg, pm/lr, 30/11/04 BD T OU Main Landing Gear − Main Fitting−to−Trunnion Gaps Figure 402 (Sheet 1 of 2) Master EFFECTIVITY: See Pageblock 32−11−00 page 401 32−11−00 Page 413 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL NOTES 2 Total gap after assembly Pre−Mod 0.012 to 0.028 in. (0.30 to 0.71 mm) Post−Mod 0.007 to 0.023 in. (0.18 to 0.58 mm). 3 Messier Dowty check dimension 1.882 to 1.889 in. (47.80 to 47.98 mm) (reference only). 4 3 4 2 2 MLG trunnion bushings check dimension Pre−Mod 1.861 to 1.870 in. (47.27 to 47.50 mm) Post−Mod 1.866 to 1.875 in. (47.40 to 47.62 mm). MLG MAIN FITTING (REF) 1 LEGEND 1. Pintle pin nut. 2. MLG trunnion bushing. 3. MLG trunnion bushing. 4. Bushing. 5. Bushing. 6. Trunnion bushing. 0.040 TO 0.098 in. (1.02 TO 2.49 mm) AFTER ASSEMBLY 4 PINTLE PIN 2 3 5 6 MLG MAIN FITTING END CAP ram3211004_003.dg, rm/lr, 30/11/04 PINTLE PIN Main Landing Gear − Main Fitting−to−Trunnion Gaps Figure 402 (Sheet 2 of 2) Master EFFECTIVITY: See Pageblock 32−11−00 page 401 32−11−00 Page 414 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL SHOCK STRUT, MAIN LANDING GEAR (MLG) − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the main landing gear (MLG) shock strut. Each shock strut is attached between the main fitting and the MLG trailing arm. TASK 32−11−05−000−801 Removal of the MLG Shock Strut 1. Job Set−Up Information Subtask 32−11−05−943−004 A. Tools and Equipment REFERENCE 02−7813−8100 DESIGNATION Jack − 15 ton, MLG axle Subtask 32−11−05−946−001 B. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 12−12−32−610−802 TASK 29−00−00−910−801 TASK 32−41−01−000−801 DESIGNATION Put the Aircraft on Jacks Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − System No. 3 Servicing (Oil and Nitrogen) of the MLG Shock Strut − Aircraft on Jacks Hydraulic Safety Precautions Removal of the Main Wheel/Tire Assembly 2. Job Set−Up Subtask 32−11−05−865−001 A. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 ZONE 221 221 222 222 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−11−05−941−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Install the applicable warning tags on the landing−gear control lever. WARNING: B. C. Subtask 32−11−05−910−001 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: D. Subtask 32−11−05−863−001 E. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−11−05−582−001 F. Put the aircraft on jacks (Ref. TASK 07−11−01−582−801). Make sure that the MLG shock strut is fully extended and that the main wheel/tire−assemblies do not touch the ground and that approximately 5 inches (127 mm) of the chrome surface of the shock strut piston can be seen. Subtask 32−11−05−010−001 G. Remove the inboard main wheel/tire−assembly (Ref. TASK 32−41−01−000−801). Subtask 32−11−05−863−002 H. If the MLG shock strut is unserviceable and is to be replaced, release the nitrogen pressure from the MLG shock strut (Ref. TASK 12−12−32−610−802). NOTE: It will not be necessary to release the nitrogen pressure from the MLG shock strut if the MLG shock is to be removed for access to do maintenance on another component (or components) of the MLG. Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. Procedure **ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7063−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087, 7089−7090, 7093, 7095−7098, 7104, 7107, 7112−7114, 7118−7122, 7124, 7126, 7128, 7130, 7135−7136, 7144, 7158−7214 and ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7062, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088, 7091−7092, 7094, 7099−7103, 7105−7106, 7108−7111, 7115−7117, 7123, 7125, 7127, 7129, 7131−7134, 7137−7143, 7145−7157 Post SB601R−32−065 Subtask 32−11−05−020−001 Refer to Figure 401. A. Disconnect the left or the right MLG shock strut [Refer to Figure 401 (Sheet 1)] from the MLG trailing arm as follows: (1) At the bottom of the MLG shock strut piston, remove and discard the cotter pin (1) from the nut (2). (2) Remove the nut (2), the washer(s) (3), the recessed washer (4) from the greasing bolt (5). WARNING: DO NOT LIFT THE LANDING GEAR WITH THE AXLE JACK TOO MUCH. THE AIRCRAFT CAN BE LIFTED OFF OF THE MAIN JACKS WITH THE AXLE JACK. IF THE LANDING GEAR SHOCK STRUT IS PRESSURIZED, USE THE AXLE JACK TO SUPPORT THE LANDING GEAR ONLY. DAMAGE TO EQUIPMENT AND INJURIES TO PERSONS CAN OCCUR. (3) Put an axle jack in position on the jacking pad for the MLG to support the trailing arm. Lift the trailing arm a small amount with the axle jack until the weight of the trailing arm is supported by the axle jack and the pin (7) can move freely. (4) Support the MLG shock strut by hand and use a soft face drift to remove the pin (7) and the spacer (8). Do not remove the greasing bolt (5) from the pin (7) unless it is necessary for other maintenance. (5) If it is necessary to remove the greasing bolt (5) from the pin (7), do the steps that follow: (a) Remove the greasing bolt (5) from the pin (7). (b) Remove and discard the six preformed packings (6) from the greasing bolt (5). (6) Move the piston spherical bearing at the bottom of the MLG shock strut from between the two lugs on the trailing arm, and remove the anti−rotation washer (9) from the piston spherical bearing. NOTE: The anti−rotation washer (9) is installed on the outboard side of the piston spherical bearing for the left MLG and the inboard side for the right MLG. (7) Remove the spacer (8) from the pin (7). B. Disconnect the MLG shock strut [Refer to Figure 401 (Sheet 2)] from the MLG main fitting on the left side of the aircraft as follows: NOTE: The steps that follow are applicable to the MLG on the left side of the aircraft only. Master EFFECTIVITY: See Pageblock 32−11−05 page 401 403 32−11−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL C. (1) At the top of the MLG shock strut, remove and discard the cotter pin (1) from the nut (2). (2) Remove the nut (2) and the washer(s) (3) from the greasing bolt (5). (3) Remove the recessed washer (10), the outer shims (12), and the inner shims (13) from the greasing bolt (5). (4) Hold the MLG shock strut in position and use a soft face drift to carefully remove the pin (7) with the cap−end (14) from the top of the MLG shock strut and the MLG main fitting. Do not remove the greasing bolt (5) from the pin (7) unless it is necessary for other maintenance. (5) Move the MLG shock strut away from the MLG main fitting and remove the anti−rotation washer (16) from the outboard side of the spherical bearing in the MLG main bearing. (6) If it is necessary to remove the greasing bolt (5) from the pin (7), do the steps that follow: (a) Remove the greasing bolt (5) from the pin (7). (b) Remove and discard the six preformed packings (6) from the greasing bolt (5). (7) Remove the cap−end (14) from the pin (7). Disconnect the MLG shock strut [Refer to Figure 401 (Sheet 3)] from the MLG main fitting on the right side of the aircraft as follows: NOTE: The steps that follow are applicable to the MLG on the left side of the aircraft only. (1) At the top of the MLG shock strut, remove and discard the cotter pin (1) from the nut (2). (2) Remove the nut (2) and the washer(s) (3) from the greasing bolt (5). (3) Remove the recessed washer (11), the outer shims (12), and the inner shims (13) from the greasing bolt (5). (4) Hold the MLG shock strut in position and use a soft face drift to carefully remove the pin (7) with the washer (15) from the top of the MLG shock strut and the MLG main fitting. Do not remove the greasing bolt (5) from the pin (7) unless it is necessary for other maintenance. (5) Move the MLG shock strut away from the MLG main fitting and remove the anti−rotation washer (16) from the inboard side of the spherical bearing in the MLG main fitting. (6) If it is necessary to remove the greasing bolt (5) from the pin (7), do the steps that follow: (a) Remove the greasing bolt (5) from the pin (7). (b) Remove and discard the six preformed packings (6) from the greasing bolt (5). (7) Remove the washer (15) from the pin (7). Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7003, 7020, 7053, 7057, 7081, 7084, 7126, 7140, 7144, 7152, 7164, 7166, 7170, 7182−7184, 7197 and ON A/C 7004−7019, 7021−7052, 7054−7056, 7058−7067, 7069−7080, 7082−7083, 7085−7125, 7127−7139, 7141−7143, 7145−7151, 7153−7163, 7165, 7167−7169, 7171−7181, 7185−7196, 7198−7214 Post SB601R−32−072 Subtask 32−11−05−020−002 Refer to Figure 402. D. Disconnect the left or the right MLG shock strut [Refer to Figure 402 (Sheet 1)] from the MLG trailing arm as follows: (1) At the bottom of the MLG shock strut piston, remove and discard the cotter pin (1) from the nut (2). (2) Remove the nut (2), the washer(s) (3), the recessed washer (4) from the greasing bolt (5). WARNING: DO NOT LIFT THE LANDING GEAR WITH THE AXLE JACK TOO MUCH. THE AIRCRAFT CAN BE LIFTED OFF OF THE MAIN JACKS WITH THE AXLE JACK. IF THE LANDING GEAR SHOCK STRUT IS PRESSURIZED, USE THE AXLE JACK TO SUPPORT THE LANDING GEAR ONLY. DAMAGE TO EQUIPMENT AND INJURIES TO PERSONS CAN OCCUR. (3) Put an axle jack in position on the jacking pad for the MLG to support the trailing arm. Lift the trailing arm a small amount with the axle jack until the weight of the trailing arm is supported by the axle jack and the pin (7) can move freely. (4) Support the MLG shock strut by hand and use a soft face drift to remove the pin (7) and the washer (8). Do not remove the greasing bolt (5) from the pin (7) unless it is necessary for other maintenance. (5) If it is necessary to remove the greasing bolt (5) from the pin (7), do the steps that follow: (a) Remove the greasing bolt (5) from the pin (7). (b) Remove and discard the six preformed packings (6) from the greasing bolt (5). (6) Move the piston spherical bearing at the bottom of the MLG shock strut from between the two lugs on the trailing arm, and remove the anti−rotation washer (9) from the piston spherical bearing. NOTE: The anti−rotation washer (9) is installed on the outboard side of the piston spherical bearing for the left MLG and the inboard side for the right MLG. (7) Remove the spacer (8) from the pin (7). E. Disconnect the left or the right MLG shock strut [Refer to Figure 402 (Sheet 2 and Sheet 3)] from the MLG main fitting as follows: (1) At the top of the MLG shock strut, remove and discard the cotter pin (1) from the nut (2). (2) Remove the nut (2) and the washer(s) (3) from the greasing bolt (5). (3) Remove the recessed washer (10), the outer shims (11), and the inner shims (12) from the greasing bolt (5). (4) Hold the MLG shock strut in position and use a soft face drift to carefully remove the pin (7) with the cap−end (13) from the top of the MLG shock strut and the MLG main fitting. Do not remove the greasing bolt (5) from the pin (7) unless it is Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL necessary for other maintenance. (5) Move the MLG shock strut away from the MLG main fitting and remove the anti−rotation washer (14) from the spherical bearing in the MLG main fitting. NOTE: The anti−rotation washer (14) is installed on the outboard side of the MLG main fitting spherical bearing for the left MLG and the inboard side for the right MLG. (6) If it is necessary to remove the greasing bolt (5) from the pin (7), do the steps that follow: (a) Remove the greasing pin (5) from the pin (7). (b) Remove and discard the six preformed packings (6) from the greasing pin (5). (7) Remove the cap−end (13) from the pin (7). **ON A/C 7215−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7214 Post VSBM−DT−17002−32−16 Subtask 32−11−05−020−003 Refer to Figure 403. F. Disconnect the left or the right MLG shock strut [Refer to Figure 403 (Sheet 1)] from the MLG trailing arm as follows: (1) At the bottom of the MLG shock strut piston, remove and discard the cotter pin (1) from the nut (2). (2) Remove the nut (2) and also the washer(s) (3) and (4) from the greasing bolt (5). WARNING: DO NOT LIFT THE LANDING GEAR WITH THE AXLE JACK TOO MUCH. THE AIRCRAFT CAN BE LIFTED OFF OF THE MAIN JACKS WITH THE AXLE JACK. IF THE LANDING GEAR SHOCK STRUT IS PRESSURIZED, USE THE AXLE JACK TO SUPPORT THE LANDING GEAR ONLY. DAMAGE TO EQUIPMENT AND INJURIES TO PERSONS CAN OCCUR. (3) Put an axle jack in position on the jacking pad for the MLG to support the trailing arm. Lift the trailing arm a small amount with the axle jack until the weight of the trailing arm is supported by the axle jack and the pin (7) can move freely. (4) Support the MLG shock strut by hand and use a soft face drift to remove the pin (7). Do not remove the greasing bolt (5) from the pin (7) unless it is necessary for other maintenance. (5) If it is necessary to remove the greasing bolt (5) from the pin (7), do the steps that follow: (a) Remove the greasing bolt (5) from the pin (7). (b) Remove and discard the six preformed packings (6) from the greasing bolt (5). (6) Move the piston spherical bearing at the bottom of the MLG shock strut from between the two lugs on the trailing arm, and remove the anti−rotation washer (8) from the piston spherical bearing. NOTE: The anti−rotation washer (8) is installed on the outboard side of the piston spherical bearing for the left MLG and the inboard side for the right MLG. Master EFFECTIVITY: See Pageblock 32−11−05 page 401 406 32−11−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL G. Disconnect the left or the right MLG shock strut [Refer to Figure 403 (Sheet 2 and Sheet 3)] from the MLG main fitting as follows: (1) At the top of the MLG shock strut, remove and discard the cotter pin (1) from the nut (2). (2) Remove the nut (2) and also the washer(s) (3) and (4) from the greasing bolt (5). (3) If it is necessary to remove the greasing bolt (5) from the pin (7), do the steps that follow: (a) Remove the greasing pin (5) from the pin (7). (b) Remove and discard the six preformed packings (6) from the greasing pin (5). (4) Hold the MLG shock strut in position and use a soft face drift to carefully remove the pin (7) from the top of the MLG shock strut and the MLG main fitting. Do not remove the greasing bolt (5) from the pin (7) unless it is necessary for other maintenance. (5) Move the MLG shock strut away from the MLG main fitting and remove the anti−rotation washer (9) from the spherical bearing in the MLG main fitting. NOTE: The anti−rotation washer (9) is installed on the outboard side of the piston spherical bearing for the left MLG and the inboard side for the right MLG. Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND A F 1. Cotter pin. 2. Nut. 3. Washer. 4. Recessed washer. 5. Greasing bolt. 6. Preformed packing. 7. Pin. 8. Spacer. 9. Anti−rotation washer. SHOCK STRUT PISTON (REF) C B SPHERICAL BEARING (REF) NOTES A Right MLG is shown Left MLG is opposite. Post S/B 601R−32−065. Pre S/B M−DT 17002−32−16. GREASE FITTING (REF) 1 Item 9 is installed on the outboard side for the left MLG. 1 2 1 9 3 FW D 4 D 5 8 7 TRAILING ARM (REF) B 6 VIEW LOOKING OUTBOARD AND FORWARD ram3211054_001(4).dc, gg/kms, 26/01/99 INB MLG Shock Strut − Removal/Installation Figure 401 (Sheet 1 of 3) Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 408 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Cotter pin. 2. Nut. 3. Washer. 5. Greasing bolt. 6. Preformed packing. 7. Pin. 10. Recessed washer. 12. Outer shim. 13. Inner shim. 14. Cap−end. 16. Anti−rotation washer. 0.010 in. (0.25 mm) minimum gap. 0.015 in. (0.38 mm) maximum gap. D E VIEW LOOKING FORWARD 5 LH MLG MAIN FITTING (REF) SPHERICAL BEARING (REF) C 16 NOTE 6 LH MLG is shown. Post S/B 601R−32−065. Pre S/B M−DT 17002−32−16. 13 14 10 FW D E 12 LH SHOCK STRUT CYLINDER (REF) 3 2 D D INB ram3211054_002(1).dc, gg/kms, 26/01/99 1 7 MLG Shock Strut − Removal/Installation Figure 401 (Sheet 2 of 3) Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 409 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 0.010 in. (0.25 mm) minimum gap. 0.015 in. (0.38 mm) maximum gap. LEGEND 1. Cotter pin. 2. Nut. 3. Washer. 5. Greasing bolt. 6. Preformed packing. 7. Pin. 11. Recessed washer. 12. Outer shim. 13. Inner shim. 15. Washer. 16. Anti−rotation washer. G H VIEW LOOKING FORWARD RH MLG MAIN FITTING SPHERICAL BEARING (REF) F 1 2 11 16 NOTE RH MLG is shown. Post S/B 601R−32−065. Pre S/B A601R−32−072. Pre S/B M−DT 17002−32−16. 3 15 12 7 13 FW D 5 D H RH SHOCK STRUT CYLINDER (REF) 6 G ram3211054_003(1).dc, rm/kms, 26/01/99 INB MLG Shock Strut − Removal/Installation Figure 401 (Sheet 3 of 3) Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 410 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND A F 1. Cotter pin. 2. Nut. 3. Washer. 4. Recessed washer. 5. Greasing bolt. 6. Preformed packing. 7. Pin. 8. Spacer. 9. Anti−rotation washer. SHOCK STRUT PISTON (REF) C B SPHERICAL BEARING (REF) NOTES A Right MLG is shown Left MLG is opposite. Post S/B 601R−32−065. Pre S/B M−DT 17002−32−16. GREASE FITTING (REF) 1 Item 9 is installed on the outboard side for the left MLG. 1 2 1 9 3 FW D 4 D 5 8 7 TRAILING ARM (REF) B 6 VIEW LOOKING OUTBOARD AND FORWARD ram3211054_001(4).dc, gg/kms, 26/01/99 INB MLG Shock Strut − Removal/Installation Figure 402 (Sheet 1 of 3) Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 411 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Cotter pin. 2. Nut. 3. Washer. 5. Greasing bolt. 6. Preformed packing. 7. Pin. 10. Recessed washer. 11. Outer shim. 12. Inner shim. 13. Cap−end. 14. Anti−rotation washer. 0.010 in. (0.25 mm) minimum gap. 0.015 in. (0.38 mm) maximum gap. D E VIEW LOOKING FORWARD SPHERICAL BEARING (REF) C 5 LH MLG MAIN FITTING (REF) 14 NOTES LH MLG is shown. Post S/B 601R−32−065. Pre S/B M−DT 17002−32−16. 6 1 Anti−rotation stop removed on M17100−101/−103 shock strut Post S/B 12 A601R−32−072 only. 13 10 FW D INB D E 11 LH SHOCK STRUT CYLINDER (REF) 3 2 1 D ram3211054_004.dc, gg/kms, 26/01/99 1 7 MLG Shock Strut − Removal/Installation Figure 402 (Sheet 2 of 3) Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 412 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 0.010 in. (0.25 mm) minimum gap. 0.015 in. (0.38 mm) maximum gap. LEGEND 1. Cotter pin. 2. Nut. 3. Washer. 5. Greasing bolt. 6. Preformed packing. 7. Pin. 10. Recessed washer. 11. Outer shim. 12. Inner shim. 13. Cap−end. 14. Anti−rotation washer. G H VIEW LOOKING FORWARD RH MLG MAIN FITTING SPHERICAL BEARING (REF) F NOTES 1 2 10 14 RH MLG is shown. Post S/B A601R−32−072. Pre S/B M−DT 17002−32−16. 3 1 Anti−rotation stop removed on M17100−101/−103 shock strut only. 13 11 7 12 FW D D 5 H 6 RH SHOCK STRUT CYLINDER (REF) 1 G ram3211054_005.dc, rm/kms, 26/01/99 INB MLG Shock Strut − Removal/Installation Figure 402 (Sheet 3 of 3) Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 413 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND A F 1. Cotter pin. 2. Nut. 3. Washer. 4. Washer. 5. Greasing bolt. 6. Preformed packing. 7. Pin. 8. Anti−rotation washer. SHOCK STRUT PISTON (REF) C B SPHERICAL BEARING (REF) NOTES A Right MLG is shown Left MLG is opposite. Post S/B M−DT 17002−32−16. GREASE FITTING (REF) 1 Item 8 is installed on the outboard side for the left MLG. 1 2 1 8 3 FW D 4 D 5 7 TRAILING ARM (REF) B 6 VIEW LOOKING OUTBOARD AND FORWARD ram3211054_006.dc, gg/kms, 26/01/99 INB MLG Shock Strut − Removal/Installation Figure 403 (Sheet 1 of 3) Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 414 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Cotter pin. 2. Nut. 3. Washer. 4. Washer. 5. Greasing bolt. 6. Preformed packing. 7. Pin. 9. Anti−rotation washer. D E VIEW LOOKING FORWARD LH MLG MAIN FITTING (REF) SPHERICAL BEARING (REF) 5 C 9 NOTE LH MLG is shown. Post S/B M−DT 17002−32−16. 7 4 FW D E 3 2 LH SHOCK STRUT CYLINDER (REF) D D INB ram3211054_007.dc, kms/rm, 10/02/99 1 6 MLG Shock Strut − Removal/Installation Figure 403 (Sheet 2 of 3) Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 415 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Cotter pin. 2. Nut. 3. Washer. 4. Washer. 5. Greasing bolt. 6. Preformed packing. 7. Pin. 9. Anti−rotation washer. G H VIEW LOOKING FORWARD RH MLG MAIN FITTING SPHERICAL BEARING (REF) F 1 9 NOTE RH MLG is shown. Post S/B M−DT 17002−32−16. 2 3 4 7 FW D 5 D H RH SHOCK STRUT CYLINDER (REF) 6 G ram3211054_008.dc, kms/rm, 10/02/99 INB MLG Shock Strut − Removal/Installation Figure 403 (Sheet 3 of 3) Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 416 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL TASK 32−11−05−400−801 Installation of the MLG Shock Strut 1. Job Set−Up Information **ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7063−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087, 7089−7090, 7093, 7095−7098, 7104, 7107, 7112−7114, 7118−7122, 7124, 7126, 7128, 7130, 7135−7136, 7144, 7158−7214 and ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7062, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088, 7091−7092, 7094, 7099−7103, 7105−7106, 7108−7111, 7115−7117, 7123, 7125, 7127, 7129, 7131−7134, 7137−7143, 7145−7157 Post SB601R−32−065 Subtask 32−11−05−943−006 A. Tools and Equipment REFERENCE None specified None specified DESIGNATION Feeler gauge, 0−0.015 inch (0−0.382 mm) Torque wrench, torque range 0−150 pound−inches (0−20 N·m) **ON A/C 7003, 7020, 7053, 7057, 7081, 7084, 7126, 7140, 7144, 7152, 7164, 7166, 7170, 7182−7184, 7197 and ON A/C 7004−7019, 7021−7052, 7054−7056, 7058−7067, 7069−7080, 7082−7083, 7085−7125, 7127−7139, 7141−7143, 7145−7151, 7153−7163, 7165, 7167−7169, 7171−7181, 7185−7196, 7198−7214 Post SB601R−32−072 Subtask 32−11−05−943−003 B. Tools and Equipment REFERENCE None specified None specified DESIGNATION Feeler gauge, 0−0.015 inch (0−0.382 mm) Torque wrench, torque range 0−150 pound−inches (0−20 N·m) **ON A/C 7215−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7214 Post VSBM−DT−17002−32−16 Subtask 32−11−05−943−005 C. Tools and Equipment REFERENCE Commercially available DESIGNATION Torque wrench, torque range 0−150 pound−inches (0−20 N·m) Master EFFECTIVITY: See Pageblock 32−11−05 page 401 417 32−11−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL Subtask 32−11−05−944−001 D. Consumable Materials REFERENCE 04−005 05−004 16−003 DESIGNATION Grease, aircraft and instrument, gear and actuator screw Lockwire Polyurethane paint, fluid resistant, red, gloss finish **ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7063−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087, 7089−7090, 7093, 7095−7098, 7104, 7107, 7112−7114, 7118−7122, 7124, 7126, 7128, 7130, 7135−7136, 7144, 7158−7214 and ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7062, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088, 7091−7092, 7094, 7099−7103, 7105−7106, 7108−7111, 7115−7117, 7123, 7125, 7127, 7129, 7131−7134, 7137−7143, 7145−7157 Post SB601R−32−065 Subtask 32−11−05−945−001 E. Parts NOTE: REF 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 Quantity for the alternate installation shown in parentheses. NAME OF PART Cotter pin Nut Washer Recessed washer (lower) Greasing bolt, (upper, and preferred lower L/H and R/H) Greasing bolt, (alternate lower L/H) Greasing bolt, (alternate lower R/H) Preformed packing Pin Washer Antirotation washer Recessed washer (upper L/H) Recessed washer (upper R/H) Outer shim Inner shim Cap−end (L/H) Washer (R/H) Antirotation washer Master EFFECTIVITY: See Pageblock 32−11−05 page 401 QTY 2 2 A/R 1 IPC SEQUENCE NO. IPC 32−11−00−02−070 IPC 32−11−00−02−065 IPC 32−11−00−02−060 IPC 32−11−00−02−048 2 [1] IPC 32−11−00−02−050 [1] 12 2 1 1 1 1 A/R A/R 1 1 1 IPC 32−11−00−02−053 IPC 32−11−00−02−055 IPC 32−11−11−01−120 IPC 32−11−00−02−035 IPC 32−11−00−02−037 IPC 32−11−00−02−025 IPC 32−11−00−02−047 IPC 32−11−00−02−046 IPC 32−11−00−02−034 IPC 32−11−00−02−033 IPC 32−11−00−02−045 IPC 32−11−00−02−040 IPC 32−11−00−02−020 418 32−11−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7003, 7020, 7053, 7057, 7081, 7084, 7126, 7140, 7144, 7152, 7164, 7166, 7170, 7182−7184, 7197 and ON A/C 7004−7019, 7021−7052, 7054−7056, 7058−7067, 7069−7080, 7082−7083, 7085−7125, 7127−7139, 7141−7143, 7145−7151, 7153−7163, 7165, 7167−7169, 7171−7181, 7185−7196, 7198−7214 Post SB601R−32−072 Subtask 32−11−05−945−002 F. Parts NOTE: REF 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Quantity for the alternate installation shown in parentheses. NAME OF PART QTY Cotter pin 2 Nut 2 Washer A/R Recessed washer (lower) 1 Greasing bolt, (preferred upper and lower) 2, [1] Greasing bolt, (alternate lower L/H) [1] Greasing bolt, (alternate lower R/H) Preformed packing 12 Pin 2 Washer 1 Antirotation washer 1 Recessed washer (upper L/H and R/H) 1 Outer shim A/R Inner shim A/R Cap−end (L/H and R/H) 1 Antirotation washer 1 IPC SEQUENCE NO. IPC 32−11−00−02−070 IPC 32−11−00−02−065 IPC 32−11−00−02−060 IPC 32−11−00−02−048 IPC 32−11−00−02−050 IPC 32−11−00−02−053 IPC 32−11−00−02−055 IPC 32−11−11−01−120 IPC 32−11−00−02−035 IPC 32−11−00−02−037 IPC 32−11−00−02−025 IPC 32−11−00−02−047 IPC 32−11−00−02−034 IPC 32−11−00−02−033 IPC 32−11−00−02−045 IPC 32−11−00−02−020 **ON A/C 7215−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7214 Post VSBM−DT−17002−32−16 Subtask 32−11−05−945−003 G. Parts REF 1 2 3 4 5 6 7 8 9 NAME OF PART Cotter pin Nut Washer Washer Greasing bolt Preformed packing Pin Antirotation washer Antirotation washer Master EFFECTIVITY: See Pageblock 32−11−05 page 401 QTY 2 2 A/R 2 2 12 2 1 1 IPC SEQUENCE NO. IPC 32−11−00−02−070 IPC 32−11−00−02−065 IPC 32−11−00−02−060 IPC 32−11−00−02−062 IPC 32−11−00−02−050 IPC 32−11−11−01−120 IPC 32−11−00−02−035 IPC 32−11−00−02−025 IPC 32−11−00−02−020 419 32−11−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL Subtask 32−11−05−946−002 H. Reference Information REFERENCE TASK 07−11−01−582−804 TASK 12−12−32−610−802 TASK 12−20−32−640−802 TASK 32−41−01−400−801 TASK 51−26−00−110−801 DESIGNATION Removal of the Aircraft from Jacks Servicing (Oil and Nitrogen) of the MLG Shock Strut − Aircraft on Jacks Lubrication of the Main Landing Gear Installation of the Main Wheel/Tire Assembly Solvent Cleaning 2. Job Set−Up Subtask 32−11−05−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Subtask 32−11−05−110−001 B. Remove any unwanted grease and solvent clean the components that follow (Ref. TASK 51−26−00−110−801): ± The upper and lower attachment points on the MLG shock strut ± The spherical bearing in the MLG main fitting ± The MLG shock strut attachment point on the MLG trailing arm ± All of the MLG shock strut attachment components that were removed in the removal task. 3. Procedure **ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7063−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087, 7089−7090, 7093, 7095−7098, 7104, 7107, 7112−7114, 7118−7122, 7124, 7126, 7128, 7130, 7135−7136, 7144, 7158−7214 and ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7062, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088, 7091−7092, 7094, 7099−7103, 7105−7106, 7108−7111, 7115−7117, 7123, 7125, 7127, 7129, 7131−7134, 7137−7143, 7145−7157 Post SB601R−32−065 Subtask 32−11−05−420−001 Refer to Figure 401. Master EFFECTIVITY: See Pageblock 32−11−05 page 401 420 32−11−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL A. Connect the MLG shock strut to the MLG main fitting [Refer to Figure 401 (Sheet 2)] on the left side of the aircraft as follows: NOTE: The steps that follow apply to the MLG shock strut on the left side of the aircraft only. NOTE: Before you assemble the top of the MLG shock strut to the MLG main fitting, make sure that the three grease holes in the spherical bearing of the MLG main fitting are not clogged with any unwanted materials. (1) Install the cap−end (14) on the pin (7). (2) Apply a thin layer of 04−005 grease to the outside diameter of the pin (7). (3) Align the top of the MLG shock strut with the spherical bearing in the lug of the MLG main fitting. (4) Install the anti−rotation washer (16) over the outboard side of the spherical bearing in the the MLG main fitting and then put the lugs on the top of the shock strut cylinder in position over the MLG main fitting. (5) Align the bores of the bushings and install the pin (7) from the inboard side of the MLG. NOTE: Make sure that the cap−end (14) is correctly installed over the inboard lug on the shock strut cylinder and that the flat edge of the pin (7) is aligned with the anti−rotation lug on the inboard side of the cap−end (14). (6) If the greasing bolt (5) was removed from the pin (7) in the removal procedure, do the steps that follow: (a) Lubricate six serviceable preformed packings (6) and install them on the outside diameter of the greasing bolt (5). (b) Apply a layer of 04−005 grease to the inside diameter of the pin (7) and to the outside diameter of the greasing bolt (5). (c) Install the greasing bolt (5) through the pin (7) from the inboard side. Make sure that the flat edge of the greasing bolt (5) is aligned with the anti−rotation lug on the pin (7). NOTE: The three grease fittings will be pointed towards the anti−rotation lug on the inboard side of the shock strut cylinder. (7) Temporarily install the two inner shims (13), the four outer shims (12), and the recessed washer (10) on the greasing bolt (5). Make sure that the flat edge of the recessed washer (10) is aligned with the anti−rotation lug on the outboard side of the shock strut cylinder. (8) Install a maximum of two washers (3) (as required) to make sure that the cotter pin holes will be aligned when the nut (2) is installed. (9) Install the nut (2). (10) Torque the nut (2) to 85−100 pound−inches (9.61−11.30 N·m). (11) Use a feeler gauge to measure the clearance between the outboard lug of the shock strut cylinder and the recessed washer (10). The clearance must be between 0.010 inch (0.254 mm) and 0.015 inch (0.380 mm). (12) If you do not get the required clearance, do the steps that follow: Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 421 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (a) Remove the nut (2). (b) Adjust the number inner shims (13), or outer shims (12), and also the washers (3) until you get the required clearance and the cotter pin holes are aligned when the nut (2) is installed. NOTE: The inner shims (13) are 0.005 inch (0.127 mm) thick. The outer shims (12) are 0.010 inch (0.254 mm) thick. (c) Install the nut (2) again. (d) Torque the nut (2) to 85−100 pound−inches (9.61−11.30 N·m). (13) Safety the nut (2) with the cotter pin (1). (14) Apply a red torque line on the nut (2), the washer(s) (3), and the recessed washer (10) with 16−003 paint. B. Connect the MLG shock strut to the MLG main fitting [Refer to Figure 401 (Sheet 3)] on the right side of the aircraft as follows: NOTE: The steps that follow apply to the MLG shock strut on the right side of the aircraft only. NOTE: Before you assemble the top of the MLG shock strut to the MLG main fitting, make sure that the three grease holes in the spherical bearing of the MLG main fitting are not clogged with any unwanted materials. (1) Install the washer (15) on the pin (7). (2) Apply a thin layer of 04−005 grease to the outside diameter of the pin (7). (3) Align the top of the MLG shock strut with the spherical bearing in the lug of the MLG main fitting. (4) Install the anti−rotation washer (16) over the inboard side of the spherical bearing in the MLG main fitting and then put the lugs on the top of the shock strut cylinder in position over the MLG main fitting. (5) Align the bores of the bushings and install the pin (7) from the inboard side of the MLG. NOTE: Make sure that the flat edges of both the pin (7) and also the washer (15) are correctly aligned with the anti−rotation lug on the inboard side of the shock strut cylinder. (6) If the greasing bolt (5) was removed from the pin (7) in the removal procedure, do the steps that follow: (a) Lubricate six serviceable preformed packings (6) and install them on the outside diameter of the greasing bolt (5). (b) Apply a layer of 04−005 grease to the inside diameter of the pin (7) and to the outside diameter of the greasing bolt (5). (c) Install the greasing bolt (5) through the pin (7) from the inboard side. Make sure that the flat edge of the greasing bolt (5) is aligned with the anti−rotation lug on the pin (7). The three grease fittings will be pointed towards the anti−rotation lug on the inboard side of the shock strut cylinder. (7) Temporarily install the two inner shims (13), the four outer shims (12), and the recessed washer (11) on the greasing bolt (5). NOTE: The recessed washer (11) does not have a flat edge. Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 422 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (8) Install a maximum of two washers (3) (as required) to make sure that the cotter pin holes will be aligned when the nut (2) is installed. (9) Install the nut (2). (10) Torque the nut (2) to 85−100 pound−inches (9.61−11.30 N·m). (11) Use a feeler gauge to measure the clearance between the outboard lug of the shock strut cylinder and the recessed washer (10). The clearance must be between 0.010 inch (0.254 mm) and 0.015 inch (0.380 mm). (12) If you do not get the required clearance, do the steps that follow: (a) Remove the nut (2). (b) Adjust the number inner shims (13), or outer shims (12), and also the washers (3) until you get the required clearance and the cotter pin holes are aligned when the nut (2) is installed. NOTE: The inner shims (13) are 0.005 inch (0.127 mm) thick. The outer shims (12) are 0.010 inch (0.254 mm) thick. (c) Install the nut (2) again. (d) Torque the nut (2) to 85−100 pound−inches (9.61−11.30 N·m). (13) Safety the nut (2) with the cotter pin (1). (14) Apply a red torque line on the nut (2), the washer(s) (3), and the recessed washer (11) with 16−003 paint. C. Connect the left or the right MLG shock strut [Refer to Figure 401 (Sheet 1)] to the MLG trailing arm as follows: NOTE: Before you assemble the MLG shock strut to the MLG trailing arm, make sure that the three grease holes in the spherical bearing at the bottom the shock strut piston are not clogged with any unwanted materials. (1) Install the spacer (8) on the pin (7). (2) Apply a thin layer of 04−005 grease to the outside diameter of the pin (7). (3) Align the spherical bearing at the bottom of the shock strut piston with the two lugs on the MLG trailing arm. (4) Install the anti−rotation washer (9) over the spherical bearing in the shock strut piston and put the shock strut piston in position between the lugs of the MLG trailing arm. NOTE: The anti−rotation washer (9) is installed on the outboard side of the piston spherical bearing for the left MLG and on the inboard side for the right MLG. (5) Align the bores of the bushings and install the pin (7) from the inboard side of the MLG. NOTE: Make sure that the flat edge of the pin (7) is aligned with the anti−rotation lug on the inboard side of the MLG trailing arm. (6) If the greasing bolt (5) was removed from the pin (7) in the removal procedure, do the steps that follow: (a) Lubricate six serviceable preformed packings (6) and install them on the outside diameter of the greasing bolt (5). Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 423 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (7) (8) (9) (10) (11) (12) (b) Apply a layer of 04−005 grease to the inside diameter of the pin (7) and to the outside diameter of the greasing bolt (5). (c) Install the greasing bolt (5) through the pin (7) from the inboard side. Make sure that the flat edge of the greasing bolt (5) is aligned with the anti−rotation lug on the pin (7). NOTE: The three grease fittings on the greasing bolt (5) will be pointed towards the anti−rotation lug on the inboard side of the MLG trailing arm. Install the recessed washer (4) on the greasing bolt (5). Make sure that the flat edge of the recessed washer (4) is aligned with the anti−rotation lug on the outboard side of the MLG trailing arm. Install a maximum of two washers (3) (as required) to make sure that the cotter pin holes will be aligned when the nut (2) is installed. Install the nut (2). Torque the nut (2) to 85−100 pound−inches (9.61−11.30 N·m). Safety the nut (2) with the cotter pin (1). Apply a red torque line on the nut (2), the washer(s) (3), and the recessed washer (4) with 16−003 paint. **ON A/C 7003, 7020, 7053, 7057, 7081, 7084, 7126, 7140, 7144, 7152, 7164, 7166, 7170, 7182−7184, 7197 and ON A/C 7004−7019, 7021−7052, 7054−7056, 7058−7067, 7069−7080, 7082−7083, 7085−7125, 7127−7139, 7141−7143, 7145−7151, 7153−7163, 7165, 7167−7169, 7171−7181, 7185−7196, 7198−7214 Post SB601R−32−072 Subtask 32−11−05−420−002 Refer to Figure 402. D. Connect the left or the right MLG shock strut to the MLG main fitting [Refer to Figure 402 (Sheet 2 and Sheet 3)] as follows: NOTE: Before you assemble the top of the MLG shock strut to the MLG main fitting, make sure that the three grease holes in the spherical bearing of the MLG main fitting are not clogged with any unwanted materials. (1) Install the cap−end (13) on the pin (7). (2) Apply a thin layer of 04−005 grease to the outside diameter of the pin (7). (3) Align the top of the MLG shock strut with the spherical bearing in the lug of the MLG main fitting. (4) Install the anti−rotation washer (14) over the spherical bearing in the MLG main fitting and then move the lugs on the top of the shock strut cylinder in position over the MLG main fitting. NOTE: The anti−rotation washer (14) is installed on the outboard side of the spherical bearing in MLG main fitting for the left MLG and the inboard side for the right MLG. (5) Align the bores of the bushings and install the pin (7) from the inboard side of the Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 424 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL MLG. NOTE: Make sure that the cap−end (13) is correctly installed over the inboard lug on the shock strut cylinder and that the flat edge of the pin (7) is aligned with the anti−rotation lug on the inboard side of the cap−end (13). (6) If the greasing bolt (5) was removed from the pin (7) in the removal procedure, do the steps that follow: (a) Lubricate six serviceable preformed packings (6) and install them on the outside diameter of the greasing bolt (5). (b) Apply a layer of 04−005 grease to the inside diameter of the pin (7) and to the outside diameter of the greasing bolt (5). (c) Install the greasing bolt (5) through the pin (7) from the inboard side. Make sure that the flat edge of the greasing bolt (5) is aligned with the anti−rotation lug on the pin (7). NOTE: The three grease fittings will be pointed towards the anti−rotation lug on the inboard side of the shock strut cylinder. (7) Temporarily install the two inner shims (12), the four outer shims (11), and the recessed washer (10) on the greasing bolt (5). Make sure that the flat edge of the recessed washer (10) is aligned with the anti−rotation lug on the outboard side of the shock strut cylinder. (8) Install a maximum of two washers (3) (as required) to make sure that the cotter pin holes will be aligned when the nut (2) is installed. (9) Install the nut (2). (10) Torque the nut (2) to 85−100 pound−inches (9.61−11.30 N·m). (11) Use a feeler gauge to measure the clearance between the outboard lug of the shock strut cylinder and the recessed washer (10). The clearance must be between 0.010 inch (0.254 mm) and 0.015 inch (0.380 mm). (12) If you do not get the required clearance, do the steps that follow: (a) Remove the nut (2). (b) Adjust the number inner shims (12), or outer shims (11), and also the washers (3) until you get the required clearance and the cotter pin holes are aligned when the nut (2) is installed. NOTE: The inner shims (12) are 0.005 inch (0.127 mm) thick. The outer shims (11) are 0.010 inch (0.254 mm) thick. (c) Install the nut (2) again. (d) Torque the nut (2) to 85−100 pound−inches (9.61−11.30 N·m). (13) Safety the nut (2) with the cotter pin (1). (14) Apply a red torque line on the nut (2), the washer(s) (3), and the recessed washer (10) with 16−003 paint. E. Connect the left or the right MLG shock strut [Refer to Figure 402 (Sheet 1)] to the MLG trailing arm as follows: NOTE: Before you assemble the MLG shock strut to the MLG trailing arm, make sure that the three grease holes in the spherical bearing at the bottom the shock strut piston are not clogged with any unwanted materials. Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 425 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (1) Install the spacer (8) on the pin (7). (2) Apply a thin layer of 04−005 grease to the outside diameter of the pin (7). (3) Align the spherical bearing at the bottom of the shock strut piston with the two lugs on the MLG trailing arm. (4) Install the anti−rotation washer (9) over the spherical bearing in the shock strut piston and put the shock strut piston in position between the lugs of the MLG trailing arm. NOTE: The anti−rotation washer (9) is installed on the outboard side of the piston spherical bearing for the left MLG and on the inboard side for the right MLG. (5) Align the bores of the bushings and install the pin (7) from the inboard side of the MLG. NOTE: Make sure that the flat edge of the pin (7) is aligned with the anti−rotation lug on the inboard side of the MLG trailing arm. (6) If the greasing bolt (5) was removed from the pin (7) in the removal procedure, do the steps that follow: (a) Lubricate six serviceable preformed packings (6) and install them on the outside diameter of the greasing bolt (5). (b) Apply a layer of 04−005 grease to the inside diameter of the pin (7) and to the outside diameter of the greasing bolt (5). (c) Install the greasing bolt (5) through the pin (7) from the inboard side. Make sure that the flat edge of the greasing bolt (5) is aligned with the anti−rotation lug on the pin (7). NOTE: The three grease fittings will be pointed towards the anti−rotation lug on the MLG trailing arm. (7) Install the recessed washer (4) on the greasing bolt (5). Make sure that the flat edge of the recessed washer (4) is aligned with the anti−rotation lug on the outboard side of the MLG trailing arm. (8) Install a maximum of two washers (3) (as required) to make sure that the cotter pin holes will be aligned when the nut (2) is installed. (9) Install the nut (2). (10) Torque the nut (2) to 85−100 pound−inches (9.61−11.30 N·m). (11) Safety the nut (2) with the cotter pin (1). (12) Apply a red torque line on the nut (2), the washer(s) (3), and the recessed washer (4) with 16−003 paint. **ON A/C 7215−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7214 Post VSBM−DT−17002−32−16 Subtask 32−11−05−420−003 Refer to Figure 403. Master EFFECTIVITY: See Pageblock 32−11−05 page 401 426 32−11−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL F. Connect the left or the right MLG shock strut to the MLG main fitting [Refer to Figure 403 (Sheet 2 and Sheet 3)] as follows: NOTE: Before you assemble the top of the MLG shock strut to the MLG main fitting, make sure that the three grease holes in the spherical bearing of the MLG main fitting are not clogged with any unwanted materials. (1) Apply a thin layer of 04−005 grease to the outside diameter of the pin (7). (2) Align the top of the MLG shock strut with the spherical bearing in the lug of the MLG main fitting. (3) Install the anti−rotation washer (9) over the spherical bearing in the MLG main fitting and then move the lugs on the top of the shock strut cylinder in position over the MLG main fitting. NOTE: The anti−rotation washer (9) is installed on the outboard side of the spherical bearing in MLG main fitting for the left MLG and the inboard side for the right MLG. (4) Align the bores of the bushings and install the pin (7) from the inboard side of the MLG. (5) If the greasing bolt (5) was removed from the pin (7) in the removal procedure, do the steps that follow: (a) Lubricate six serviceable preformed packings (6) and install them on the outside diameter of the greasing bolt (5). (b) Apply a layer of 04−005 grease to the inside diameter of the pin (7) and to the outside diameter of the greasing bolt (5). (c) Install the greasing bolt (5) through the pin (7) from the inboard side. Make sure that the flat edge of the greasing bolt (5) is aligned with the anti−rotation lug on the pin (7). NOTE: The three grease fittings will be pointed towards the anti−rotation lug on the inboard side of the shock strut cylinder. (6) Install the washer (4) on the greasing bolt (5). (7) Install a maximum of two washers (3) (as required) to make sure that the cotter pin holes will be aligned when the nut (2) is installed. (8) Install the nut (2). (9) Torque the nut (2) to 85−100 pound−inches (9.61−11.30 N·m). (10) Safety the nut (2) with the cotter pin (1). (11) Apply a red torque line on the nut (2), the washer(s) (3), and the recessed washer (10) with 16−003 paint. G. Connect the left or the right MLG shock strut [Refer to Figure 403 (Sheet 1)] to the MLG trailing arm as follows: NOTE: Before you assemble the MLG shock strut to the MLG trailing arm, make sure that the three grease holes in the spherical bearing at the bottom the shock strut piston are not clogged with any unwanted materials. (1) Apply a thin layer of 04−005 grease to the outside diameter of the pin (7). (2) Align the spherical bearing at the bottom of the shock strut piston with the two lugs on the MLG trailing arm. Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 427 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (3) Install the anti−rotation washer (8) over the spherical bearing in the shock strut piston and move the shock strut piston in position between the lugs of the MLG trailing arm. NOTE: The anti−rotation washer (8) is installed on the outboard side of the piston spherical bearing for the left MLG and on the inboard side for the right MLG. (4) Align the bores of the bushings and install the pin (7) from the inboard side of the MLG. NOTE: Make sure that the flat edge of the pin (7) is aligned with the anti−rotation lug on the inboard side of the MLG trailing arm. (5) If the greasing bolt (5) was removed from the pin (7) in the removal procedure, do the steps that follow: (a) Lubricate six serviceable preformed packings (6) and install them on the outside diameter of the greasing bolt (5). (b) Apply a layer of 04−005 grease to the inside diameter of the pin (7) and to the outside diameter of the greasing bolt (5). (c) Install the greasing bolt (5) through the pin (7) from the inboard side. Make sure that the flat edge of the greasing bolt (5) is aligned with the anti−rotation lug on the pin (7). NOTE: The three grease fittings will be pointed towards the anti−rotation lug on the MLG trailing arm. (6) Install the washer (4) on the greasing bolt (5). (7) Install a maximum of two washers (3) (as required) to make sure that the cotter pin holes will be aligned when the nut (2) is installed. (8) Install the nut (2). (9) Torque the nut (2) to 85−100 pound−inches (9.61−11.30 N·m). (10) Safety the nut (2) with the cotter pin (1). (11) Apply a red torque line on the nut (2), the washer(s) (3), and the recessed washer (4) with 16−003 paint. **ON A/C ALL 4. Close Out Subtask 32−11−05−865−002 A. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 ZONE 221 221 222 222 Page 428 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−11−05−863−003 B. If the MLG shock strut was unserviceable and was replaced, make sure that the MLG shock strut is correctly pressurized with nitrogen (Ref. TASK 12−12−32−610−802). Subtask 32−11−05−640−001 C. Lubricate the MLG at the locations that follow (Ref. TASK 12−20−32−640−802): (1) Use a grease gun to apply 04−005 grease through the three grease inserts on the upper greasing bolt (5). Make sure that the grease is seen to come out from the inboard and outboard MLG shock strut bushings and from the spherical bearing in the MLG main fitting. (2) Use a grease gun to apply 04−005 grease through the three grease inserts on the lower greasing bolt (5). Make sure that the grease is seen to come out from the inboard and outboard MLG trailing arm bushings and from the spherical bearing at the bottom of the MLG shock strut. (3) Use a grease gun to apply 04−005 grease through the grease fitting at the bottom of the MLG shock strut. Make sure that the grease is seen to come out from the shock strut attachment−joint. Subtask 32−11−05−410−001 D. Install the inboard main wheel/tire−assembly (Ref. TASK 32−41−01−400−801). Subtask 32−11−05−582−002 E. F. Remove the axle jack from below the MLG jacking pad that was used to support the trailing arm. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−11−05−941−002 G. Remove all tools, placards, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−11−05 page 401 32−11−05 Page 429 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL SHOCK STRUT, MAIN LANDING GEAR − ADJUSTMENT/TEST 1. General A. The maintenance procedure that follows is for the functional test of the main landing gear (MLG) shock strut. Each shock strut is attached between the main fitting and the MLG trailing arm. TASK 32−11−05−720−801 Functional Test of the Main Landing Gear (MLG) Shock Strut Extension 1. Reason for the Job Refer to MRB 32−00−00−11. 2. Job Set−Up Information Subtask 32−11−05−943−007 A. Tools and Equipment REFERENCE 14−6805−8000 DESIGNATION Gauge kit − strut/accumulator nitrogen servicing Subtask 32−11−05−944−003 B. Consumable Materials REFERENCE 05−002 DESIGNATION Nitrogen, technical Subtask 32−11−05−946−004 C. Reference Information REFERENCE TASK 12−12−32−610−801 DESIGNATION Servicing (Oil and Nitrogen) of the MLG Shock Strut − A/C on the Ground 3. Procedure Subtask 32−11−05−720−001 Refer to Figure 501 and Figure 502. A. Do a functional check of the MLG shock strut extension as follows: (1) Measure and record the chrome extension of the MLG shock strut (dimension ‘X’). (2) Remove the dust cap from the nitrogen charging valve at the top of the shock strut. (3) Connect the gauge kit to the nitrogen charging valve. Master EFFECTIVITY: See Pageblock 32−11−05 page 501 501 32−11−05 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL (4) Slowly turn the thin nut on the nitrogen charging valve to the open position and read the pressure on the pressure gauge. (5) If the ambient temperature is 41°F to 77°F (5°C to 25°C), refer to the MLG−shock−strut service plate and find the correct extension for the shock strut as follows: (a) On the service plate, find the pressure gauge reading on the vertical scale (PRESSURE GAUGE READING (PSI)). (b) From the pressure reading, go across horizontally to the area (range) between the two lines of the SERVICING CURVE. (c) From this range, between the lines of the SERVICING CURVE, go down vertically to the ‘X’ DIMENSION (INCHES) scale. (d) Record the range from the ‘X’ DIMENSION (INCHES) scale. (6) If the ambient temperature is −65°F to 86°F (−54°C to 30°C), refer to the alternate MLG servicing curve (Refer to Figure 502) and find the correct extension for the shock strut as follows: (a) On the alternate MLG servicing curve, find the pressure gauge reading on the vertical scale (strut pressure (X 10³ PSI)). (b) From the pressure reading, go across horizontally to a point on the servicing curve depending on the ambient temperature. (c) From this point on the servicing curve, go down vertically to the ‘Exposed Chrome (in.)’ scale. (d) Record the reading from the ‘Exposed Chrome (in.)’ scale. (7) If the chrome extension measurement (dimension ‘‘X’’) is in the limits found on the charts, the shock strut extension is good and servicing is not necessary. Do the steps that follow: (a) Close the thin nut. (b) Slowly disconnect the gauge kit from the nitrogen charging valve. (c) Install the dust cap on the nitrogen charging valve. (8) If the extension is not correct, service the MLG shock strut with oil and nitrogen (Ref. TASK 12−12−32−610−801). 4. Close Out Subtask 32−11−05−943−008 A. Remove all tools, equipment and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−11−05 page 501 502 32−11−05 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Dust cap. 2. Nitrogen charging valve. 3. Thin nut. A NOTE X = Chrome Extension. B SERVICE PLATE SHOCK STRUT ASSEMBLY 3 2 X 1 A ram1212323_005.dc, pb, 28/09/95 B MAIN LANDING GEAR Main Landing Gear (MLG) Shock Strut Extension − Functional Test Figure 501 Master EFFECTIVITY: See Pageblock 32−11−05 page 501 503 32−11−05 DecPage 15/2004 C −1.0 0.0 0.5 1.0 1.5 2.0 2.5 4.0 4.5 5.0 5.5 6.0 3 LOAD ( X 10 3 LBS ) 0 10 20 30 40 50 60 70 80 90 100 STRUT PRESSURE ( X 10 PSI ) Exposed Chrome (in.) ram1212323_008.dg, rm, 20/09/00 −30 3.0 −54 −15 3.5 0 15 30 0.0 1.0 2.0 3.0 4.0 5.0 6.0 7.0 8.0 9.0 10.0 AIRCRAFT MAINTENANCE MANUAL Alternate MLG Servicing Curves Figure 502 Master EFFECTIVITY: See Pageblock 32−11−05 page 501 504 32−11−05 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL SHOCK STRUT, MAIN LANDING GEAR (MLG) − INSPECTION/CHECK 1. General A. The maintenance procedure is the detailed inspection of the main−landing−gear (MLG) shock strut. TASK 32−11−05−220−801 Detailed Inspection of the MLG Shock Strut Extension 1. Reason for the Job Refer to MRB 32−00−00−11. 2. Job Set−Up Information Subtask 32−11−05−943−001 A. Tools and Equipment REFERENCE 14−6805−8000 DESIGNATION Gauge kit − strut/accumulator nitrogen servicing Subtask 32−11−05−944−002 B. Consumable Materials REFERENCE 05−002 DESIGNATION Nitrogen, technical Subtask 32−11−05−946−003 C. Reference Information REFERENCE TASK 12−12−32−220−801 DESIGNATION Extension Check and Adjustment (with Nitrogen) of the MLG Shock Strut 3. Procedure Subtask 32−11−05−220−001 A. Do a check of the chrome area of each MLG shock−strut piston for correct extension as follows: NOTE: This procedure is applicable only if the ambient temperature is 41°F to 77°F (5°C to 25°C). If the ambient temperature is not 41°F to 77°F (5°C to 25°C), refer to TASK 12−12−32−220−801. (1) Measure and record the chrome extension of the MLG−shock−strut (dimension ‘‘X’’). (2) Remove the dust cap from the nitrogen charging valve at the top of the shock strut. Master EFFECTIVITY: See Pageblock 32−11−05 page 601 32−11−05 Page 601 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL B. (3) Connect the gauge kit to the nitrogen charging valve. (4) Slowly turn the thin nut on the nitrogen charging valve to the open position and read the pressure on the pressure gauge. (5) Find the shock strut pressure on the side scale of the servicing placard graph. Read the graph to find the permitted extension (dimension X) of the shock strut chrome for the shock strut pressure. (6) If the chrome extension measurement (dimension ‘‘X’’) is in the limits found on the ‘‘X’’ DIMENSION (INCHES) scale, the shock strut extension is good and servicing is not necessary. (7) Close the thin nut. (8) Slowly disconnect the gauge kit from the nitrogen charging valve. (9) Install the dust cap on the nitrogen charging valve. If the extension is not correct, service the MLG shock strut (Ref. TASK 12−12−32−220−801). 4. Close Out Subtask 32−11−05−943−002 A. Remove all tools, equipment and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−11−05 page 601 32−11−05 Page 602 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL TRAILING ARM − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the trailing arm assembly of the main landing gear (MLG). TASK 32−11−10−000−801 Removal of the Trailing Arm 1. Job Set−Up Information Subtask 32−11−10−946−001 A. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−41−01−000−801 TASK 32−44−01−000−801 TASK 32−11−15−000−801 TASK 32−11−25−000−801 TASK 32−43−26−000−801 DESIGNATION Put the Aircraft on Jacks Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Removal of the Main Wheel/Tire Assembly Removal of the Wheel Speed Transducer Removal of the MLG Axle Removal of the Swivel Coupling Assembly Removal of the Brake Unit 2. Job Set−Up Subtask 32−11−10−941−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802. WARNING: A. Subtask 32−11−10−582−001 B. Put the aircraft on jacks (Ref. TASK 07−11−01−582−801). Make sure that the main wheel/tire−assemblies do not touch the ground and that approximately 5 inches (127 mm) of the chrome surface of the shock strut piston can be seen. Subtask 32−11−10−010−001 C. D. Remove the wheel speed transducers from the MLG (Ref. TASK 32−44−01−000−801). Remove the inboard and outboard wheel assemblies (Ref. TASK 32−41−01−000−801). Master EFFECTIVITY: See Pageblock 32−11−10 page 401 32−11−10 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL E. F. G. Remove the inboard and outboard brake units (Ref. TASK 32−43−26−000−801). If required, remove the MLG axle assembly (Ref. TASK 32−11−15−000−801). NOTE: It will not be necessary to remove the MLG axle assembly if the MLG trailing arm that will be removed is the same one that will be installed again in the installation task. Remove the inboard and outboard swivel coupling assemblies (and the related MLG electrical harness components as necessary) (Ref. TASK 32−11−25−000−801). NOTE: Disconnect only as many components as required to remove the swivel coupling assemblies. Disconnect the rigid brake lines for the inboard and the outboard brakes at the quick disconnect couplings only. Do this so that you will not have to bleed the brakes too much when the brake units are installed again. 3. Procedure **ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7063−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087, 7089−7090, 7093, 7095−7098, 7104, 7107, 7112−7114, 7118−7122, 7124, 7126, 7128, 7130, 7135−7136, 7144, 7158−7214 and ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7062, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088, 7091−7092, 7094, 7099−7103, 7105−7106, 7108−7111, 7115−7117, 7123, 7125, 7127, 7129, 7131−7134, 7137−7143, 7145−7157 Post SB601R−32−065 Subtask 32−11−10−020−001 Refer to Figure 401. A. Remove the MLG trailing arm as follows: (1) Disconnect the MLG shock strut from the MLG trailing arm as follows: (a) Remove and discard the cotter pin (1). (b) Remove the nut (2), the washers (3), the recessed washer (4) from the greasing bolt (5). (c) Support the MLG trailing arm in position. (d) Hold the MLG shock strut in position by hand and use a soft face drift to remove the pin (7) and the washer (8). Do not remove the greasing bolt (5) from the pin (7) unless it is necessary for other maintenance. (e) If it is necessary to remove the greasing bolt (5) from the pin (7), do the steps that follow: 1 Remove the greasing bolt (5). 2 Remove and discard the six preformed packings (6) from the greasing bolt (5). (f) Move the piston spherical bearing at the bottom of the MLG shock strut from between the two lugs on the trailing arm, and remove the anti−rotation washer Master EFFECTIVITY: See Pageblock 32−11−10 page 401 402 32−11−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (9) from the piston spherical bearing. NOTE: The anti−rotation washer (9) is installed on the outboard side of the piston spherical bearing for the left MLG and the inboard side for the right MLG. (2) Disconnect the MLG trailing arm from the MLG main fitting as follows: (a) Remove the sealant from the head of the bolt (15) and from the nut (10). (b) At the top of the MLG trailing arm, remove and discard the cotter pin (11) from the nut (10). (c) Remove the nut (10), and the washers (12) and (13), from the bolt (15). (d) Remove the bolt (15) with the washers (12) and (13) from the MLG trailing arm. (e) Hold the MLG trailing arm in position and carefully remove the main fitting pin (14) to disconnect the MLG main fitting from the MLG trailing arm. (3) Carefully remove the MLG trailing arm from the MLG main fitting. **ON A/C 7215−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7214 Post VSBM−DT−17002−32−16 Subtask 32−11−10−020−002 Refer to Figure 402. B. Remove the MLG trailing arm as follows: (1) Disconnect the MLG shock strut from the MLG trailing arm as follows: (a) Remove and discard the cotter pin (1). (b) Remove the nut (2), the washers (3), and the washer (4) from the greasing bolt (5). (c) Support the MLG trailing arm in position. (d) Hold the MLG shock strut in position by hand and use a soft face drift to remove the pin (7). Do not remove the greasing bolt (5) from the pin (7) unless it is necessary for other maintenance. (e) If it is necessary to remove the greasing bolt (5) from the pin (7), do the steps that follow: 1 Remove the greasing bolt (5). 2 Remove and discard the six preformed packings (6) from the greasing bolt (5). (f) Move the piston spherical bearing at the bottom of the MLG shock strut from between the two lugs on the trailing arm, and remove the anti−rotation washer (8) from the piston spherical bearing. NOTE: The anti−rotation washer (8) is installed on the outboard side of the piston spherical bearing for the left MLG and the inboard side for the right MLG. (2) Disconnect the MLG trailing arm from the MLG main fitting as follows: Master EFFECTIVITY: See Pageblock 32−11−10 page 401 403 32−11−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (a) Remove the sealant from the head of the bolt (14) and from the nut (9). (b) At the top of the MLG trailing arm, remove and discard the cotter pin (10) from the nut (9). (c) Remove the nut (9), and the washers (11) and (12), from the bolt (14). (d) Remove the bolt (14) with the washers (11) and (12) from the MLG trailing arm. (e) Hold the MLG trailing arm in position and carefully remove the main fitting pin (13) to disconnect the MLG main fitting from the MLG trailing arm. (3) Carefully remove the MLG trailing arm from the MLG main fitting. Master EFFECTIVITY: See Pageblock 32−11−10 page 401 32−11−10 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL MLG MAIN FITTING (REF) A NOTES Right MLG is shown Left MLG is opposite. Post S/B 601R−32−065. Pre S/B M−DT 17002 −32−16. B 1 Item 9 is installed on the outboard side for the left MLG. FW D 15 14 12 13 A SHOCK STRUT PISTON (REF) D INB GREASE FITTING (REF) SPHERICAL BEARING (REF) 10 1. Cotter pin. 2. Nut. 3. Washer. 4. Recessed washer. 5. Greasing bolt. 6. Preformed packing. 7. Pin. 8. Washer 9. Anti−rotation washer. 10. Nut. 11. Cotter pin. 12. Washer. 13. Washer. 14. Main fitting pin. 15. Bolt. 13 12 MLG TRAILING ARM (REF) 4 1 9 2 3 5 7 8 6 B VIEW LOOKING OUTBOARD AND FORWARD 1 ram3211104_001(4).dc, jp/rm, 05/02/99 11 LEGEND MLG Trailing Arm − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−11−10 page 401 32−11−10 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL MLG MAIN FITTING (REF) A NOTE Right MLG is shown Left MLG is opposite. Post S/B M−DT− 17002−32−16. 1 Item 8 is installed on the outboard side for the left MLG. B 14 13 FW D 11 12 D INB A SHOCK STRUT PISTON (REF) GREASE FITTING (REF) SPHERICAL BEARING (REF) 9 LEGEND 1. Cotter pin. 2. Nut. 3. Washer. 4. Recessed washer. 5. Greasing bolt. 6. Preformed packing. 7. Pin. 8. Anti−rotation washer. 9. Nut. 10. Cotter pin. 11. Washer. 12. Washer. 13. Main fitting pin. 14. Bolt. 12 11 MLG TRAILING ARM (REF) 4 1 8 2 3 5 7 6 B VIEW LOOKING OUTBOARD AND FORWARD 1 ram3211104_002.dc, kms/pt, 31/10/00 10 MLG Trailing Arm − Removal/Installation Figure 402 Master EFFECTIVITY: See Pageblock 32−11−10 page 401 32−11−10 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL TASK 32−11−10−400−801 Installation of the Trailing Arm 1. Job Set−Up Information Subtask 32−11−10−943−001 A. Tools and Equipment REFERENCE None specified None specified DESIGNATION Plastic scraper Torque wrench, torque range 0−150 pound−inches (0−20 N·m) Subtask 32−11−10−944−001 B. Consumable Materials REFERENCE 04−005 06−028 09−009 16−003 DESIGNATION Grease, aircraft and instrument, gear and actuator screw Compound, corrosion−preventive, solvent cutback, cold application − Grade 4 Sealant, corrosion−inhibitive (Pro−Seal 870B1/2) Polyurethane paint, fluid resistant, red, gloss finish **ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7063−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087, 7089−7090, 7093, 7095−7098, 7104, 7107, 7112−7114, 7118−7122, 7124, 7126, 7128, 7130, 7135−7136, 7144, 7158−7214 and ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7062, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088, 7091−7092, 7094, 7099−7103, 7105−7106, 7108−7111, 7115−7117, 7123, 7125, 7127, 7129, 7131−7134, 7137−7143, 7145−7157 Post SB601R−32−065 Subtask 32−11−10−945−001 C. Parts REF 1 2 3 4 5 6 NAME OF PART Cotter pin Nut Washer Recessed washer Greasing bolt, (preferred) Greasing bolt, (alternate L/H) Greasing bolt, (alternate R/H) Preformed packing Master EFFECTIVITY: See Pageblock 32−11−10 page 401 QTY 1 1 A/R 1 1 6 IPC SEQUENCE NO. IPC 32−11−00−02−070 IPC 32−11−00−02−065 IPC 32−11−00−02−060 IPC 32−11−00−02−048 IPC 32−11−00−02−050 IPC 32−11−00−02−053 IPC 32−11−00−02−055 IPC 32−11−11−01−120 407 32−11−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL REF 7 8 9 10 11 12 13 14 15 NAME OF PART Pin Washer Antirotation washer Nut Cotter pin Washer Washer Main fitting pin Bolt QTY 1 1 1 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−11−00−02−035 IPC 32−11−00−02−037 IPC 32−11−00−02−025 IPC 32−11−00−02−170 IPC 32−11−00−02−175 IPC 32−11−00−02−165 IPC 32−11−00−02−160 IPC 32−11−00−02−150 IPC 32−11−00−02−155 **ON A/C 7215−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7214 Post VSBM−DT−17002−32−16 Subtask 32−11−10−945−002 D. Parts REF 1 2 3 4 5 6 7 8 9 10 11 12 13 14 NAME OF PART Cotter pin Nut Washer Washer Greasing bolt Preformed packing Pin Antirotation washer Nut Cotter pin Washer Washer Main fitting pin Bolt QTY 1 1 A/R 1 1 6 1 1 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−11−00−02−070 IPC 32−11−00−02−065 IPC 32−11−00−02−060 IPC 32−11−00−02−062 IPC 32−11−00−02−050 IPC 32−11−11−01−120 IPC 32−11−00−02−035 IPC 32−11−00−02−025 IPC 32−11−00−02−170 IPC 32−11−00−02−175 IPC 32−11−00−02−165 IPC 32−11−00−02−160 IPC 32−11−00−02−150 IPC 32−11−00−02−155 **ON A/C ALL Subtask 32−11−10−946−002 E. Reference Information REFERENCE TASK 07−11−01−582−804 TASK 12−20−32−640−802 TASK 32−11−15−400−801 DESIGNATION Removal of the Aircraft from Jacks Lubrication of the Main Landing Gear Installation of the MLG Axle Master EFFECTIVITY: See Pageblock 32−11−10 page 401 408 32−11−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL REFERENCE TASK 32−11−25−400−801 TASK 32−41−01−400−801 TASK 32−43−26−400−801 TASK 32−44−01−400−801 TASK 51−26−00−110−801 DESIGNATION Installation of the Swivel Coupling Assembly Installation of the Main Wheel/Tire Assembly Installation of the Brake Unit Installation of the Wheel Speed Transducer Solvent Cleaning 2. Job Set−Up Subtask 32−11−10−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. **ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7063−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087, 7089−7090, 7093, 7095−7098, 7104, 7107, 7112−7114, 7118−7122, 7124, 7126, 7128, 7130, 7135−7136, 7144, 7158−7214 and ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7062, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088, 7091−7092, 7094, 7099−7103, 7105−7106, 7108−7111, 7115−7117, 7123, 7125, 7127, 7129, 7131−7134, 7137−7143, 7145−7157 Post SB601R−32−065 Subtask 32−11−10−110−001 B. C. Use a plastic scraper and solvent (Ref. TASK 51−26−00−110−801) to remove any unwanted sealant that remains on the MLG trailing arm at the head of the bolt (15) and at the nut (10). Remove any unwanted grease and solvent clean the components that follow (Ref. TASK 51−26−00−110−801): ± The spherical bearing at the bottom the MLG shock strut ± The MLG shock strut attachment point on the MLG trailing arm ± All of the MLG trailing arm attachment components that were removed in the removal task. **ON A/C 7215−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7214 Post VSBM−DT−17002−32−16 Subtask 32−11−10−110−002 D. E. Use a plastic scraper and solvent (Ref. TASK 51−26−00−110−801) to remove any unwanted sealant that remains on the MLG trailing arm at the head of the bolt (14) and at the nut (9). Remove any unwanted grease and solvent clean the components that follow (Ref. TASK 51−26−00−110−401): ± The spherical bearing at the bottom the MLG shock strut ± The MLG shock strut attachment point on the MLG trailing arm Master EFFECTIVITY: See Pageblock 32−11−10 page 401 409 32−11−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL ± All of the MLG trailing arm attachment components that were removed in the removal task. **ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7063−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087, 7089−7090, 7093, 7095−7098, 7104, 7107, 7112−7114, 7118−7122, 7124, 7126, 7128, 7130, 7135−7136, 7144, 7158−7214 and ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7062, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088, 7091−7092, 7094, 7099−7103, 7105−7106, 7108−7111, 7115−7117, 7123, 7125, 7127, 7129, 7131−7134, 7137−7143, 7145−7157 Post SB601R−32−065 3. Procedure Subtask 32−11−10−420−001 Refer to Figure 401. A. Install the MLG trailing arm to the MLG main fitting as follows: (1) Apply a layer of 04−005 grease to the bores of the bushings in the fork of the MLG main fitting and the two bushings in the head of the MLG trailing arm. (2) Align the bushings in the fork of the MLG main fitting with the bushings in the head of the MLG trailing arm and install the main fitting pin (14). Make sure that the proximity sensor targets are at the top of the main fitting pin (14) and that the threaded attachment lugs for the swivel couplings are at the aft edge of the main fitting pin (14). (3) Install the washer (12) and then the washer (13) on the bolt (15). (4) Align the holes for the bolt (15) in the main fitting pin (14) with their related holes in the MLG trailing arm. (5) Make sure that there is a layer of 06−028 corrosion−preventive compound on the mating surfaces of the bolt (15) and the related holes in the main fitting pin (14) and the MLG trailing arm. (6) Install the bolt (15) through the end of the MLG trailing arm and the main fitting pin (14). (7) Install the washers (13) and (12), and the nut (10) on the bolt (15). (8) Torque the nut (10) to 90−100 pound−inches (10.17−11.3 N·m). (9) Safety the nut (10) with the cotter pin (11). B. Connect the MLG shock strut to the MLG trailing arm as follows: NOTE: Before you assemble the MLG shock strut to the MLG trailing arm, make sure that the three grease holes in the spherical bearing at the bottom the shock strut piston are not clogged with any unwanted materials. (1) Install the spacer (8) on the pin (7). (2) Apply a thin layer of 04−005 grease to the outside diameter of the pin (7). (3) Align the spherical bearing at the bottom of the shock strut piston with the two lugs on the MLG trailing arm. (4) Install the anti−rotation washer (9) over the spherical bearing on the shock strut piston and put the shock strut piston in position between the lugs of the MLG trailing Master EFFECTIVITY: See Pageblock 32−11−10 page 401 410 32−11−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL arm. NOTE: (5) (6) (7) (8) (9) (10) (11) (12) The anti−rotation washer (9) is installed on the outboard side of the piston spherical bearing for the left MLG and on the inboard side for the right MLG. Align the bores of the bushings and install the pin (7) from the inboard side of the MLG. NOTE: Make sure that the flat edge of the pin (7) is aligned with the anti−rotation lug on the inboard side of the MLG trailing arm. If the greasing bolt (5) was removed from the pin (7) in the removal procedure, do the steps that follow: (a) Lubricate six serviceable preformed packings (6) with 04−005 grease and install them on the outside diameter of the greasing bolt (5). (b) Apply a layer of 04−005 grease to the inside diameter of the pin (7) and to the outside diameter of the greasing bolt (5). (c) Install the greasing bolt (5) through the pin (7) from the inboard side. Make sure that the flat edge of the greasing bolt (5) is aligned with the anti−rotation lug on the pin (7). NOTE: The three grease inserts on the greasing bolt (5) will be pointed towards the anti−rotation lug on the inboard side of the MLG trailing arm. Install the recessed washer (4) on the greasing bolt (5). Make sure that the flat edge of the recessed washer (4) is aligned with the anti−rotation lug on the outboard side of the MLG trailing arm. Install a maximum of two washers (3) (as required) to make sure that the cotter pin holes will be aligned when the nut (2) is installed. Install the nut (2). Torque the nut (2) to 85−100 pound−inches (9.61−11.30 N·m). Safety the nut (2) with the cotter pin (1). Apply a red torque line on the nut (2), the washer(s) (3), and the recessed washer (4) with 16−003 paint. Subtask 32−11−10−390−001 C. Apply a layer (dome) of 09−009 sealant to the head of the bolt (15) and the nut (10). Make sure that the bolt (15) and the nut (10) are covered completely with sealant. **ON A/C 7215−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7214 Post VSBM−DT−17002−32−16 4. Procedure Subtask 32−11−10−420−002 Refer to Figure 402. Master EFFECTIVITY: See Pageblock 32−11−10 page 401 411 32−11−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL A. B. Install the MLG trailing arm to the MLG main fitting as follows: (1) Apply a layer of 04−005 grease to the bores of the bushings in the fork of the MLG main fitting and the two bushings in the head of the MLG trailing arm. (2) Align the bushings in the fork of the MLG main fitting with the bushings in the head of the MLG trailing arm and install the main fitting pin (13). Make sure that the proximity sensor targets are at the top of the main fitting pin (13) and that the threaded attachment lugs for the swivel couplings are at the aft edge of the main fitting pin (13). (3) Install the washer (11) and then the washer (12) on the bolt (14). (4) Align the holes for the bolt (14) in the main fitting pin (13) with their related holes in the MLG trailing arm. (5) Make sure that there is a layer of 06−028 corrosion−preventive compound on the mating surfaces of the bolt (14) and the related holes in the main fitting pin (13) and the MLG trailing arm. (6) Install the bolt (14) through the end of the MLG trailing arm and the main fitting pin (13). (7) Install the washers (12) and (11), and the nut (9) on the bolt (14). (8) Torque the nut (9) to 90−100 pound−inches (10.17−11.3 N·m). (9) Safety the nut (9) with the cotter pin (10). Connect the MLG shock strut to the MLG trailing arm as follows: NOTE: Before you assemble the MLG shock strut to the MLG trailing arm, make sure that the three grease holes in the spherical bearing at the bottom the shock strut piston are not clogged with any unwanted materials. (1) Apply a thin layer of 04−005 grease to the outside diameter of the pin (7). (2) Align the spherical bearing at the bottom of the shock strut piston with the two lugs on the MLG trailing arm. (3) Install the anti−rotation washer (8) over the spherical bearing of the shock strut piston and move the shock strut piston in position between the lugs of the MLG trailing arm. NOTE: The anti−rotation washer (8) is installed on the outboard side of the piston spherical bearing for the left MLG and on the inboard side for the right MLG. (4) Align the bores of the bushings and install the pin (7) from the inboard side of the MLG. NOTE: Make sure that the flat edge of the pin (7) is aligned with the anti−rotation lug on the inboard side of the MLG trailing arm. (5) If the greasing bolt (5) was removed from the pin (7) in the removal procedure, do the steps that follow: (a) Lubricate six serviceable preformed packings (6) with 04−005 grease and install them on the outside diameter of the greasing bolt (5). (b) Apply a layer of 04−005 grease to the inside diameter of the pin (7) and to the outside diameter of the greasing bolt (5). (c) Install the greasing bolt (5) through the pin (7) from the inboard side. Make sure that the flat edge of the greasing bolt (5) is aligned with the anti−rotation Master EFFECTIVITY: See Pageblock 32−11−10 page 401 32−11−10 Page 412 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (6) (7) (8) (9) (10) (11) lug on the pin (7). NOTE: The three grease inserts on the greasing bolt (5) will be pointed towards the anti−rotation lug on the inboard side of the MLG trailing arm. Install the washer (4) on the greasing bolt (5). Install a maximum of two washers (3) (as required) to make sure that the cotter pin holes will be aligned when the nut (2) is installed. Install the nut (2). Torque the nut (2) to 85−100 pound−inches (9.61−11.30 N·m). Safety the nut (2) with the cotter pin (1). Apply a red torque line on the nut (2), the washer(s) (3), and the washer (4) with 16−003 paint. Subtask 32−11−10−390−002 C. Apply a layer (dome) of 09−009 sealant to the head of the bolt (14) and the nut (9). Make sure that the bolt (14) and the nut (9) are covered completely with sealant. **ON A/C ALL 5. Close Out Subtask 32−11−10−410−001 A. B. C. D. E. Install the MLG axle assembly if it was removed in the removal task (Ref. TASK 32−11−15−400−801). Install the inboard and outboard brake units (Ref. TASK 32−43−26−400−801). Install the two swivel coupling assemblies (and the related MLG electrical harness components as necessary) (Ref. TASK 32−11−25−400−801). Make sure that there is a minimum of 0.125 inch (3.18 mm) clearance between the greasing bolt (5) and the MLG electrical harness. Install the wheel speed transducers (Ref. TASK 32−44−01−400−801). Install the inboard and outboard wheels (Ref. TASK 32−41−01−400−801). Subtask 32−11−10−640−001 F. Lubricate the MLG at the locations that follow (Ref. TASK 12−20−32−640−802): NOTE: Make sure that the lubrication of the two swivel coupling assemblies was done (Ref. TASK 32−11−25−400−801). (1) Use a grease gun to apply 04−005 grease through the three grease inserts on the greasing bolt (5). Make sure that the grease is seen to come out from the inboard and outboard MLG trailing arm bushings and from the spherical bearing. (2) Use a grease gun to apply 04−005 grease through the grease fitting at the bottom of the MLG shock strut. Make sure that the grease is seen to come out from the shock strut attachment−joint. Master EFFECTIVITY: See Pageblock 32−11−10 page 401 32−11−10 Page 413 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−11−10−582−002 G. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−11−10−941−002 H. Remove all tools, placards, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−11−10 page 401 32−11−10 Page 414 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL MAIN LANDING GEAR (MLG) AXLE − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the main landing gear (MLG) axle. The MLG axle is installed on the trailing arm of the MLG. TASK 32−11−15−000−801 Removal of the MLG Axle 1. Job Set−Up Information Subtask 32−11−15−946−001 A. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−41−01−000−801 TASK 32−44−01−000−801 TASK 32−61−20−000−801 TASK 32−61−20−000−802 DESIGNATION Put the Aircraft on Jacks Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Removal of the Main Wheel/Tire Assembly Removal of the Wheel Speed Transducer Removal of the MLG Electrical Harness − Outboard Removal of the MLG Electrical Harness − Inboard 2. Job Set−Up Subtask 32−11−15−941−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. Subtask 32−11−15−582−001 B. Put the aircraft on jacks (Ref. TASK 07−11−01−582−801). Subtask 32−11−15−010−001 C. D. E. Remove the wheel speed transducers (Ref. TASK 32−44−01−000−801). Remove the two main wheel/tire assemblies and their related axle spacers (Ref. TASK 32−41−01−000−801). Disconnect the end of the MLG outboard and inboard electrical harnesses which are connected to the wheel speed transducers (Ref. TASK 32−61−20−000−801 and TASK 32−61−20−000−802). Master EFFECTIVITY: See Pageblock 32−11−15 page 401 32−11−15 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL F. Remove the electrical harnesses of the two wheel speed transducers from the MLG axle (Ref. TASK 32−61−20−000−801 and TASK 32−61−20−000−802). Do not disconnect the electrical harness connectors at the brake−temperature thermocouple sensors. 3. Procedure Subtask 32−11−15−020−001 Refer to Figure 401. A. Remove and discard the two cotter pins (1). B. Remove the nuts (2), the washers (3) and (4), and the bolts (5) that attach the jacking pad (6) and the cross axle pin (7) to the MLG trailing arm. Remove the jacking pad (6). C. Carefully remove the cross axle pin (7). D. Remove the MLG axle (8) from the MLG trailing arm. Be careful not to damage the threads on the MLG axle (8) when you remove it. Master EFFECTIVITY: See Pageblock 32−11−15 page 401 32−11−15 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Cotter pin. 2. Nut. 3. Washer. 4. Washer. 5. Bolt. 6. Jacking pad. 7. Cross axle pin. 8. MLG axle. A NOTE 1 Use of washers (3 and 4) as required to install the cotter pin (1) correctly. Make sure that there is a minimum of one washer under the head of the bolt (5) and under the nut (2). AXLE SPACER (REF) MLG TRAILING ARM (REF) 8 5 4 3 1 7 2 1 3 4 6 1 A ram3211154_001(2).dc, jr/rm, 25/02/97 AXLE SPACER (REF) MLG Axle − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−11−15 page 401 32−11−15 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−11−15−400−801 Installation of the MLG Axle 1. Job Set−Up Information Subtask 32−11−15−943−002 A. Tools and Equipment REFERENCE None specified DESIGNATION Torque wrench, torque range 0−50 pound−inches (0−10 N·m) Subtask 32−11−15−944−001 B. Consumable Materials REFERENCE 04−005 05−001 11−013 16−003 or equivalent DESIGNATION Grease, aircraft and instrument, gear and actuator screw Cloths, cleaning, low−lint Toluene Paint, red Subtask 32−11−15−945−001 C. Parts REF 1 2 3 4 5 7 NAME OF PART Cotter pin Nut Washer Washer Bolt Cross axle pin QTY 2 2 2 2 2 1 IPC SEQUENCE NO. IPC 32−11−00−02−105 IPC 32−11−00−02−100 IPC 32−11−00−02−095 IPC 32−11−00−02−097 IPC 32−11−00−02−090 IPC 32−11−00−02−085 Subtask 32−11−15−946−002 D. Reference Information REFERENCE TASK 07−11−01−582−804 TASK 32−41−01−400−801 TASK 32−44−01−400−801 TASK 32−44−06−740−801 TASK 32−61−20−400−801 TASK 32−61−20−400−802 DESIGNATION Removal of the Aircraft from Jacks Installation of the Main Wheel/Tire Assembly Installation of the Wheel Speed Transducer Antiskid Control Unit (ASCU) System BITE−Test Installation of the MLG Electrical Harness − Outboard Installation of the MLG Electrical Harness − Inboard Master EFFECTIVITY: See Pageblock 32−11−15 page 401 32−11−15 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 2. Job Set−Up Subtask 32−11−15−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Subtask 32−11−15−110−001 B. Use a cloth that is moist with 11−013 solvent to remove any unwanted 04−005 grease from the MLG axle (8) and in the bore of the MLG trailing arm. Subtask 32−11−15−640−001 C. Apply a thin layer of 04−005 grease to the bore of the MLG trailing arm and to the mating surfaces on the MLG axle (8). 3. Procedure Subtask 32−11−15−420−001 Refer to Figure 401. A. Put the MLG axle (8) in the MLG trailing arm. B. Install the cross axle pin (7). Make sure that the two harness holes of the MLG axle (8) align with the harness holes of the MLG trailing arm. C. Align the cross axle pin (7) attachment hole with the attachment hole of the jacking pad (6). Attach the jacking pad (6) and the cross axle pin (7) to the trailing arm with the bolts (5), the washers (4) and (3), and the nuts (2). NOTE: Install washers (3) or (4) as required to correctly torque the nuts (2) and install the cotter pin (1). Remove any washers that are not required Make sure that there is a minimum of one washer under the head of the bolt (5) and one under the nut (2). D. Torque the nuts (2) to 15−20 pound−inches (1.7−2.26 N·m). E. Safety each nut (2) with the cotter pin (1). F. Apply a torque stripe with 16−003 red paint at the nuts (2) and the bolts (4). Subtask 32−11−15−110−002 G. Use a cloth that is moist with 11−013 to remove any unwanted 04−005 grease from the MLG axle (8) and the MLG trailing arm. Make sure that the MLG axle (8) stays correctly lubricated with 04−005 grease. 4. Close Out Subtask 32−11−15−410−001 A. B. Install the electrical harnesses through the MLG axle (Ref. TASK 32−61−20−400−801 or TASK 32−61−20−400−802). Connect the end of the MLG outboard and inboard electrical harnesses to the wheel speed transducer connectors (Ref. TASK 32−61−20−000−801 and TASK 32−61−20−000−802). Master EFFECTIVITY: See Pageblock 32−11−15 page 401 32−11−15 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL C. D. Install the main wheel/tire assemblies and their related axle spacers (Ref. TASK 32−41−01−400−801). Install the wheel speed transducers (Ref. TASK 32−44−01−400−801). Subtask 32−11−15−586−001 E. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−11−15−740−001 F. Do an antiskid−control−unit system BITE−test for the wheel speed transducers (Ref. TASK 32−44−06−740−801). Subtask 32−11−15−941−002 G. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−11−15 page 401 32−11−15 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL AXLE ASSEMBLY, MAIN LANDING GEAR (MLG) − INSPECTION/CHECK 1. General A. The maintenance procedure that follows is for the detailed inspection of the main−landing−gear (MLG) axle assembly. TASK 32−11−15−220−801 Detailed Inspection of the MLG Axle Assembly 1. Reason for the Job Refer to MRB 32−00−00−15. 2. Job Set−Up Information Subtask 32−11−15−946−003 A. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−11−10−000−801 TASK 32−11−10−400−801 TASK 32−11−15−000−801 TASK 32−11−15−400−801 TASK 32−41−01−000−801 TASK 32−41−01−400−801 TASK 32−43−26−000−801 TASK 32−43−26−400−801 TASK 32−61−20−000−801 TASK 32−61−20−400−801 TASK 32−61−20−000−802 TASK 32−61−20−400−802 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Removal of the Trailing Arm Installation of the Trailing Arm Removal of the MLG Axle Installation of the MLG Axle Removal of the Main Wheel/Tire Assembly Installation of the Main Wheel/Tire Assembly Removal of the Brake Unit Installation of the Brake Unit Removal of the MLG Electrical Harness − Outboard Installation of the MLG Electrical Harness − Outboard Removal of the MLG Electrical Harness − Inboard Installation of the MLG Electrical Harness − Inboard Master EFFECTIVITY: See Pageblock 32−11−15 page 601 32−11−15 Page 601 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. Job Set−Up Subtask 32−11−15−941−004 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. Subtask 32−11−15−010−002 B. C. Remove the applicable main wheel/tire assemblies (Ref. TASK 32−41−01−000−801). Remove the applicable brake units (Ref. TASK 32−43−26−000−801). 4. Procedure Subtask 32−11−15−210−001 A. B. Examine the the brake−unit attachment flange of the MLG trailing arm and make sure that the eutectic (overheat) plug has not melted. If the plug is melted, do the steps that follow: (1) Remove the MLG trailing arm and its related axle (Ref. TASK 32−11−10−000−801). (2) Inspect the inboard and the outboard electrical harness for the wheel speed transducers for heat damage. If damage is found, do the steps that follow: (a) Remove and replace (or repair) the applicable outboard electrical harness (Ref. TASK 32−61−20−000−801 and TASK 32−61−20−400−801), or remove and replace (or repair) the applicable inboard electrical harness (Ref. TASK 32−61−20−000−802 and TASK 32−61−20−400−802). (b) Discard (or send to the vendor for inspection/repair) each related wheel speed transducer that was connected to an electrical harness that required repair or replacement. (3) Install a serviceable MLG trailing arm and axle (Ref. TASK 32−11−10−400−801). (4) Send the unserviceable trailing arm and axle to the vendor for inspection/repair. (5) Go to the Close Out section of this procedure. If the MLG trailing arm did not have a melted overheat plug, continue to do the visual inspection of the MLG axle as follows: (1) Examine the MLG axle for: ± Damage ± Security of attachment ± Corrosion ± Discoloration caused by heat. (2) Examine the sealing compound around the edge of the MLG axle and the trailing arm for damage. (3) Examine the threads of the MLG axle for damage. Master EFFECTIVITY: See Pageblock 32−11−15 page 601 32−11−15 Page 602 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL C. On a MLG where you found an axle with discoloration caused by heat, do the steps that follow: (1) Remove the axle (Ref. TASK 32−11−15−000−801). (2) Inspect the related inboard and outboard electrical harnesses for signs of heat damage. (3) If heat damage to the inboard and/or the outboard electrical harness is found, do the steps that follow: (a) Remove and replace (or repair) the applicable outboard electrical harness (Ref. TASK 32−61−20−000−801 and TASK 32−61−20−400−801), or remove and replace (or repair) the applicable inboard electrical harness (Ref. TASK 32−61−20−000−802 and TASK 32−61−20−400−802). (b) Discard (or send to the vendor for inspection) each related wheel speed transducer that was connected to an electrical harness that required repair or replacement. (4) Install a servicable axle (Ref. TASK 32−11−15−400−801). 5. Close Out Subtask 32−11−15−410−002 A. B. Install the applicable brake units (Ref. TASK 32−43−26−400−801). Install the applicable main wheel/tire assemblies (Ref. TASK 32−41−01−400−801). Subtask 32−11−15−941−003 C. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−11−15 page 601 32−11−15 Page 603 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL UPPER BRAKE SWIVEL ASSEMBLY − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the upper swivel assembly of the brake hydraulic system (written as the "swivel assembly" in this procedure. There is one swivel assembly installed on the forward end of each main−landing−gear (MLG) pintle pin. TASK 32−11−20−000−801 Removal of the Upper Brake Swivel Assembly 1. Job Set−Up Information Subtask 32−11−20−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Container, hydraulic fluid − phosphate ester base resistant Subtask 32−11−20−946−001 B. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−802 TASK 12−00−06−863−804 TASK 29−00−00−910−801 TASK 32−45−00−910−802 DESIGNATION Put the Aircraft on Jacks Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − Systems No. 1 and No. 2 Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions Release the Parking Brake 2. Job Set−Up Subtask 32−11−20−941−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. Master EFFECTIVITY: See Pageblock 32−11−20 page 401 401 32−11−20 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−11−20−910−001 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: B. Subtask 32−11−20−582−002 C. Put the aircraft on jacks (Ref. TASK 07−11−01−582−801). Subtask 32−11−20−863−001 D. Release the hydraulic pressure from system No. 2 and system No. 3 (Ref. TASK 12−00−06−863−802 and TASK 12−00−06−863−804). Subtask 32−11−20−910−002 E. If it is set, release the parking brake (Ref. TASK 32−45−00−910−802). Subtask 32−11−20−865−001 F. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 A5 G11 G14 A2 G15 NAME HYD PUMP 3B HYD PUMP 2 HYD SYST AC PUMP CONT 3B HYD SYST AC PUMP CONT 2 HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 221 221 222 222 Subtask 32−11−20−930−001 G. Install a WARNING placard (DO NOT CONNECT THE GROUND HYDRAULIC POWER UNIT) on the No. 2 and the No. 3 ground hydraulic connection points. 3. Procedure Subtask 32−11−20−020−001 Refer to Figure 401. A. Put the hydraulic fluid container below the work area. B. Remove the swivel assembly (1) as follows: (1) Loosen the hydraulic lines (11), (12), (15) and (16) from the swivel assembly (1). (2) Remove and discard the cotter pin (2). (3) Remove the nut (3), the washer (4), and the cross pin (5). (4) Carefully move the swivel assembly (1) and disconnect the hydraulic lines (11), Master EFFECTIVITY: See Pageblock 32−11−20 page 401 402 32−11−20 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (12), (15) and (16). NOTE: Make sure that you identify (tag) the hydraulic lines (11), (12), (13), (14), (15) and (16) so that they will be installed correctly in the installation task. (5) Install protective caps and plugs on all open hydraulic lines and ports. (6) Carefully remove the swivel assembly (1), with the retaining ring (6), from the pintle pin nut. Subtask 32−11−20−030−001 C. Remove the retaining ring (6) from the swivel assembly (1) as follows: (1) From each side of the swivel assembly/retaining ring assembly, remove the cotter pin (7), the nut (8), the washers (9), and the bolt (10). Discard the cotter pins (7). (2) Remove the retaining ring (6) from the swivel assembly (1). Master EFFECTIVITY: See Pageblock 32−11−20 page 401 403 32−11−20 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Swivel assembly. 2. Cotter pin. 3. Nut. 4. Washer. 5. Cross pin. 6. Retaining ring. 7. Cotter pin. 8. Nut. 11 9. Washer. 10. Bolt. 11. Hydraulic line. 12. Hydraulic line. 13. Hydraulic line. 14. Hydraulic line. 15. Hydraulic line. 16. Hydraulic line. A 13 PINTLE PIN NUT (REF) 7 8 9 6 2 4 3 16 5 11 9 10 12 1 ram3211204_001.dg, ds/rm, 25/05/05 13 14 NOTE Left side shown. Right side opposite. 15 A Upper Brake Swivel Assembly − Removal/Installation Figure 401 (Sheet 1 of 2) Master EFFECTIVITY: See Pageblock 32−11−20 page 401 404 32−11−20 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL LEGEND 11. Hydraulic line. 12. Hydraulic line. 13. Hydraulic line. 14. Hydraulic line. 17. Structure channel. 18. Trunnion mount. 19. Structure angle. 20. B−nut. B NOTE Left side shown. Right side opposite. ELECTRICAL CONNECTOR (REF) 17 18 A B D 11 20 12 14 C 19 BD T OU 13 MLG MAIN FITTING (REF) UPPER STRAP (REF) B VIEW LOOKING FORWARD IN LEFT MLG BAY FW D ram3211204_002.dg, rm/lr, 11/05/05 E Upper Brake Swivel Assembly − Removal/Installation Figure 401 (Sheet 2 of 2) Master EFFECTIVITY: See Pageblock 32−11−20 page 401 405 32−11−20 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL TASK 32−11−20−400−801 Installation of the Upper Brake Swivel Assembly 1. Job Set−Up Information Subtask 32−11−20−945−001 A. Parts REF 1 2 3 4 5 6 7 8 9 10 NAME OF PART Swivel assembly Cotter pin Nut Washer Cross pin Retaining ring Cotter pin Nut Washer Bolt QTY 1 1 1 1 1 1 2 2 4 2 IPC SEQUENCE NO. IPC 32−11−00−03−010 IPC 32−11−00−03−075 IPC 32−11−00−03−070 IPC 32−11−00−03−065 IPC 32−11−00−03−060 IPC 32−11−00−03−115 IPC 32−11−00−03−035 IPC 32−11−00−03−030 IPC 32−11−00−03−025 IPC 32−11−00−03−020 Subtask 32−11−20−946−002 B. Reference Information REFERENCE TASK 07−11−01−582−804 TASK 12−00−06−863−802 TASK 12−00−06−863−803 TASK 12−00−06−863−804 TASK 29−10−00−870−802 TASK 29−10−00−870−803 TASK 32−00−00−790−801 TASK 32−12−00−840−801 TASK 32−12−00−800−802 TASK 32−30−00−710−802 TASK 32−43−00−870−801 DESIGNATION Removal of the Aircraft from Jacks Release Hydraulic Pressure − Systems No. 1 and No. 2 Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 Bleed Hydraulic System No. 2 Bleed Hydraulic System No. 3 External Leak Check of the Landing Gear Disconnect the MLG Doors for Maintenance Access Connect the MLG Doors after Maintenance Landing Gear Extension and Retraction − Maintenances Practices Bleeding of the Brakes Master EFFECTIVITY: See Pageblock 32−11−20 page 401 406 32−11−20 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 2. Procedure Subtask 32−11−20−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Subtask 32−11−20−430−001 Refer to Figure 401. B. Install the swivel assembly (1) to the retaining ring (6) as follows: (1) Position the retaining ring (6) against the swivel assembly (1). Align the mounting holes of the swivel assembly with the center of the elongated holes on the retaining ring. (2) On each side of the swivel assembly/retaining ring assembly, install the bolt (10), the washers (9), and the nut (8). Do not fully tighten the nut and do not install the cotter pin (7) at this time. NOTE: Tighten the nuts until the swivel assembly (1) does not turn on the retaining ring. Subtask 32−11−20−820−001 C. Adjust the swivel assembly (1) as follows: (1) Put in position the assembly of the swivel assembly (1) and retaining ring (6) on the pintle pin nut. (2) Turn the swivel assembly/retaining ring assembly together until the connection points for the swivel assembly hydraulic−lines (12) and (14) and the hydraulic lines (11) and (13) on the MLG leg align. (3) Turn the swivel assembly/retaining ring assembly together again, if necessary, to align the retaining ring hole that is nearest to the hole of the pintle pin/nut assembly. (4) Temporarily install the cross pin (5). (5) To align the hydraulic lines (11), (12), (15), and (16) again (for small adjustments), loosen the nuts (8) and turn the swivel assembly (1) on the retaining ring (6). (6) When the hydraulic lines (11), (13), (15), and (16) are aligned, tighten the nuts (8) sufficiently to prevent movement of the swivel assembly (1) against the retaining ring (6). (7) Remove the cross pin (5) and remove the swivel assembly/retaining ring assembly from the aircraft. Make sure that the swivel assembly (1) does not turn on the retaining ring (6) during the removal. NOTE: The swivel assembly is removed for the final torque of the nuts (8), and to install the cotter pins (7). It is easier to do this while the swivel assembly is removed from the aircraft. (8) Tighten the nuts (8) and install the cotter pins (7). Subtask 32−11−20−420−001 D. Install the swivel assembly (1) as follows: (1) Remove the protective caps and plugs from the hydraulic lines (11), (12), (13), and (14) and ports. Master EFFECTIVITY: See Pageblock 32−11−20 page 401 407 32−11−20 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (2) Put the swivel assembly (1) in position again, and align the hydraulic lines (11) and (13) with the hydraulic lines (12) and (14). (3) Align the the hydraulic lignes (15) and (16) with the hydraulic fittings. NOTE: Make sure that the electrical harness stay in position below the hydraulic lines. (4) Tighten by hand the hydraulic lines (11), (12), (13), (14), (15) and (16). (5) Install the cross pin (5), the washer (4), and the nut (3). (6) Safety the nut (3) with the cotter pin (2). CAUTION: MAKE SURE THAT THE HYDRAULIC LINE OF THE BRAKE SWIVEL ASSEMBLY IS CORRECTLY CONNECTED TO ITS RELATED HYDRAULIC LINE FROM THE SWIVEL COUPLING ASSEMBLY. THE INCORRECT INSTALLATION OF THE HYDRAULIC LINES WILL CAUSE THE BRAKES AND/OR THE ANTI−SKID SYSTEM TO OPERATE INCORRECTLY. (7) Torque the hydraulic lines (11), (12), (13), (14), (15) and remove the identification tags that were attached to the hydraulic lines in the removal procedure. 3. Close Out Subtask 32−11−20−865−003 A. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 A5 G11 G14 A2 G15 NAME HYD PUMP 3B HYD PUMP 2 HYD SYST AC PUMP CONT 3B HYD SYST AC PUMP CONT 2 HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 221 221 222 222 Subtask 32−11−20−870−001 B. Bleed hydraulic systems No. 2 and No. 3 (Ref. TASK 29−10−00−870−802 and TASK 29−10−00−870−803). Subtask 32−11−20−870−002 C. Bleed the inboard and outboard brake units for the applicable MLG (Ref. TASK 32−43−00−870−801). Subtask 32−11−20−110−001 D. Clean all remaining hydraulic fluid from the work area. Subtask 32−11−20−220−001 Refer to Figure 401Table 401. Master EFFECTIVITY: See Pageblock 32−11−20 page 401 408 32−11−20 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL Measure the clearance between the upper brake swivel hydraulic Refer to Figure Main landing gear (MLG) lines (11), (12), (13), and (14) . condition and the applicable MLG surround structure that follows: Area A Structure channel (17) During MLG extension and retraction Area B MLG mounting fitting (18) MLG fully retracted Area C Structural angle (19) During MLG extension and retraction Area D and E Between the hydraulic lines (11), MLG fully retracted or fully (12), (13), and (14) and the extended space between the hydraulic fittings (‘B−nuts’) (20) To any electrical connectors and harnesses During MLG extension and retraction Upper Brake Swivel Assembly − Clearance to Components Table 401 E. Required clearance 0.100 in. (2.54 mm) minimum Do a clearance check of the swivel assembly (1) as follows: (1) To get access to the work area, disconnect the applicable MLG door strut from the MLG (Ref. TASK 32−12−00−800−801). (2) Retract the MLG (Ref. TASK 32−30−00−710−802) and make sure that you get a minimum clearance of 0.100 inch (2.54 mm) between the swivel assembly (1) and the components given in Table 401. (3) Extend the MLG (Ref. TASK 32−30−00−710−802) and make sure that you get a minimum clearance of 0.100 inch (2.54 mm) between the swivel assembly (1) and the components given in Table 401. (4) If you do not get the specified clearance, do the adjustment of the swivel assembly (1) again. (5) If the specified clearances between the swivel assembly (1) and the components given in Table 401 are satisfactory, connect the MLG door strut to the MLG (Ref. TASK 32−12−00−800−802). Subtask 32−11−20−210−001 F. Examine the swivel assembly (1) and the hydraulic fittings (‘B−nuts’) (15) for hydraulic leaks (Ref. TASK 32−00−00−790−801). Subtask 32−11−20−869−002 G. Do the steps that follow to make sure that the brake and anti−skid systems operate correctly: (1) On the LDG GEAR control panel, set the ANTI SKID switch to OFF. (2) With hydraulic systems No. 2 and No. 3 still pressurized, apply the brakes and Master EFFECTIVITY: See Pageblock 32−11−20 page 401 409 32−11−20 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (3) (4) (5) (6) (7) (8) (9) (10) make sure that the inboard and outboard brake stacks compress. NOTE: Movement of the wear indicator pins is sufficient to show that the brake stacks compress. Operate the brakes four to six times and hold them momentarily to the applied position to test the swivel assembly assembly for leaks. Release the pressure from hydraulic systems No. 2 and No. 3 (Ref. TASK 12−00−06−863−802 and TASK 12−00−06−863−804). Make sure that the main wheels can be turned freely. Pressurize hydraulic system No. 3 again (Ref. TASK 12−00−06−863−803). Make sure that the brake pressure on the hydraulic synoptic page is 3000±100 psi (20684±689 kPa) for the inboard brake accumulator and that no pressure is shown for the outboard brake accumulator. Make sure that the main wheels can be turned freely. Apply full brake pressure at the pilot’s or the copilot’s brake pedals. Make sure that the two inboard main wheels do not turn and that the two outboard main wheels can still be turned freely. Release the hydraulic pressure from hydraulic system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−11−20−582−001 H. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−11−20−941−002 I. J. Remove the WARNING placard from the No. 2 and the No. 3 ground hydraulic connection points. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−11−20 page 401 410 32−11−20 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL SWIVEL COUPLING ASSEMBLY, MAIN LANDING GEAR (MLG) − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the swivel coupling assembly of the main landing gear (MLG). There are two swivel coupling assemblies installed in the main fitting pin of each MLG. The outboard swivel coupling assembly is pressurized by hydraulic system No. 2. The inboard swivel coupling assembly is pressurized by hydraulic system No. 3. TASK 32−11−25−000−801 Removal of the Swivel Coupling Assembly 1. Job Set−Up Information Subtask 32−11−25−943−001 A. Tools and Equipment REFERENCE None specified None specified None specified DESIGNATION Container, hydraulic fluid Grease pencil Torque wrench, torque range 0−150 pound−inches (0−20 N·m) Subtask 32−11−25−946−001 B. Reference Information REFERENCE TASK 12−00−06−863−802 TASK 12−00−06−863−804 TASK 29−00−00−910−801 TASK 32−61−20−000−801 TASK 32−61−20−000−802 DESIGNATION Release Hydraulic Pressure − Systems No. 1 and No. 2 Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions Removal of the MLG Electrical Harness − Outboard Removal of the MLG Electrical Harness − Inboard Master EFFECTIVITY: See Pageblock 32−11−25 page 401 32−11−25 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 2. Job Set−Up Subtask 32−11−25−910−001 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: A. Subtask 32−11−25−863−001 B. C. If the outboard swivel coupling assembly (3) will be removed, release the pressure from hydraulic system No. 2 (Ref. TASK 12−00−06−863−802). If the inboard swivel coupling assembly (3) will be removed, release the pressure from hydraulic system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−11−25−865−001 D. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 A5 G11 G14 A2 G15 NAME HYD PUMP 3B HYD PUMP 2 HYD SYST AC PUMP CONT 3B HYD SYST AC PUMP CONT 2 HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 221 221 222 222 Subtask 32−11−25−010−001 E. F. Disconnect the MLG electrical harness attachment components, as necessary, from the hydraulic line of the applicable swivel coupling assembly (3) (Ref. TASK 32−61−20−000−801 or TASK 32−61−20−000−802). NOTE: Do not disconnect the electrical harness from its related electrical connectors. Disconnect the clamps (5) of the hydraulic lines from the band clamp bolts (6). NOTE: Make a mark with a grease pencil of the location of each band clamp bolt (6). 3. Procedure Subtask 32−11−25−020−001 Refer to Figure 401. A. Remove the swivel coupling assembly (3) as follows: NOTE: The procedure that follows is applicable to both swivel coupling assemblies. (1) Put the hydraulic fluid container below the work area. CAUTION: DO NOT LET THE HYDRAULIC FLUID TOUCH THE BRAKE UNITS. HYDRAULIC FLUID CAN CAUSE DAMAGE TO THE BRAKE UNITS. (2) Disconnect the hydraulic line of the swivel coupling assembly (3) from the hydraulic Master EFFECTIVITY: See Pageblock 32−11−25 page 401 32−11−25 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (3) (4) (5) (6) (7) (8) line of the upper brake swivel assembly. Install protective caps on all open hydraulic lines. NOTE: Make sure that you identify (tag) the hydraulic lines of the swivel coupling assembly (3) and the hydraulic lines so that they will be installed correctly in the installation task. Disconnect the quick disconnect coupling (1) from the brake unit. Install protective caps/covers on all open hydraulic lines and/or ports. Remove and discard the lockwire from the bolt (2). Remove the bolt (2). Carefully remove the swivel coupling assembly (3) from the main fitting pin (4). Remove and discard the two preformed packings (7). Install a protective plug at the main fitting pin. Subtask 32−11−25−960−001 B. If the quick disconnect coupling (1) that was connected to the brake assembly is not serviceable (leaking, for an example) do the steps that follow: DO NOT LET THE HYDRAULIC FLUID TOUCH THE BRAKE UNITS. CAUTION: HYDRAULIC FLUID CAN CAUSE DAMAGE TO THE BRAKE UNITS. (1) Disconnect the quick disconnect coupling (1) from the rigid pipe that is part of the swivel coupling assembly (3). Make sure that the rigid pipe does not twist when you loosen the quick disconnect coupling (1). NOTE: Be prepared to catch any hydraulic fluid that remains in the swivel coupling assembly (3) in the hydraulic fluid container when you disconnect the quick disconnect coupling (1). (2) Remove and discard the preformed packing (8) from the quick disconnect coupling (1). (3) Lightly lubricate a preformed packing (8) with clean 02−001 hydraulic fluid and install it on a serviceable quick disconnect coupling (1). (4) Install the quick disconnect coupling (1) with its preformed packing (8) on the rigid pipe that is part of the swivel coupling assembly (3). Make sure that the rigid pipe does not twist when you tighten the quick disconnect coupling (1). (5) Torque the quick disconnect coupling (1) to 135−145 pound−inches (15.26−16.38 N·m). Make sure that the rigid pipe does not twist when you torque the quick disconnect coupling (1). (6) Install a protective cover on the quick disconnect coupling (1). Master EFFECTIVITY: See Pageblock 32−11−25 page 401 32−11−25 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 1 BAND CLAMP No. 1 (REF) BAND CLAMP No. 2 (REF) 5 7 MLG MAIN FITTING (REF) 4 2 A 3 6 5 A 5 5 1 11 9 BAND CLAMP No. 3 (REF) 10 TYPICAL AT EACH BAND CLAMP B LEGEND 1. Quick disconnect coupling. 2. Bolt. 3. Swivel coupling assembly. 4. Main fitting pin. 5. Clamp. 6. Clamp bolt. 7. Preformed packing. 8. Preformed packing. 9. Washer. 10. Nut. 11. Cotter pin. 2 8 1 NOTES RIGID BRAKE LINE (REF) B 1 MLG WOW proximity sensor and related components are removed for clarity. 2 MLG wheel assemblies and brake units are removed for clarity. ram3211254_001.dg, gg/yf, 17/11/03 BAND CLAMP No. 4 (REF) Swivel Coupling Assembly − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−11−25 page 401 32−11−25 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−11−25−400−801 Installation of the Swivel Coupling Assembly 1. Job Set−Up Information Subtask 32−11−25−943−002 A. Tools and Equipment REFERENCE None specified None specified DESIGNATION Torque wrench, torque range 0−50 pound−inches (0−10 N·m) Torque wrench, torque range 0−150 pound−inches (0−20 N·m) Subtask 32−11−25−944−001 B. Consumable Materials REFERENCE 02−001 05−005 DESIGNATION Hydraulic fluid, phosphate ester base Lockwire Subtask 32−11−25−945−001 C. Parts REF 1 2 5 7 8 NAME OF PART Coupling, quick disconnect − LH Coupling, quick disconnect − RH Bolt Clamps Preformed packing Preformed packing QTY 1 1 1 5 2 2 IPC SEQUENCE NO. IPC 32−11−00−02−126 IPC 32−11−00−02−142 IPC 32−11−00−02−140 IPC 32−11−00−04−020 IPC 32−11−11−01−020 IPC 32−11−11−01−048 Subtask 32−11−25−946−002 D. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 12−00−06−863−802 TASK 12−00−06−863−804 TASK 12−00−06−863−801 TASK 12−00−06−863−803 TASK 12−20−32−640−802 TASK 29−10−00−870−802 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Release Hydraulic Pressure − Systems No. 1 and No. 2 Release Hydraulic Pressure − System No. 3 Pressurize Hydraulic Systems No. 1 and No. 2 Pressurize Hydraulic System No. 3 Lubrication of the Main Landing Gear Bleed Hydraulic System No. 2 Master EFFECTIVITY: See Pageblock 32−11−25 page 401 32−11−25 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REFERENCE TASK 29−10−00−870−803 TASK 32−43−00−870−801 TASK 32−00−00−790−801 TASK 32−61−05−220−801 TASK 32−61−20−400−801 TASK 32−61−20−400−802 DESIGNATION Bleed Hydraulic System No. 3 Bleeding of the Brakes External Leak Check of the Landing Gear Gap Inspection of the Proximity Sensor Installation of the MLG Electrical Harness − Outboard Installation of the MLG Electrical Harness − Inboard 2. Job Set−Up Subtask 32−11−25−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. 3. Procedure Subtask 32−11−25−420−001 Refer to Figure 401. A. Install the swivel coupling assembly (3) as follows: (1) Remove the protective plug from the main fitting pin (4). (2) Lightly lubricate the preformed packings (7) with clean 02−001 hydraulic fluid. (3) Install the swivel coupling assembly (3) with its preformed packings (7) in the main fitting pin (4). (4) Attach the swivel coupling assembly (3) with the bolt (2). Torque the bolt (2) to 20−25 pound−inches (2.26−2.83 N·m). (5) Safety the bolt (2) with 05−005 lockwire. (6) Remove the protective cap from the hydraulic line of the upper brake swivel assembly. (7) Remove the protective caps/covers from the upper hydraulic line of the swivel coupling assembly (3) and also the quick disconnect coupling (1). CAUTION: MAKE SURE THAT THE HYDRAULIC LINE OF THE BRAKE SWIVEL ASSEMBLY IS CORRECTLY CONNECTED TO ITS RELATED HYDRAULIC LINE FROM THE SWIVEL COUPLING ASSEMBLY. THE INCORRECT INSTALLATION OF THE HYDRAULIC LINES WILL CAUSE THE BRAKES AND/OR THE ANTI−SKID SYSTEM TO OPERATE INCORRECTLY. (8) Connect the fitting on the hydraulic line of the upper brake swivel assembly to the fitting on the hydraulic line of the swivel coupling assembly (3) and remove the identification tags that were attached to the hydraulic lines in the removal procedure. (9) Torque the hydraulic fittings from 135 to 145 pound−inches (15.26 to 16.38 N·m). Master EFFECTIVITY: See Pageblock 32−11−25 page 401 32−11−25 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (10) Connect the quick disconnect coupling (1) to its related quick disconnect coupling on the brake unit. 4. Close Out Subtask 32−11−25−410−001 A. B. Attach the hydraulic line of the swivel coupling assembly (3) to the band clamp bolts (6) with the clamps (5), the washer (10), the nut (11), the cotter pin (12) and the MLG electrical harness attachment components (Ref. TASK 32−61−20−400−801 or TASK 32−61−20−400−802). Make sure that the MLG weight on wheels (WOW) proximity sensor is installed and adjusted correctly (Ref. TASK 32−61−05−400−803). Make sure that the clearance between the components that follow is a minimum of 0.100 inch (2.54 mm) from the MLG surround structure and from any electrical connector or harness: ± the hydraulic lines of the upper brake swivel assembly ± the rigid hydraulic lines of the swivel coupling assembly ± the space between the related hydraulic fittings (‘B−nuts’). Subtask 32−11−25−865−002 C. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 A5 G11 G14 A2 G15 NAME HYD PUMP 3B HYD PUMP 2 HYD SYST AC PUMP CONT 3B HYD SYST AC PUMP CONT 2 HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 221 221 222 222 Subtask 32−11−25−870−001 D. E. For the outboard swivel coupling assembly (3), bleed hydraulic system No. 2 (Ref. TASK 29−10−00−870−802). For the inboard swivel coupling assembly (3), bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−11−25−870−002 F. Bleed the inboard or outboard brakes, as applicable (Ref. TASK 32−43−00−870−801). Subtask 32−11−25−210−001 G. Examine the swivel coupling assembly (3) and the fittings on the hydraulic lines of the upper brake swivel assembly for leaks (Ref. TASK 32−00−00−790−801). Master EFFECTIVITY: See Pageblock 32−11−25 page 401 32−11−25 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−11−25−863−003 H. I. For the outboard swivel coupling assembly (3), pressurize hydraulic system No. 2 (Ref. TASK 12−00−06−863−801). For the inboard swivel coupling assembly (3), pressurize hydraulic system No. 3 (Ref. TASK 12−00−06−863−803). Subtask 32−11−25−869−002 J. Do the steps that follow to make sure that the brake and anti−skid systems operate correctly: (1) On the LDG GEAR control panel, set the ANTI SKID switch to OFF. (2) With hydraulic systems No. 2 and No. 3 pressurized, apply the brakes and make sure that the inboard and outboard brake stacks compress. NOTE: Movement of the wear indicator pins is sufficient to show that the brake stacks compress. Operate the brakes four to six times and hold them momentarily to the applied position to test the swivel assembly assembly for leaks. (3) Release the pressure from hydraulic systems No. 2 and No. 3 (Ref. TASK 12−00−06−863−802 and TASK 12−00−06−863−804). (4) Put the aircraft on jacks (Ref. TASK 07−11−01−582−801). Make sure that the main wheels can be turned freely. (5) Pressurize hydraulic system No. 3 again (Ref. TASK 12−00−06−863−803). (6) Make sure that the brake pressure on the hydraulic synoptic page is 3000±100 psi (20684±689 kPa) for the inboard brake accumulator and that no pressure is shown for the outboard brake accumulator. (7) Make sure that the main wheels can be turned freely. (8) Apply full brake pressure at the pilot’s or the copilot’s brake pedals. (9) Make sure that the two inboard main wheels do not turn and that the two outboard main wheels can still be turned freely. (10) Release the hydraulic pressure from hydraulic system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−11−25−640−001 K. Apply grease with a grease gun to the grease fitting on the swivel coupling assembly (3) until new grease can be seen (Ref. TASK 12−20−32−640−802). Subtask 32−11−25−941−002 L. Remove the fluid container from below the work area. Subtask 32−11−25−586−001 M. Lower the aircraft and remove from jacks (Ref . TASK 07−11−01−582−804). Master EFFECTIVITY: See Pageblock 32−11−25 page 401 32−11−25 Page 408 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−11−25−941−003 N. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−11−25 page 401 32−11−25 Page 409 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL MAIN DOOR AND MECHANISM SYSTEM − DESCRIPTION AND OPERATION 1. 2. 3. General A. The aircraft has two main door and mechanism systems. The main door and mechanism system gives the aircraft a smooth surface when each main landing gear (MLG) is retracted. B. Each main door and mechanism system has the components that follow: ± One MLG door assembly ± One door brush ± One push/pull rod ± One bellcrank assembly ± One end rod. Component Details Refer to Figure 1. A. MLG Door Assembly (1) The MLG door assembly is hinged on the wing structure and is opened or closed by a mechanical mechanism attached to the MLG. When retracted, the MLG door assembly makes a smooth surface with the aircraft. The outboard main−wheel/tire assembly of each MLG is not covered by the MLG door assembly. B. Door Brush (1) The door brush is installed on the bottom edge of the MLG door assembly and is used to prevent damage of the MLG. It also makes a smooth surface when the MLG is retracted. The door brush is made of nylon. C. Push/Pull Rod (1) The push/pull rod is installed between the hinged point of the fuselage and the bellcrank assembly. The push/pull rod transmits a mechanical force from the retraction or extension of each MLG to the bellcrank assembly. D. Bellcrank Assembly (1) The bellcrank assembly is installed on the MLG by a pivot joint. It transmits a mechanical force from the push/pull rod to the end rod during the extension or retraction of the MLG. E. End Rod (1) The end rod is installed on the MLG−door−assembly pivot fitting and is attached to the bellcrank assembly. It pushes open or pulls closed the MLG door assembly during a retraction or extension of the MLG. Operation Refer to Figure 1. A. When the MLG extends, it makes the bellcrank assembly turn, which pushes the end rod and pulls the push/pull rod. The end rod pushes and opens the MLG door assembly. When the MLG retracts, it makes the bellcrank assembly turn, which pulls the end rod and pushes the push/pull rod. The end rod pulls and closes the MLG door assembly. At the same time, the push/pull rod makes the bellcrank assembly and the end rod engage Master EFFECTIVITY: See Pageblock 32−12−00 page 1 32−12−00 Page 1 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 4. correctly. This action prevents damage to the MLG when the MLG door assembly is fully closed. Component Location Index Refer to Figure 1. COMPONENT NAME Bellcrank assembly Door brush End rod Push/pull rod MLG door assembly QTY 2 2 2 2 2 Master EFFECTIVITY: See Pageblock 32−12−00 page 1 ACCESS/ZONE 732/742 732/742 732/742 732/742 732/742 REFERENCE 32−12−15 32−12−05 32−12−20 32−12−10 32−12−01 32−12−00 Page 2 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL PUSH/PULL ROD MLG DOOR ASSEMBLY BELL CRANK ASSEMBLY DOOR BRUSH FWD ram3212000_001(1).dc, mb/pb, 01/12/93 END ROD Main Door and Mechanism System − Component Location/Recognition Figure 1 Master EFFECTIVITY: See Pageblock 32−12−00 page 1 32−12−00 Page 3 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL MAIN DOOR AND MECHANISM SYSTEM − MAINTENANCE PRACTICES 1. General A. The maintenance tasks that follow give the procedures to disconnect the main landing gear (MLG) door from the MLG for maintenance access when the MLG is retracted and also to connect the MLG door to the MLG again after the maintenance task is completed. B. The procedures given are for the MLG door on the right side of the aircraft. The procedures for the MLG door on the left side of the aircraft are the same. TASK 32−12−00−800−801 Disconnect the MLG Door for Maintenance Access 1. Job Set−Up Information Subtask 32−12−00−944−001 A. Consumable Materials REFERENCE 05−044 DESIGNATION Tape, water−proof, duct Subtask 32−12−00−946−001 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins 2. Job Set−Up Subtask 32−12−00−490−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Make sure that the safety lockpins are installed at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. 3. Procedure Subtask 32−12−00−910−001 Refer to Figure 201. Master EFFECTIVITY: See Pageblock 32−12−00 page 201 32−12−00 Page 201 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A. Disconnect the MLG door from the MLG for maintenance access as follows: NOTE: The removal procedure for the door strut of the right and left gear is the same. (1) Remove and discard the cotter pin (1) from the nut (2). (2) Remove the nut (2), the washer (3), and the bolt (4) with the clamp−up bushing (5). (3) Remove the door strut (6) from the bellcrank assembly (7). CAUTION: IF THE MLG WILL BE RETRACTED OR EXTENDED WITH THE MLG DOOR DISCONNECTED, MAKE SURE THAT THE MLG DOOR AND THE DOOR STRUT IS HELD CLEAR OF THE MLG. DAMAGE TO THE AIRCRAFT CAN OCCUR. MAKE SURE THAT THE BELLCRANK ASSEMBLY IS ROTATED CAUTION: OVERCENTER TO THE CORRECT POSITION. IF IT IS NOT IN THE CORRECT POSITION, DAMAGE TO AIRCRAFT CAN OCCUR. B. If the MLG will move during the maintenance task, do the steps that follow: (1) Temporarily attach the MLG door to the aircraft structure with 05−044 duct tape to keep the MLG door in the open position and clear of the MLG. (2) Secure the door strut (6) to the MLG door with 05−044 duct tape. Master EFFECTIVITY: See Pageblock 32−12−00 page 201 202 32−12−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL A LEGEND 1. Cotter pin. 2. Nut. 3. Washer. 4. Bolt. 5. Clamp−up bushing. 6. Door strut. 7. Bell crank assembly. B MLG DOOR (REF) 6 A 4 5 3 1 NOTE Right equipment shown, left equipment opposite. 2 B ram3212002_001.dg, rm/cc, 13/05/05 7 Prepare the MLG Door for Access when the MLG is Retracted Figure 201 Master EFFECTIVITY: See Pageblock 32−12−00 page 201 203 32−12−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL TASK 32−12−00−800−802 Connect the MLG Door after Maintenance 1. Job Set−Up Information Subtask 32−12−00−945−001 A. Parts REF 1 2 3 4 5 NAME OF PART Cotter pin Nut Washer Bolt Bushing, clamp−up QTY 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−12−00−01−041 IPC 32−12−00−01−040 IPC 32−12−00−01−035 IPC 32−12−00−01−030 IPC 32−12−00−01−140 Subtask 32−12−00−946−002 B. Reference Information REFERENCE TASK 32−12−10−400−801 TASK 32−12−15−400−801 DESIGNATION Installation of the Push/Pull Rod Installation of the Bellcrank Assembly 2. Job Set−Up Subtask 32−12−00−840−001 A. If the MLG was extended or retracted during the maintenance task, do the steps that follow: (1) Remove the 05−044 duct tape that was used to temporarily keep the MLG door in the open position. (2) Remove the 05−044 duct tape that was used to temporarily attach the MLG door strut (6) to the MLG door. 3. Procedure Subtask 32−12−00−910−002 Refer to Figure 201. A. After maintenance to the MLG has been completed, do the steps that follow: NOTE: The installation procedure for the door strut of the right and left gear is the same. CAUTION: MAKE SURE THAT THE BELLCRANK ASSEMBLY IS ROTATED OVERCENTER TO THE CORRECT POSITION. IF IT IS NOT IN THE CORRECT POSITION, DAMAGE TO AIRCRAFT CAN OCCUR. (1) If the bellcrank assembly (7) or the push/pull rod for the MLG door was removed or adjusted during maintenance, make sure that the belcrank assembly (7) was rotated to the correct overcenter position before you attach the door strut (6) to the Master EFFECTIVITY: See Pageblock 32−12−00 page 201 32−12−00 Page 204 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (2) (3) (4) (5) bellcrank assembly (7) (Ref. TASK 32−12−10−400−801 or TASK 32−12−15−400−801). Align the end of the door strut (6) with its related attachment point on the bellcrank assembly (7). Insert the bolt (4) in the aft side of the bellcrank assembly (7). Make sure that the clamp−up bushing (5) is installed correctly in the bellcrank assembly (7). Install the washer (3), and the nut (2). Tighten the nut (2). Safety the nut (2) with the cotter pin (1). 4. Close Out Subtask 32−12−00−941−001 A. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−12−00 page 201 32−12−00 Page 205 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL DOORS, MAIN LANDING GEAR − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the main landing gear doors (written as the "doors" in this procedure). Each door is installed on the wing structure and is attached to the main landing gear. TASK 32−12−01−000−801 Removal of the Main Landing Gear Doors 1. Job Set−Up Information Subtask 32−12−01−946−001 A. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−12−05−000−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Removal of the Door Brush 2. Job Set−Up Subtask 32−12−01−490−003 WARNING: A. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). 3. Procedure Subtask 32−12−01−020−001 Refer to Figure 401. A. Remove the door (1) as follows: NOTE: The removal procedure for the door of the left and right main landing gears is the same. (1) Remove the nut (2), the washers (3) and (4), and the bolt (5). Disconnect the bonding cable (6) from the door (1). (2) Remove and discard the cotter pin (7) from the rod end bolt (10). (3) Remove the nut (8), the washer (9), and the bolt (10). Disconnect the rod end (11) from the door (1). (4) Remove and discard the cotter pins (12) from the door hinge pins (20). Master EFFECTIVITY: See Pageblock 32−12−01 page 401 32−12−01 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (5) Remove the nuts (14), the washers (15), (16), (17), (18), and (19), and the pin (20). NOTE: It is possible that there are more than two shim washers (16) and (19) for each hinge assembly. Discard the shim washers (16) and (19). (6) Remove the door (1). (7) If you replace the door, remove the door brush (21) (Ref. TASK 32−12−05−000−801). Master EFFECTIVITY: See Pageblock 32−12−01 page 401 32−12−01 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL NOTE Right equipment shown, left equipment opposite. 21 LEGEND 1. Door. 2. Nut. 3. Washer. 4. Washer. 5. Bolt. 6. Bonding cable. 7. Cotter pin. 8. Nut. 9. Washer. 10. Bolt. 11. Rod end. 12. Cotter pin. 13. Door hinge. 14. Nut. 15. Washer. 16. Shim washer. 17. Washer. 18. Washer. 19. Shim washer. 20. Pin. 21. Door brush. 15 7 17 19 18 2 16 6 13 9 8 5 1 3 4 ram3212014_001.dg, rm/yf, 14/10/04 11 12 20 10 14 Main Landing Gear Door − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−12−01 page 401 403 32−12−01 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−12−01−400−801 Installation of the Main Landing Gear Doors 1. Job Set−Up Information Subtask 32−12−01−945−001 A. Parts REF 2 3 4 5 7 8 9 10 12 14 15 16 17 18 19 20 NAME OF PART Nut Washer Washer Bolt Cotter pin Nut Washer Bolt Cotter pin Nut Washer Washer, shim Washer Washer Washer, shim Pin QTY 1 1 1 1 1 1 1 1 2 2 1 A/R 1 1 A/R 2 IPC SEQUENCE NO. IPC 32−12−00−01−395 IPC 32−12−00−01−390 IPC 32−12−00−01−390 IPC 32−12−00−01−385 IPC 32−12−00−01−041 IPC 32−12−00−01−025 IPC 32−12−00−01−020 IPC 32−12−00−01−015 IPC 32−12−00−01−335 IPC 32−12−00−01−330 IPC 32−12−00−01−325 IPC 32−12−00−01−315 IPC 32−12−00−01−320 IPC 32−12−00−01−320 IPC 32−12−00−01−315 IPC 32−12−00−01−310 Subtask 32−12−01−946−002 B. Reference Information REFERENCE TASK 32−12−01−820−801 TASK 32−12−05−400−801 DESIGNATION Adjustment of the Main Landing Gear Doors Installation of the Door Brush 2. Procedure Subtask 32−12−01−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Subtask 32−12−01−420−001 Refer to Figure 401. B. Install the door (1) as follows: NOTE: The installation procedure for the door of the left and right main landing gears is the same. Master EFFECTIVITY: See Pageblock 32−12−01 page 401 32−12−01 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (1) If necessary, install the door brush on the door (1) (Ref. TASK 32−12−05−400−801). (2) Align the door hinges (13) and install the pins (20), the washers (19), (18), (17), (16), and (15), and the nuts (14). NOTE: If necessary, install more than one shim washer (16) and/or (19) on the inner sides of each door hinge (13). (3) Torque the nuts (14) to 20 pound−inches (2.26 N·m). (4) Measure the lateral travel of the door (1) with the feeler gauge. (5) Make sure that the lateral travel is between 0.010−0.020 inch (0.25−0.50 mm). If necessary, add more shim washers (16) and/or (19) to adjust the lateral travel. (6) Safety the nuts (14) with the cotter pins (12). (7) Attach the rod end (11) to the door (1) with the bolt (10), the washer (9), and the nut (8). (8) Safety the nut (8) with the cotter pin (7). (9) Attach the bonding cable (6) to the door (1) with the bolt (5), the washers (4) and (3), and the nut (2). 3. Close Out Subtask 32−12−01−820−001 A. Do an adjustment of the doors (Ref. TASK 32−12−01−820−801). Master EFFECTIVITY: See Pageblock 32−12−01 page 401 32−12−01 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL DOORS, MAIN LANDING GEAR − ADJUSTMENT/TEST 1. General A. The maintenance procedure that follows is for the operational test and adjustment of the main landing gear (MLG) doors. TASK 32−12−01−710−801 Operational Test of the Main Landing Gear Doors 1. Job Set−Up Information Subtask 32−12−01−946−005 A. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 10−11−00−000−802 TASK 10−11−00−400−802 TASK 12−00−06−863−803 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Removal of the Main Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Pressurize Hydraulic System No. 3 2. Job Set−Up Subtask 32−12−01−582−005 A. Put the aircraft on jacks (Ref. TASK 07−11−01−582−801). Make sure that there is a distance of 4 inches (10 cm) between the ground and the nose and main wheel/tire assemblies. Subtask 32−12−01−865−005 B. Make sure that the circuit breakers that follow are closed: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−4 CB NO. F6 F7 F9 P2 P3 B13 NAME LGC/D1 WOW 1 WOW 2 LGC/D1 LGC/D2 WOW 1 + 2 LGC/D2 ZONE 221 221 222 222 222 222 Subtask 32−12−01−090−007 C. Remove the MLG safety lockpins (Ref. TASK 10−11−00−000−802). Master EFFECTIVITY: See Pageblock 32−12−01 page 501 32−12−01 Page 501 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−12−01−863−005 D. Pressurize hydraulic system No. 3 (Ref. TASK 12−00−06−863−803). 3. Procedure Subtask 32−12−01−867−005 A. B. C. Put the landing−gear selector handle on the center pedestal to the "UP" position. Make sure that the landing gear retracts. When the MLG doors are closed, make sure that the doors make a smooth surface with the aircraft skin contour. Put the landing−gear selector handle on the center pedestal to the DN position. Make sure that the landing gear extends and locks down. 4. Close Out Subtask 32−12−01−490−001 A. Install the MLG safety lockpins (Ref. TASK 10−11−00−400−802). Subtask 32−12−01−586−005 B. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Master EFFECTIVITY: See Pageblock 32−12−01 page 501 32−12−01 Page 502 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−12−01−820−801 Adjustment of the Main Landing Gear Doors 1. Job Set−Up Information Subtask 32−12−01−943−006 A. Tools and Equipment REFERENCE TE−0709 (or equivalent) None specified None specified None specified DESIGNATION Stand, hydraulic test Container, hydraulic fluid Straight edge Feeler gauge Subtask 32−12−01−944−002 B. Consumable Materials REFERENCE 05−004 DESIGNATION Lockwire Subtask 32−12−01−945−002 C. Parts REF 2 3 4 5 6 8 9 12 13 14 15 16 17 20 22 23 24 25 NAME OF PART Cotter pin Nut Washer Bolt Bushing Bolt Nut Jam nut Tab washer Jam nut Tab washer nut Washer Laminated shim Wedge Laminated shim Screw Screw Master EFFECTIVITY: See Pageblock 32−12−01 page 501 QTY 1 1 1 1 1 4 4 1 1 1 1 6 AR 2 1 1 1 1 IPC SEQUENCE NO. IPC 32−12−00−01−041 IPC 32−12−00−01−025 IPC 32−12−00−01−020 IPC 32−12−00−01−015 IPC 32−12−00−01−100 IPC 32−12−00−01−240 IPC 32−12−00−01−250 IPC 32−12−00−01−070 IPC 32−12−00−01−080 IPC 32−12−00−01−085 IPC 32−12−00−01−075 IPC 32−12−00−01−420 IPC 32−12−00−01−415 IPC 32−12−00−01−440 IPC 57−20−00−01−385 IPC 57−20−00−01−397 IPC 57−20−00−01−390 IPC 57−20−00−01−395 32−12−01 Page 503 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−12−01−946−006 D. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 10−11−00−000−801 TASK 10−11−00−000−802 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 29−00−00−910−801 TASK 29−10−00−870−803 TASK 32−12−01−710−801 TASK 53−83−01−000−801 TASK 53−83−01−400−801 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Removal of the Nose Landing Gear Lockpin Removal of the Main Landing Gear Lockpins Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions Bleed Hydraulic System No. 3 Operational Test of the Main Landing Gear Doors Removal of the MLG Wheel Bin Installation of the MLG Wheel Bin 2. Job Set−Up Subtask 32−12−01−910−006 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: A. Subtask 32−12−01−490−002 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: B. Subtask 32−12−01−863−007 C. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−12−01−582−006 D. Put the aircraft on jacks (Ref. TASK 07−11−01−582−801). Make sure that there is a distance of 4 inches (10 cm) between the ground and the nose and main wheel/tire assemblies. Master EFFECTIVITY: See Pageblock 32−12−01 page 501 32−12−01 Page 504 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−12−01−010−006 E. Remove the applicable MLG wheel bin (Ref. TASK 53−83−01−000−801). Subtask 32−12−01−030−001 Refer to Figure 502 F. Disconnect the MLG door from the MLG as follows: (1) Remove and discard the cotter pin (2). (2) Remove the nut (3) and the washer (4) from the bolt (5). (3) Remove the bolt (5) from the rod end of the door strut (1). (4) Remove the clamp−up bushing (6) from the rod end of the door strut (1). Subtask 32−12−01−840−001 Refer to Figure 501. WHEN THE GROUND−HYDRAULIC POWER UNIT IS USED TO PRESSURIZE CAUTION: THE HYDRAULIC SYSTEM, DO NOT OPERATE THE AIRCRAFT HYDRAULIC PUMPS ON THAT SAME SYSTEM. YOU CAN CAUSE DAMAGE TO THE SYSTEM. G. Connect the hydraulic test stand as follows: (1) Put a hydraulic fluid container below the MLG selector valve in the MLG bay at FS 552, RBL 2. (2) Disconnect the "UP" and "DOWN" hydraulic lines from the MLG selector valve. Install protective caps on the "UP" and "DOWN" ports of the MLG selector valve. (3) Install protective caps on the disconnected "UP" and "DOWN" hydraulic lines. (4) Connect line No. 1 of the hydraulic test stand to the MLG "UP" line. (5) Connect line No. 2 of the hydraulic test stand to the "DOWN" line. (6) Set the pressure to the "DOWN" line of the hydraulic test stand (line No. 2). (7) Slowly pressurize line No. 2 from the hydraulic test stand to approximately 200 psig (1380 kPa). WARNING: MAKE SURE THAT YOU BLEED THE HYDRAULIC LINES OF ANY AIR THAT IS CAUGHT IN THEM. IF YOU DO NOT DO THIS, THE LANDING GEAR CAN DROP SUDDENLY WHEN IT IS RELEASED FROM THE UPLOCK. (8) Slowly loosen the hydraulic connections of the "DOWN" lines (one at a time) to bleed the lines of any air. Tighten the hydraulic connections. (9) Release the hydraulic pressure from line No. 2. (10) Set the pressure to the "UP" line of the hydraulic test stand (line No. 1). (11) Slowly pressurize line No. 1 from the hydraulic test stand to approximately 200 psig (1380 kPa). Master EFFECTIVITY: See Pageblock 32−12−01 page 501 32−12−01 Page 505 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL WARNING: MAKE SURE THAT YOU BLEED THE HYDRAULIC LINES OF ANY AIR THAT IS CAUGHT IN THEM. IF YOU DO NOT DO THIS, THE LANDING GEAR CAN DROP SUDDENLY WHEN IT IS RELEASED FROM THE UPLOCK. (12) Slowly loosen the hydraulic connections of the "UP" lines (one at a time) to bleed the lines of any air. Tighten the hydraulic connections. (13) Release the hydraulic pressure from line No. 1. 3. Procedure Subtask 32−12−01−820−006 Refer to Figure 502 A. Do the steps that follow to adjust the over center distance between the push/pull rod and the bellcrank assembly of the MLG door operating−mechanism: (1) Measure the horizontal distance between the bellcrank pivot pin and the push/pull rod attachment−point (7) at the bellcrank. Make sure that there is a minimum over center distance of 1.1 inches (27.9 mm). (2) If a minimum over center distance of 1.1 inches (27.9 mm) is correct, temporarily connect the rod end of the door strut (1) to the MLG door with the bolt (5) and the clamp−up bushing (6) and then go to the next step (the basic adjustment of the length of the door strut (1)). (3) If a minimum over center distance of 1.1 inches (27.9 mm) is not obtained, do the steps that follow: (a) Loosen the four bolts (8) and the nuts (9) of the upper pivot fitting slightly until you can move the upper pivot fitting up or down on the serrated plate (10). (b) Move the upper pivot fitting up or down to adjust the overcenter distance to a minimum of 1.1 inches (27.94 mm). (c) Hold the upper pivot fitting in position on the serrated plate (10) and tighten the four bolts (8) and the nuts (9). Make sure that the serrated surfaces of the upper pivot fitting and the serrated plate (10) are engaged correctly. (d) Do the these steps again, if required, until the correct dimension is obtained. (e) Temporarily connect the rod end of the door strut (1) to the MLG door with the bolt (5) and the clamp−up bushing (6). B. Do the steps that follow to do the basic adjustment of the length of the door strut (1): (1) Measure the distance between the strut−to−bellcrank attachment point (11) and the point that the rod end of the door strut (1) attaches to the MLG door. If a measurement of 13.10 inches (332.7 mm) is not obtained, do the steps that follow: NOTE: If the measurement is correct, go to the last step in this subtask. (a) Remove and discard the lockwire from the jam nut (12). (b) Bend the locking tab of the tab washer (13) that is bent against the jam nut (14) to allow adjustment of the jam nut (14). NOTE: It is not necessary to bend the locking tab on the tab washer (15) that is bent against the door strut (1). Master EFFECTIVITY: See Pageblock 32−12−01 page 501 32−12−01 Page 506 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (c) Loosen the jam nuts (12) and (14). (d) Turn the jam nuts (12) and (14) as required to adjust the the rod end to get a distance of 13.10 inches (332.7 mm). (e) Tighten the jam nuts (12) and (14). Do not safety the jam nuts at this time. (f) Remove the bolt (5) and the clamp−up bushing (6) from the rod end of the door strut (1). Subtask 32−12−01−090−008 C. Remove the applicable MLG safety lockpin (Ref. TASK 10−11−00−000−802). Subtask 32−12−01−980−001 BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. CAUTION: MAKE SURE THAT THE CONTROL RODS WILL NOT CATCH THE GEAR OR SURROUNDING AREA WHEN THE LANDING GEAR IS OPERATED. DAMAGE TO THE AIRCRAFT CAN OCCUR. D. Set the pressure to the "UP" line of the hydraulic test stand (line No. 1). E. Slowly pressurize line No. 1 from the hydraulic test stand until the MLG downlock releases (monitor the downlock port in the actuator end housing to confirm). NOTE: The downlock will release between 450 and 1000 psig (3100 and 6895 kPa). F. Continue to retract the main landing gear until it is up and locked. NOTE: With the MLG door disconnected, the MLG uplock latch will lock at a pressure of between 1200 and 1800 psig (8274 and 12411 kPa). G. Release the hydraulic pressure from line No. 1. WARNING: Subtask 32−12−01−820−007 Refer to Figure 502 H. Do this subtask only if a new MLG door was installed. NOTE: No adjustment is required to the door hinge fittings (18) if the MLG door has not been changed in service. I. Do the steps that follow to adjust the MLG door clearance and mismatch at the outboard edge (ZONE C) of the MLG door: (1) With the MLG fully retracted and locked, manually close the MLG door by hand and hold it in the closed position. (2) Measure the clearance between the outboard edge of the MLG door and the adjacent wing lower skin (ZONE C). Make sure that the clearance between the wing lower skin and the MLG door is 0.030−0.090 inch (0.76−2.3 mm). If you do not obtain the required clearance, do the steps that follow: (a) Lower the MLG door. (b) Remove the nuts (16), the washers (17), the door hinge fitting (18), and the Master EFFECTIVITY: See Pageblock 32−12−01 page 501 32−12−01 Page 507 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL J. K. L. serrated plate (19). NOTE: Keep the nuts (16) that are removed so that they can be used temporarily in the steps below. (c) Add or remove laminated shims (20) as required to get the 0.030−0.090 inch (0.76−2.3 mm) maximum dimension at the outboard edge of the MLG door. NOTE: Make sure that the laminated shim thickness does not exceed 0.125 inch (3.18 mm). (d) Temporarily install the serrated plate (19) the door hinge fitting (18) and the washers (17) with the nuts (16) that were removed. Make sure that the serrated surfaces of the door hinge fitting (18) and the serrated plate (19) are engaged correctly. (e) Manually close the MLG door by hand and make sure that the clearance is acceptable. If the clearance is satisfactory at the MLG door outboard edge (ZONE C), make sure that the MLG door mismatch is satisfactory at the MLG door outboard edge (ZONE C) as follows: (1) Put a straight−edge across the MLG door and the wing lower surface and use a feeler gauge to check that there is a 0±0.040 inch (0±1 mm) maximum mismatch along the outboard edge of the door−to−wing lower skin. (2) If the mismatch of the MLG door−to−wing surface is not within the limits given, do the steps that follow: (a) Lower the MLG door. (b) Loosen the nuts (16) slightly until the door hinge fitting (18) can move up and down on the serrated plate (19). (c) Adjust the door hinge fitting (18) up or down on the serrated plate (19) until the surfaces are flush within the limits given. (d) Hold the door hinge fitting (18) in position on the serrated plate (19) and tighten the nuts (16). Make sure that the serrated surfaces of the door hinge fitting (18) and the serrated plate (19) are engaged correctly. (e) Manually close the MLG door by hand and make sure that the mismatch is acceptable. If the mismatch is satisfactory, do a check of the alignment of the roller (21) and the wedge (22). The roller (21) must be in contact with a minimum of 80% of the width of the wedge (22) when the door is correctly adjusted. NOTE: If the roller (21) is not in contact with a minimum of 80% of the width of the wedge (22), it is possible that you will need to do the adjustment steps given in this subtask again. If the clearance, mismatch, and roller/wedge alignment is satisfactory in ZONE C, do the steps that follow: (1) Lower the MLG door. (2) Remove and discard each of the temporarily installed nuts (16) (one at a time) and replace it with a serviceable one. Tighten each nut (16) as it is installed. (3) Torque the nuts (16) from 50 to 70 lbf·in (5.65 to 7.91 N·m). Master EFFECTIVITY: See Pageblock 32−12−01 page 501 32−12−01 Page 508 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−12−01−980−002 M. Do the steps that follow to prepare the aircraft for the final adjustment of the MLG door: (1) Set the pressure to the "DOWN" line of the hydraulic test stand (line No. 2). WARNING: BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. CAUTION: MAKE SURE THAT THE CONTROL RODS WILL NOT CATCH THE GEAR OR SURROUNDING AREA WHEN THE LANDING GEAR IS OPERATED. DAMAGE TO THE AIRCRAFT CAN OCCUR. (2) Slowly pressurize line No. 2 from the hydraulic test stand until the MLG uplock releases. NOTE: The MLG uplock latch will release between 350 and 550 psig (2413 and 3792 kPa). (3) Adjust the pressure to 600 psig (4137 kpa) and fully extend the landing gear. Make sure that the landing gear is down and that the MLG downlock is locked. (4) Install the applicable MLG safety lockpin (Ref. TASK 10−11−00−400−802). (5) Release the hydraulic pressure from line No. 2. (6) Temporarily attach the rod end of the door strut (1) to the MLG door with the bolt (5) and the clamp−up bushing (6). (7) Remove the applicable MLG safety lockpin (Ref. TASK 10−11−00−000−802). WARNING: BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. (8) Retract the applicable MLG as follows: (a) Set the pressure to the "UP" line of the hydraulic test stand (line No. 1). (b) Slowly pressurize line No. 1 from the hydraulic test stand to retract the MLG until it is approximately 2 inches (50 mm) from the MLG uplock latch. NOTE: Make sure that the MLG door will close correctly against the adjacent structure when the MLG uplock latches. If necessary, adjust the door strut (1) to make sure that there will be enough clearance. One turn of the jam nuts (12) and (14) on the rod end is approximately equal to 0.070 inch (1.78 mm) travel at the inboard end of the MLG door. (c) Slowly increase the pressure to retract the main landing gear until it is up and locked. NOTE: With the MLG door installed, the MLG uplock latch will lock at a maximum pressure of 2200 psig (15168 kPa). Subtask 32−12−01−820−008 Refer to Figure 502 Master EFFECTIVITY: See Pageblock 32−12−01 page 501 32−12−01 Page 509 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL N. O. Do the steps that follow to adjust the wedge (22) at the MLG door roller (21) (ZONE B): (1) With the MLG fully retracted and locked, make sure that the roller (21) installed on the aft edge of the MLG door lightly touches the wedge (22). Make sure that the aft edge of the MLG door adjacent to the wedge (22) is flush (0±0.030 inch (0±0.76 mm)) to the aircraft lower skin surface (ZONE B). NOTE: Make sure that the inside surface of the MLG door does not touch or rub against any adjacent components or wiring harnesses. (2) If the mismatch is not correct in this location, add or remove the laminated shims (23) to do the basic adjustment of the wedge (22) as follows: (a) Remove the two screws (24) and (25) and the wedge (22). (b) Add or remove the laminated shims (23) to adjust the wedge (22) as necessary. (c) Install the wedge (22) with the laminated shims (23) and attach them with the screws (24) and (25). (d) Make sure that the aft edge of the MLG door adjacent to the wedge (22) is still flush (0±0.030 inch (0±0.76 mm)) to the aircraft lower skin surface. If necessary, do this adjustment again. When the wedge (22) basic adjustment has been done, do a check of the remaining MLG door mismatches (ZONES A, B, D, and E) to the aircraft lower skin surfaces as follows: (1) Make sure that: ± In ZONE A, there is a +0.100/−0.050 inch (+2.54/−1.27 mm) maximum mismatch along the forward edge of the MLG door at the wing lower skin ± In ZONE B, there is a 0±0.030 inch (0±0.76 mm) maximum mismatch along the aft edge of the MLG door at the wing lower skin ± In ZONE D, there is a 0±0.020 inch (0±0.5 mm) maximum mismatch along the forward edge of the MLG door at the wing lower skin ± In ZONE E, there is a +0.050/−0.100 inch (+1.27/−2.54 mm) maximum mismatch along the forward edge of the MLG door at the wing lower skin (2) If necessary, adjust the door strut (1) again if the surfaces are not flush within the limits given at the forward or aft edges of the MLG door. One turn of the jam nuts (12) and (14) on the rod end of the door strut (1) is approximately equal to 0.070 inch (1.78 mm) travel at the inboard end of the MLG door. NOTE: If the surfaces are still not flush within the limits given, it is possible that you will have to adjust the wedge (22), or the adjust the length of the door strut (1) again, or adjust the MLG door mismatch at the MLG door outboard edge (ZONE C) again. Subtask 32−12−01−820−009 P. Do the steps that follow to adjust the remaining MLG door clearances (ZONES A, B, D, and E): (1) If the engines (or engine ballast) are installed on the aircraft, measure the clearance between the MLG door and the adjacent metallic and composite wing skins (in ZONES A, B, D, and E) as follows: Master EFFECTIVITY: See Pageblock 32−12−01 page 501 32−12−01 Page 510 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (a) Make sure that the clearance between the wing skin and the MLG door is a minimum of 0.030 inch (0.76 mm) and is a maximum of 0.090 inch (2.3 mm) at the forward, aft and outboard edges. (2) If the engines (or engine ballast) are not installed on the aircraft, measure the clearance between the MLG door and the adjacent metalic and composite wing skins (in ZONES A, B, D, and E) as follows: (a) At the aft edge of the MLG door adjacent to the composite wing skin (ZONE A), make sure that: ± There is a minimum clearance of 0.110 in. (2.8 mm) ± There is a maximum clearance of 0.150 in. (3.8 mm). (b) At the forward or the aft edges of the MLG door adjacent to the metalic wing skin (ZONES B and D), make sure that: ± There is a minimum clearance of 0.030 in. (0.76 mm) ± There is a maximum clearance of 0.090 in. (2.3 mm). (c) At the forward edge of the MLG door adjacent to the composite wing skin (ZONE E), make sure that: ± There is a minimum clearance of 0.010 in. (0.25 mm) ± There is a maximum clearance of 0.030 in. (0.76 mm). Subtask 32−12−01−980−003 Q. If the MLG door clearances are satisfactory, and the MLG door is flush to the limits given, do the steps that follow: (1) Set the pressure to the "DOWN" line of the hydraulic test stand (line No. 2). WARNING: BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. CAUTION: MAKE SURE THAT THE CONTROL RODS WILL NOT CATCH THE GEAR OR SURROUNDING AREA WHEN THE LANDING GEAR IS OPERATED. DAMAGE TO THE AIRCRAFT CAN OCCUR. (2) Slowly pressurize line No. 2 from the hydraulic test stand until the MLG uplock releases. NOTE: The MLG uplock latch will release between 350 and 550 psig (2413 and 3792 kPa). (3) Adjust the pressure to 600 psig (4137 kpa) and fully extend the landing gear. Make sure that the landing gear is down and that the MLG downlock is locked. (4) Install the applicable MLG safety lockpin (Ref. TASK 10−11−00−400−802). (5) Release the hydraulic pressure from line No. 2. Subtask 32−12−01−430−007 R. Connect the door strut (1) to the MLG door as follows: (1) Align the rod end of the door strut (1) with the MLG door. Master EFFECTIVITY: See Pageblock 32−12−01 page 501 32−12−01 Page 511 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (2) (3) (4) (5) (6) (7) (8) Insert the clamp−up bushing (6) in the rod end. Insert the bolt (5) through the forward side of the rod end of the door strut (1). Install the washer (4) and the nut (3) on to the bolt (5). Safety the nut (3) with the cotter pin (2). Make sure that the jam nuts (12) and (14) are tightened correctly. Safety the jam nut (12) to the door strut (1) with 05−004 lockwire. Bend the locking tab of the tab washer (13) to safety the jam nut (14). 4. Close Out Subtask 32−12−01−090−006 A. Disconnect the hydraulic lines No. 1 and No. 2 and remove the hydraulic test stand. Subtask 32−12−01−430−006 B. Remove the protective caps from the hydraulic lines and the "UP" and "DOWN" ports of the MLG selector valve. Connect the "UP" hydraulic line to the "UP" port of the MLG selector valve and the "DOWN" hydraulic line to the "DOWN" port. Subtask 32−12−01−870−001 MAKE SURE THAT YOU BLEED THE HYDRAULIC LINES OF ANY AIR THAT IS CAUGHT IN THEM. IF YOU DO NOT DO THIS, THE LANDING GEAR CAN DROP SUDDENLY WHEN IT IS RELEASED FROM THE UPLOCK. Bleed hydraulic system No. 3 (MLG selector valve) (Ref. TASK 29−10−00−870−803). WARNING: C. Subtask 32−12−01−710−006 D. Do an operational test of the main landing gear doors (Ref. TASK 32−12−01−710−801). Subtask 32−12−01−410−006 E. Install the applicable MLG wheel bin (Ref. TASK 53−83−01−400−801). Subtask 32−12−01−586−006 F. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Master EFFECTIVITY: See Pageblock 32−12−01 page 501 32−12−01 Page 512 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL RETURN (REF) UP LINE DOWN LINE VIEW LOOKING UP ON HYDRAULIC BEAM ram3212015_001.dc,CR/br,27/04/92 M.L.G. SELECTOR VALVE Hydraulic Test Stand Connection Figure 501 Master EFFECTIVITY: See Pageblock 32−12−01 page 501 32−12−01 Page 513 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL NOTE Right equipment shown, left equipment opposite. UPPER PIVOT FITTING (REF) C 7 MLG DOOR (REF) A BELLCRANK (REF) 11 1 PIVOT PIN (REF) B OVERCENTER DISTANCE 1.1 in. (27.94 mm) A FW D 6 VIEW LOOKING FORWARD RIGHT SIDE UPPER PIVOT FITTING (REF) D LEGEND 2 1 9 ROD END (REF) 4 3 10 8 B C 14 ROD END (REF) 15 13 12 VIEW LOOKING FORWARD RIGHT SIDE 1. Door strut. 2. Cotter pin. 3. Nut. 4. Washer. 5. Bolt. 6. Bushing. 7. Push/pull rod attachment point. 8. Bolt. 9. Nut. 10. Serrated plate. 11. Strut−to−bellcrank attachment point. 12. Jam nut. 13. Tab washer. 14. Jam nut. 15. Tab washer. NOTE 1 1 D VIEW LOOKING AFT Bend the tab of the washer (15) that is on the flat of the nut (14) only. ram3212015_002(1).dc, rm, 10/03/97 5 13.10 in. (332.74 mm) Adjustment of the MLG Door Figure 502 (Sheet 1 of 3) Master EFFECTIVITY: See Pageblock 32−12−01 page 501 32−12−01 Page 514 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL METALLIC SKIN (REF) 16 NOTE 17 Right equipment shown, left equipment opposite. 18 D FW COMPOSITE SKIN (REF) LEGEND 16. Nut. 17. Washer. 18. Door hinge fitting. 19. Serrated plate. 20. Laminated shim. 21. Roller. 22. Wedge. 23. Laminated shim. 24. Screw. 25. Screw. 0.125 in. (3.18 mm) MAXIMUM MLG MOUNTING TRUNION (REF) 18 17 INBD 16 MOUNTING STUDS (REF) 20 23 22 24 19 VIEW LOOKING AFT 22 VIEW LOOKING UP AND AFT LOWER SKIN SURFACE (REF) 21 DOOR IN THE CLOSED POSITION ram3212015_003.dg, cr/lr, 15/05/03 25 Adjustment of the MLG Door Figure 502 (Sheet 2 of 3) Master EFFECTIVITY: See Pageblock 32−12−01 page 501 32−12−01 Page 515 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL NOTE Right equipment shown, left equipment opposite. ZONE E Adjacent to composite skin. ZONE A Adjacent to composite skin. ZONE D Adjacent to metallic skin. ZONE B Adjacent to metallic skin. OUTBD FWD ZONE C Adjacent to outboard edge. VIEW LOOKING DOWN RIGHT SIDE CLEARANCE CLEARANCE ZONE A + 0.100 − 0.50 in.(+2.54 − 1.27mm). With engines or engine ballast not installed. With engines or engine ballast installed. ZONE B 0 + 0.030 in.(0 + 0.76mm). ZONE A 0.110−0.150 in.(2.8−3.8mm). ALL ZONES 0.030−0.090 in.(0.76−2.3mm). ZONE C 0 + 0.040 in.(0 +1mm). ZONES B, C, and D 0.030−0.090 in.(0.76−2.3mm). ZONE D 0 + 0.020 in.(0 + 0.5mm). ZONE E 0.010−0.030 in.(0.25−0.76mm). ZONE E + 0.050 − 0.100 in.( +1.27 − 2.54mm). ram3212015_004.dg, cr/rm, 24/01/02 MISMATCH Adjustment of the MLG Door Figure 502 (Sheet 3 of 3) Master EFFECTIVITY: See Pageblock 32−12−01 page 501 32−12−01 Page 516 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL DOOR BRUSH − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the door brush of the main landing−gear door. Each door brush is installed on the edge of the main landing−gear door. TASK 32−12−05−000−801 Removal of the Door Brush 1. Job Set−Up Information Subtask 32−12−05−946−003 A. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins 2. Job Set−Up Subtask 32−12−05−941−003 WARNING: A. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). 3. Procedure Subtask 32−12−05−020−001 Refer to Figure 401. A. Remove the 12 screws (1) and the door brush (2) from the main landing−gear door (3). NOTE: The removal procedure for the right and left door brush is the same. Master EFFECTIVITY: See Pageblock 32−12−05 page 401 32−12−05 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL NOTE Right equipment shown, Left equipment opposite. LEGEND. 1. Screw. 2. Door brush. 3. Main landing gear door. 2 1 ram3212054_001.dc, CR/SB, 13/04/92 3 Door Brush − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−12−05 page 401 32−12−05 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−12−05−400−801 Installation of the Door Brush 1. Job Set−Up Information Subtask 32−12−05−945−001 A. Parts REF 1 Screw NAME OF PART QTY 12 IPC SEQUENCE NO. IPC 32−12−00−01−380 2. Procedure Subtask 32−12−05−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Subtask 32−12−05−420−001 Refer to Figure 401. B. Attach the door brush (2) to the door (3) with the 12 screws (1). NOTE: The installation procedure for the right and left door brush is the same. 3. Close Out Subtask 32−12−05−941−001 A. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−12−05 page 401 32−12−05 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL PUSH/PULL ROD − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the push/pull rod for the main landing gear (MLG) door. The push/pull rod is installed between the fuselage structure and the bellcrank assembly of the MLG door. B. The procedures given are for the push/pull rod for the MLG door on the right side of the aircraft. The procedures for the push/pull rod for the MLG door on the left side of the aircraft are the same. TASK 32−12−10−000−801 Removal of the Push/Pull Rod 1. Job Set−Up Information Subtask 32−12−10−946−002 REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins 2. Job Set−Up Subtask 32−12−10−941−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. 3. Procedure Subtask 32−12−10−020−001 Refer to Figure 401. A. Remove the push/pull rod (1) at the bellcrank assembly (5) as follows: NOTE: The removal procedure for the push/pull rod (1) of the left and right MLG is the same. (1) Remove the nut (2), the washer (3), and the pin (4). Disconnect the push/pull rod (1) from the bellcrank assembly (5). (2) Remove the clamp−up bushing (11) from the bellcrank assembly (5). B. Remove the push/pull rod (1) at the hinge assembly (10) as follows: Master EFFECTIVITY: See Pageblock 32−12−10 page 401 32−12−10 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (1) Remove and discard the cotter pin (6). (2) Remove the nut (7), the washer (8), and the bolt (9). Remove the push/pull rod (1) from the hinge assembly (10). (3) Remove the clamp−up bushing (12) from the hinge assembly (10). Master EFFECTIVITY: See Pageblock 32−12−10 page 401 32−12−10 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 1 PUSH/PULL ROD AND BELLCRANK ATTACHMENT POINT (REF) B A 5 PIVOT PIN (REF) OVERCENTER DISTANCE 1.1 in. (27.94 mm) FW D C VIEW LOOKING FORWARD RIGHT SIDE LEGEND 1. Push/pull rod. 2. Nut. 3. Washer. 4. Pin. 5. Bellcrank assembly. 6. Cotter pin. 7. Nut. 8. Washer. 9. Bolt. 10. Hinge assembly. 11. Clamp−up bushing. 12. Clamp−up bushing. 7 6 8 12 10 1 9 1 AF T B 4 NOTE Right equipment shown, left equipment opposite. 5 11 A 3 2 C ram3212104_001(2).dg, jp, 25/03/98 VIEW LOOKING OUTBOARD Push/Pull Rod − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−12−10 page 401 32−12−10 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−12−10−400−801 Installation of the Push/Pull Rod 1. Job Set−Up Information Subtask 32−12−10−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Feeler gauge 0.010−0.090 inch (0.26−2.28 mm) range Subtask 32−12−10−945−001 B. Parts REF 2 3 4 6 7 8 9 11 12 NAME OF PART Nut Washer Pin Cotter pin Nut Washer Bolt Bushing, clamp−up Bushing, clamp−up QTY 1 1 1 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−12−00−01−195 IPC 32−12−00−01−190 IPC 32−12−00−01−185 IPC 32−12−00−01−211 IPC 32−12−00−01−210 IPC 32−12−00−01−205 IPC 32−12−00−01−200 IPC 32−12−00−01−155 IPC 32−12−00−01−275 Subtask 32−12−10−946−001 C. Reference Information REFERENCE TASK 32−12−01−710−801 TASK 32−12−01−820−801 TASK 12−20−32−640−803 DESIGNATION Operational Test of the Main Landing Gear Doors Adjustment of the Main Landing Gear Doors Lubrication of the Landing Gear Doors 2. Job Set−Up Subtask 32−12−10−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. 3. Procedure Subtask 32−12−10−420−001 Refer to Figure 401. Master EFFECTIVITY: See Pageblock 32−12−10 page 401 32−12−10 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A. B. Install the push/pull rod (1) at the hinge assembly (10) as follows: NOTE: Make sure that the machined cut−outs of the push/pull rod face forward and that the curve of the push/pull rod points inboard when the push/pull rod is installed. (1) Attach the push/pull rod (1) to the hinge assembly (10) with the bolt (9), the clamp−up bushing (12), the washer (8), and the nut (7). NOTE: The bolt (9) is installed from the aft side of the hinge assembly (10). (2) With a feeler gauge, measure the distance between the aft face of the washer (8) and the forward face of the flanged bushing (that holds the clamp−up bushing (12) in the hinge assembly (10)). Make sure that the gap is between 0.010−0.090 inch (0.26−2.28 mm). (3) Safety the nut (7) with the cotter pin (6). Install the push/pull rod (1) at the bellcrank assembly (5) as follows: (1) Align the bottom end of the push/pull rod (1) with the bellcrank assembly (5). Make sure that the push/pull rod and bellcrank attachment point is approximately 1.1 inch (27.94 mm) outboard of the pivot pin (measured horizontally) as shown in view C of Figure 401. NOTE: To prevent damage during gear retraction, make sure that the bellcrank assembly (5) is rotated to get the correct over center distance before you connect the push/pull rod (1) to the bellcrank assembly (5). (2) Attach the push/pull rod (1) to the bellcrank assembly (5) with the pin (4), the washer (3), and the nut (2). Install the pin (4), with the flat side of the pin head against the machined flat on the bellcrank assembly (5). (3) With a feeler gauge, measure the distance between the forward face of the washer (3) and the aft face of the flanged bushing (that holds the clamp−up bushing (11) in the bellcrank assembly (5)). Make sure that the gap is between 0.010−0.090 inch (0.26−2.28 mm). 4. Close Out Subtask 32−12−10−640−001 A. Lubricate the bellcrank assembly (5) for the MLG door (Ref. TASK 12−20−32−640−803). Subtask 32−12−10−820−001 B. If you did not get the correct measured dimension of 1.1 inch (27.94 mm) at the push/pull rod and bellcrank attachment point, do an adjustment of the MLG doors (Ref. TASK 32−12−01−820−801). Subtask 32−12−10−710−001 C. If you got the correct measured dimension of 1.1 inch (27.94 mm) at the push/pull rod and bellcrank attachment point, do an operational test of the MLG doors (Ref. TASK 32−12−01−710−801). Master EFFECTIVITY: See Pageblock 32−12−10 page 401 32−12−10 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−12−10−943−002 D. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−12−10 page 401 32−12−10 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL BELLCRANK ASSEMBLY − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the bellcrank for the main−landing−gear (MLG) door assembly. There is one bellcrank for each door assembly. It is attached to the main fitting of the landing gear. The bellcrank is connected to the fuselage structure by a push/pull rod, and it is connected to the door by a strut. B. The procedures given are for the bellcrank assembly for the MLG door on the right side of the aircraft. The procedures for the bellcrank assembly for the MLG door on the left side of the aircraft are the same. TASK 32−12−15−000−801 Removal of the Bellcrank Assembly 1. Job Set−Up Information Subtask 32−12−15−946−002 A. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins 2. Job Set−Up Subtask 32−12−15−490−001 WARNING: A. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). 3. Procedure Subtask 32−12−15−020−001 Refer to Figure 401. **ON A/C ALL A. Remove the bellcrank assembly (1) as follows: NOTE: The removal procedure for the bellcrank assembly of the right gear door is given. The procedure for the left gear door is the same. Master EFFECTIVITY: See Pageblock 32−12−15 page 401 32−12−15 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (1) (2) (3) (4) (5) (6) (7) (8) (9) Remove the nut (2), the washer (3), the clamp−up bushing (4), and the pin (5). Disconnect the push/pull rod (6) from the bellcrank assembly (1). Remove and discard the cotter pin (7). Remove the nut (8), the washer (9), the clamp−up bushing (10), and the bolt (11). Disconnect the door strut (12) from the bellcrank assembly (1). Remove and discard the cotter pin (13). Remove the nut (14) and the washer (15). Remove the bellcrank assembly (1) from the pin (16). If installed, remove the washer(s) (17) from the pin (16). Master EFFECTIVITY: See Pageblock 32−12−15 page 401 32−12−15 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Bellcrank assembly. 2. Nut. 3. Washer. 4. Clamp−up bushing. 5. Pin. 6. Push/pull rod. 7. Cotter pin. 8. Nut. 9. Washer. A 10. Clamp−up bushing. 11. Bolt. 12. Door strut. 13. Cotter pin. 14. Nut. 15. Washer. 16. Stay stud. 17. Washer. FW D 6 PUSH/PULL ROD AND BELLCRANK ATTACHMENT POINT (REF) NOTES Right equipment shown, left equipment opposite. 1 PIVOT PIN (REF) 1 Use washers (17) as required to get OVERCENTER a gap of 0.005 to 0.016 in. (0.13 to DISTANCE 0.41mm) when the bellcrank (1) is installed. 1.1 in. (27.94 mm) 12 B MAIN FITTING VIEW LOOKING FORWARD RIGHT SIDE 6 11 5 7 10 16 FW D 4 17 1 A 15 3 13 9 8 2 B 14 ram3212154_002(1).dg, jp, 09/03/98 12 1 Bellcrank Assembly − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−12−15 page 401 32−12−15 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−12−15−400−801 Installation of the Bellcrank Assembly 1. Job Set−Up Information Subtask 32−12−15−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Feeler gauge 0.010−0.090 inch (0.26−2.28 mm) range Subtask 32−12−15−944−001 B. Consumable Materials REFERENCE 04−005 DESIGNATION Grease, aircraft and instrument, gear and actuator screw Subtask 32−12−15−945−001 C. Parts REF 2 3 4 5 7 8 9 10 11 13 14 15 17 NAME OF PART Nut Washer Bushing, clamp−up Pin Cotter pin Nut Washer Bushing, clamp−up Bolt Cotter pin Nut Washer Washer QTY 1 1 1 1 1 1 1 1 1 1 1 1 A/R IPC SEQUENCE NO. IPC 32−12−00−01−195 IPC 32−12−00−01−190 IPC 32−12−00−01−155 IPC 32−12−00−01−185 IPC 32−12−00−01−041 IPC 32−12−00−01−040 IPC 32−12−00−01−035 IPC 32−12−00−01−140 IPC 32−12−00−01−030 IPC 32−11−00−02−205 IPC 32−11−00−02−200 IPC 32−11−00−02−195 IPC 32−11−00−02−210 Subtask 32−12−15−946−001 D. Reference Information REFERENCE TASK 32−12−01−710−801 TASK 32−12−01−820−801 TASK 12−20−32−640−803 DESIGNATION Operational Test of the Main Landing Gear Doors Adjustment of the Main Landing Gear Doors Lubrication of the Landing Gear Doors Master EFFECTIVITY: See Pageblock 32−12−15 page 401 32−12−15 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 2. Job Set−Up Subtask 32−12−15−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. 3. Procedure Subtask 32−12−15−420−001 Refer to Figure 401. **ON A/C ALL A. Install the bellcrank assembly (1) to the MLG main fitting as follows: NOTE: The installation procedure for the bellcrank assembly of the right gear door is given. The procedure for the bellcrank of the left gear door is the same. (1) Apply a layer of 04−005 grease to the stay stud (16). (2) Install the washer(s) (17) that were removed in the removal task on to the stay stud (16). (3) Install the bellcrank assembly (1) on to the stay stud (16). (4) Install the washer (15) and the nut (14). (5) Tighten the nut (14) until the cotter pin holes of the nut (14) and the stay stud (16) correctly align. (6) With a feeler gauge, measure the longitudinal travel (play) of the bellcrank (1) along the axis of the stay stud (14). Make sure that the longitudinal travel of the bellcrank (1) is between 0.005−0.016 inch. (7) If the longitudinal travel is not in the specified tolerance, do the steps that follow: (a) Remove the nut (14), the washer (15), and the bellcrank (1). (b) Add or remove the washer(s) (17) (as required) to get the correct longitudinal travel of the bellcrank (1). (c) Install the bellcrank assembly (1), the washer (15), and the nut (14) again. (d) Align the cotter pin holes of the nut (14) and the stay stud (16) and make sure that the longitudinal travel of the bellcrank (1) is correct. (8) Make sure that the bellcrank (1) is free to turn on the stay stud (16). (9) Safety the nut (14) with the cotter pin (13). B. Install the door strut (12) to the bellcrank assembly (1) as follows: (1) Align the door strut (12) with the outboard fork−end of the bellcrank assembly (1). (2) Install the bolt (11), the clamp−up bushing (10), the washer (9), the nut (8), and the cotter pin (7). (3) Tighten the bolt (11). (4) With a feeler gauge, measure the gap between the aft surface of the flanged bushing (that holds the clamp−up bushing (10) in the bellcrank assembly (1)) and the forward surface of the washer (9). Make sure that the gap is between 0.010−0.090 inch (0.26−2.28 mm). C. Install the push/pull rod (6) to the bellcrank assembly (1) as follows: Master EFFECTIVITY: See Pageblock 32−12−15 page 401 32−12−15 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (1) Align the bottom end of the push/pull rod (6) with the bellcrank assembly (1). Make sure that the push/pull rod and bellcrank attachment point is approximately 1.1 inch (27.94 mm) outboard of the pivot pin (measured horizontally) as shown in view B of. NOTE: To prevent damage during gear retraction, make sure that the bellcrank assembly (1) is rotated to get the correct over center distance before you connect the push/pull rod (6) to the bellcrank assembly (1). (2) Install the pin (5), with the flat side of the pin head against the machined flat on the bellcrank (1). (3) Install the clamp−up bushing (4), the washer (3), and the nut (2). (4) With a feeler gauge, measure the gap between the aft surface of the flanged bushing (that holds the clamp−up bushing (4) in the bellcrank assembly (1)) and the forward surface of the washer (3). Make sure that the gap is between 0.010−0.090 inch (0.26−2.28 mm). 4. Close Out Subtask 32−12−15−640−001 A. Lubricate the bellcrank (1) for the MLG door (Ref. TASK 12−20−32−640−803). Subtask 32−12−15−820−001 B. If you did not get the correct measured dimension of 1.1 inch (27.94 mm) at the push/pull rod and bellcrank attachment point, do an adjustment of the MLG doors (Ref. TASK 32−12−01−820−801). Subtask 32−12−15−710−001 C. If you got the correct measured dimension of 1.1 inch (27.94 mm) at the push/pull rod and bellcrank attachment point, do an operational test of the MLG doors (Ref. TASK 32−12−01−710−801). Subtask 32−12−15−943−002 D. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−12−15 page 401 32−12−15 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL STAY STUD, DOOR − REMOVAL/INSTALLATION 1. General A. The procedures that follow are for the removal and installation of the door stay stud. The stay stud is the pivot point for MLG door bellcrank. The stay stud is installed on the MLG main fitting. It is necessary to remove the bellcrank for the removal and installation of the stay stud. B. The removal and installation procedure for the stay stud on the right main−landing−gear (MLG) is given. The removal and installation procedure for the stay stud on the left MLG is the same. TASK 32−12−17−000−801 Removal of the Door Stay Stud 1. Job Set−Up Information Subtask 32−12−17−946−001 A. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−12−15−000−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Removal of the Bellcrank Assembly 2. Job Set−Up Subtask 32−12−17−490−001 WARNING: A. MAKE SURE THAT THE LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEARS. THE NOSE AND MAIN LANDING GEARS CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the lockpins on the nose and main landing gears (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Subtask 32−12−17−010−001 B. Remove the MLG door bellcrank (Ref. TASK 32−12−15−000−801). 3. Procedure Subtask 32−12−17−020−002 Refer to Figure 401. Master EFFECTIVITY: See Pageblock 32−12−17 page 401 32−12−17 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A. Remove the stay stud (1) from the main fitting as follows: (1) Cut and discard the lockwire from the stay stud (1) and the plug (3). (2) Remove the stay stud (1) and the washer (2) from the main fitting and plug (3). (3) Remove the plug (3). Master EFFECTIVITY: See Pageblock 32−12−17 page 401 32−12−17 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A B FW D A NOTE MAIN FITTING Right side shown, left side opposite. 2 3 LEGEND 1. Stay stud. 2. Washer. 3. Plug. B ram3212174_002.dg, gg, 31/03/95 1 Door Stay Stud − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−12−17 page 401 32−12−17 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−12−17−400−801 Installation of the Door Stay Stud 1. Job Set−Up Information Subtask 32−12−17−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Torque wrench, 0−160 pound−inches (0−18 N·m) Subtask 32−12−17−944−001 B. Consumable Materials REFERENCE 08−025 05−005 DESIGNATION Retaining compound, single component, anaerobic Lockwire Subtask 32−12−17−945−001 C. Parts REF 1 2 3 NAME OF PART Stay stud Washer Plug QTY 1 1 1 IPC SEQUENCE NO. IPC 32−11−00−02−180 IPC 32−11−00−02−190 IPC 32−11−00−02−185 Subtask 32−12−17−946−002 D. Reference Information REFERENCE TASK 32−12−15−400−801 DESIGNATION Installation of the Bellcrank Assembly 2. Job Set−Up Subtask 32−12−17−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. 3. Procedure Subtask 32−12−17−420−002 Refer to Figure 401. A. Install the stay stud (1) on the main fitting as follows: (1) Install the plug (3) in the main fitting. (2) Install the washer (2) on the stay stud (1). Master EFFECTIVITY: See Pageblock 32−12−17 page 401 32−12−17 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (3) (4) (5) (6) Apply 08−025 retaining compound to the large threads of the stay stud (1). Install the stay stud (1) through the main fitting and in the plug (3). Torque the stay stud (1) to 150−160 pound−inches (17−18 N·m). Double−safety the stay stud (1) to the plug (2) with the lockwire. 4. Close Out Subtask 32−12−17−410−001 A. Install the bellcrank assembly (Ref. TASK 32−12−15−400−801). Subtask 32−12−17−941−001 B. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−12−17 page 401 32−12−17 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL DOOR STRUT − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the door strut. Each door strut connects the main landing gear (MLG) door to the bellcrank assembly on the MLG. B. The procedures given are for the MLG door strut on the right side of the aircraft. The procedures for the MLG door strut on the left side of the aircraft are the same. TASK 32−12−20−000−801 Removal of the Door Strut 1. Job Set−Up Information Subtask 32−12−20−946−004 REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins 2. Job Set−Up Subtask 32−12−20−490−001 WARNING: A. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). 3. Procedure Subtask 32−12−20−020−001 Refer to Figure 401. A. Remove the door strut (1) as follows: NOTE: The removal procedure for the door strut of the right and left MLG is the same. (1) Remove and discard the cotter pin (2) from the nut (3). (2) Remove the nut (3), the washer (4), and the bolt (5) with the clamp−up bushing (6). Disconnect the door strut (1) from the MLG door (7). (3) Remove and discard the cotter pin (8). (4) Remove the nut (9), the washer (10), and the bolt (11) with the clamp−up bushing (12). Master EFFECTIVITY: See Pageblock 32−12−20 page 401 32−12−20 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (5) Remove the door strut (1) from the bellcrank assembly (13). Master EFFECTIVITY: See Pageblock 32−12−20 page 401 32−12−20 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Door strut. 2. Cotter pin. 3. Nut. 4. Washer. 5. Bolt. 6. Clamp−up bushing. 7. MLG door. 8. Cotter pin. 9. Nut. 10. Washer. 11. Bolt. 12. Clamp−up bushing. 13. Bellcrank assembly. A B 7 5 2 1 A 6 4 3 FW 8 12 LEGEND. Right equipment shown left equipment opposite. 10 9 B ram3212204_001(2).dg, cr/jp, 09/03/98 13 D 11 Door Strut − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−12−20 page 401 32−12−20 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−12−20−400−801 Installation of the Door Strut 1. Job Set−Up Information Subtask 32−12−20−945−001 A. Parts REF 2 3 4 5 6 8 9 10 11 12 NAME OF PART Cotter pin Nut Washer Bolt Bushing, clamp−up Cotter pin Nut Washer Bolt Bushing, clamp−up QTY 1 1 1 1 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−12−00−01−041 IPC 32−12−00−01−025 IPC 32−12−00−01−020 IPC 32−12−00−01−015 IPC 32−12−00−01−100 IPC 32−12−00−01−041 IPC 32−12−00−01−040 IPC 32−12−00−01−035 IPC 32−12−00−01−030 IPC 32−12−00−01−140 Subtask 32−12−20−946−001 B. Reference Information REFERENCE TASK 32−12−01−820−801 DESIGNATION Adjustment of the Main Landing Gear Doors 2. Procedure Subtask 32−12−20−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Subtask 32−12−20−420−001 Refer to Figure 401. B. Install the door strut (1) as follows: NOTE: The installation procedure for the door strut of the right and left MLG is the same. (1) Align the fork−end of the door strut (1) with its related attachment point on the MLG door. Insert the bolt (5) in the forward side of the fork−end of the door strut (1). Make sure that the clamp−up bushing (6) is installed correctly in the fork−end of the door strut (1). (2) Install the washer (4), and the nut (3) on the bolt (5). (3) Tighten the nut (3). (4) Safety the nut (3) with the cotter pin (2). Master EFFECTIVITY: See Pageblock 32−12−20 page 401 32−12−20 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (5) Align the other end of the door strut (1) with its related attachment point on the bellcrank assembly (13). Insert the bolt (11) in the forward side of the bellcrank assembly (13). Make sure that the clamp−up bushing (12) is installed correctly in the bellcrank assembly (13). (6) Install the washer (10), and the nut (9). (7) Tighten the nut (9). (8) Safety the nut (9) with the cotter pin (8). 3. Close Out Subtask 32−12−20−941−004 A. Remove all tools, equipment, and unwanted materials from the work area. Subtask 32−12−20−820−001 B. Do an adjustment of the main landing−gear doors (Ref. TASK 32−12−01−820−801) if a new door strut (1) was installed or an adjustment to the fork−end of the door strut (1) was made. Master EFFECTIVITY: See Pageblock 32−12−20 page 401 32−12−20 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL NOSE LANDING GEAR AND DOORS − DESCRIPTION AND OPERATION 1. 2. 3. General A. The nose landing gear supports the nose and forward fuselage of the aircraft. The closed doors prevent the nose landing gear from damage and make a smooth surface with the aircraft fuselage when the nose landing gear is retracted. The nose landing gear and doors have the components that follow: ± One nose landing gear (32−21−00) ± Three nose landing−gear doors (32−22−00). Description Refer to Figure 1. A. Nose Landing Gear (1) The nose landing gear is a double−wheel, forward−retracting type. The nose landing gear is mechanically locked in the extended position and is held in the retracted position by a mechanical uplock assembly. The nose landing−gear system retracts by the extension/retraction actuator into the nosewheel well (32−30−00). B. Nose Landing−Gear Doors (1) The nose landing−gear doors have the components that follow: ± Two forward doors ± One rear door ± A mechanism system. The two forward doors are made of Kevlar and are independent of the nose landing gear. The rear door is made of Kevlar and is mechanically attached through its mechanism to the nose landing gear. It is hinged to the fuselage. Operation A. The extension/retraction system controls the extension and retraction of the nose landing gear, and opens and closes the forward doors (32−30−00). When the extension of the nose landing gear starts, the forward doors open before the nose landing gear is released from the uplock assembly. When the nose landing gear extends, it opens the rear door at the same time. When the nose landing gear is downlocked, the forward doors close and stay closed until the nose landing gear starts the retraction. The forward doors open before the nose landing gear starts the retraction. Master EFFECTIVITY: See Pageblock 32−20−00 page 1 32−20−00 Page 1 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL DOOR MECHANISM FORWARD DOORS ram3220000_001(1).dc, jp/pm, 09/11/95 REAR DOOR NOSE LANDING GEAR Nose Landing Gear and Doors Figure 1 Master EFFECTIVITY: See Pageblock 32−20−00 page 1 32−20−00 Page 2 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL NOSE LANDING GEAR AND DOORS − INSPECTION/CHECK 1. General A. The maintenance procedures that follow are for the visual inspection and the detailed inspection of the nose landing gear (NLG) and the NLG doors. TASK 32−20−00−210−801 Visual Inspection of the Nose Landing Gear and Doors 1. Procedure Subtask 32−20−00−210−001 Refer to Figure 601. A. Do an inspection of the NLG as follows: (1) NLG components: ± The NLG bypass valve for condition and leakage ± The NLG shock strut for condition and corrosion ± The NLG uplock pin at the bottom of the NLG shock strut is free to rotate. ± The drag brace for condition and safety of installation ± The downlock actuator for condition and safety of installation ± The related hydraulic lines and fittings for condition and leakage. (2) NLG door components: ± The NLG door and seals for condition and deterioration ± The NLG door actuator for condition and leakage ± The NLG door selector valve for condition and leakage ± The NLG door bypass valve for condition and leakage ± The NLG door connecting rods and the door operating mechanism for condition and safety of installation ± The door roller and lock mechanism for condition and safety of installation. Master EFFECTIVITY: See Pageblock 32−20−00 page 601 32−20−00 Page 601 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL DOOR MECHANISM FORWARD DOORS ram3220000_001(1).dc, jp/pm, 09/11/95 REAR DOOR NOSE LANDING GEAR Nose Landing Gear and Doors − Inspection/Check Figure 601 Master EFFECTIVITY: See Pageblock 32−20−00 page 601 32−20−00 Page 602 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−20−00−220−801 Detailed Inspection of the Nose Landing Gear Components and Doors 1. Job Set−Up Information Subtask 32−20−00−946−004 A. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−22−01−980−801 TASK 32−22−01−980−802 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors 2. Job Set−Up Subtask 32−20−00−490−001 WARNING: A. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Subtask 32−20−00−980−001 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the nose−gear forward doors (Ref. TASK 32−22−01−980−801). WARNING: B. 3. Procedure Subtask 32−20−00−220−001 Refer to Figure 602 Master EFFECTIVITY: See Pageblock 32−20−00 page 601 603 32−20−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL A. B. Inspect each door and nose landing gear component for signs of fluid leakage, general condition, and safety of installation. Do the detailed inspection of the nose landing gear components that follow: ± The drag brace ± The door linkage and hinges ± The door selector valve ± The extension/retraction actuator ± The uplock assembly ± The landing gear selector valve ± The priority valve ± The manual release mechanism ± The door actuator ± The nose wheel steering actuators ± The nose wheel steering RVDTs ± All hydraulic lines, hoses and electrical harnesses ± The shock strut and piston ± The uplock pin for free rotation ± The wheel and tire condition ± The sensors and targets installation ± The doors and seals. 4. Close−Out Subtask 32−20−00−090−001 A. If maintenance is complete on the aircraft, close the nose landing gear forward doors (Ref. TASK 32−22−01−980−802). Subtask 32−20−00−943−003 B. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−20−00 page 601 604 32−20−00 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Priority valve. 2. Selector valve. 3. Retraction actuator. 4. Downlock release actuator. 5. Drag brace. 6. Uplock. 7. Hydraulic line (typical). 8. Door seal. 9. Door linkage (typical). 10. Door actuator. 11. Steering actuator. A B 1 A 3 2 7 10 6 5 4 8 ram3220006_001.dg, lr, 23/11/04 8 11 9 B Nose Landing Gear Components and Doors − Detailed Inspection Figure 602 Master EFFECTIVITY: See Pageblock 32−20−00 page 601 32−20−00 Page 605 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL TASK 32−20−00−220−802 Detailed Inspection of the Nose Landing Gear (NLG) Components 1. Reason for the Job Refer to MRB 32−00−00−19 and MRB 32−50−01−05. 2. Job Set−Up Information Subtask 32−20−00−946−001 A. Reference Information REFERENCE TASK 10−11−00−000−801 TASK 10−11−00−000−802 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−22−01−980−801 TASK 32−22−01−980−802 DESIGNATION Removal of the Nose Landing Gear Lockpin Removal of the Main Landing Gear Lockpins Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors 3. Job Set−Up Subtask 32−20−00−490−002 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. Subtask 32−20−00−980−002 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the nose−gear forward doors (Ref. TASK 32−22−01−980−801). WARNING: B. Master EFFECTIVITY: See Pageblock 32−20−00 page 601 606 32−20−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 4. Procedure Subtask 32−20−00−220−002 Refer to Figure 603 A. Inspect the NLG components for signs of fluid leakage, general condition, and safety of installation. B. Do the detailed inspection of the NLG components that follow: ± The drag brace ± The door linkage and hinges ± The door selector valve ± The extension/retraction actuator ± The uplock assembly ± The landing gear selector valve ± The priority valve ± The manual release mechanism ± The door actuator ± The nose wheel steering actuators ± All hydraulic lines, hoses and electrical harnesses ± The shock strut and piston ± The uplock pin for free rotation ± The wheel and tire condition ± The sensors and targets installation 5. Close−Out Subtask 32−20−00−090−002 A. B. If maintenance is complete on the aircraft, remove the safety lockpins at the nose landing gear and at the main landing gear (TASK 10−11−00−000−801 and TASK 10−11−00−000−802). Close the nose landing gear forward doors (Ref. TASK 32−22−01−980−802). Subtask 32−20−00−943−001 C. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−20−00 page 601 607 32−20−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Extension/retraction actuator. 2. Drag brace. 3. Uplock and uplock pin. 4. Hydraulic line (typical). 5. Door linkage (typical). 6. Door actuator. 7. Steering actuator. 8. NLG bypass valve. 9. Door bypass valve. 10. Hinge (typical). 11. NLG shock strut asembly. 12. Shock strut. 13. Piston. 14. Door. A 1 5 4 2 6 3 9 14 8 11 10 7 5 12 13 A ram3220006_002.dg, rm/lr, 5/10/05 14 Nose Landing Gear (NLG) Components − Detailed Inspection Figure 603 (Sheet 1 of 2) Master EFFECTIVITY: See Pageblock 32−20−00 page 601 608 32−20−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 15 LEGEND 15. NLG selector valve. 16. NLG door selector valve. 17. NLG priority valve. 17 ram3220006_003.dg, rm/lr, 13/10/04 16 Nose Landing Gear (NLG) Components − Detailed Inspection Figure 603 (Sheet 2 of 2) Master EFFECTIVITY: See Pageblock 32−20−00 page 601 32−20−00 Page 609 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL TASK 32−20−00−220−803 Detailed Inspection of the Nose Landing Gear (NLG) Doors 1. Reason for the Job Refer to MRB 32−00−00−20. 2. Job Set−Up Information Subtask 32−20−00−946−002 A. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−22−01−980−801 TASK 32−22−01−980−802 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors 3. Job Set−Up Subtask 32−20−00−490−003 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. Subtask 32−20−00−980−003 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the nose−gear forward doors (Ref. TASK 32−22−01−980−801). WARNING: B. Master EFFECTIVITY: See Pageblock 32−20−00 page 601 32−20−00 Page 610 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL 4. Procedure Subtask 32−20−00−220−003 Refer to Figure 604 A. Inspect the NLG doors for condition and safety of installation. 5. Close−Out Subtask 32−20−00−090−003 A. If maintenance is complete on the aircraft, close the nose landing gear forward doors (Ref. TASK 32−22−01−980−802). Subtask 32−20−00−943−002 B. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−20−00 page 601 32−20−00 Page 611 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL A LEGEND 1. Left NLG door (711). 2. Right NLG door (712). 3. Aft NLG door (713). 3 ram3220006_004.dg, lr, 28/09/04 2 1 A Nose Landing Gear (NLG) Doors − Detailed Inspection Figure 604 Master EFFECTIVITY: See Pageblock 32−20−00 page 601 32−20−00 Page 612 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL NOSE LANDING GEAR (NLG) − DESCRIPTION AND OPERATION 1. 2. General A. There is one nose landing gear (NLG) on the aircraft. The NLG retracts forward into the nosewheel well. The NLG is mechanically locked in the extended position and is held in the retracted position by a mechanical uplock assembly. The NLG has the components that follow: ± One NLG shock−strut assembly ± One drag brace ± One torque link assembly ± One NLG axle ± One set of NLG seals. Component Details Refer to Figure 1. A. NLG Shock−Strut Assembly (1) The shock strut assembly is of a divided gas/oil type. The shock strut assembly is made of forged and machined aluminium alloy. It has a cylinder and a piston subassembly. The annular space made by the difference between the internal and external diameters of the cylinder and piston makes the recoil damping chamber. (2) The piston subassembly has a tubular piston and a separate axle. The piston subassembly has a nitrogen charge valve installed on the bottom end of the piston. The piston is a steel tube with chrome−plated, dynamic, external and internal surfaces. (3) The piston tube has a floating piston. This floating piston isolates the nitrogen from the hydraulic fluid in the shock strut. The upper end of the floating piston has a spring−loaded taxi valve which gives primary damping during landing, and secondary damping during taxiing. (4) The cylinder subassembly has integral lugs. These lugs are used for the installation of the NLG on the aircraft, the drag brace, and the steering adaptor assembly. The steering adaptor assembly prevents the need for a splined or similar joint on the cylinder subassembly. The steering adaptor assembly holds the steering actuators and the steering collar. The cylinder subassembly has oil−fill provisions installed on its top end. The cylinder bore of the cylinder subassembly is anodized. (5) The shock strut has a set of centering cams installed to the piston subassembly and the cylinder subassembly. The centering cams align the wheels in the correct direction when the shock strut is fully extended. The centering cams give unrestricted movement of the wheels when the weight of the aircraft is on the NLG. (6) The upper cam has the upper bearing and the rebound ring. The lower cam has the static, dynamic, and spare seals. The lower bearing has the lower cam in the cylinder subassembly and is held by the gland nut. The gland nut has a scraper seal. Master EFFECTIVITY: See Pageblock 32−21−00 page 1 32−21−00 Page 1 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL B. Drag Brace (1) The drag brace is made of an upper and lower link assembly. It is hinged at the center joint and attached to the airframe and to the NLG. The drag brace mechanically locks the NLG in the down position and releases hydraulically during the retraction. (2) The drag brace has two assister springs attached to the lower link of the drag brace and to the NLG. These assister springs help the the drag brace to lock correctly. (3) The drag brace has an over−center lock mechanism. The lock mechanism is hydraulically released and lets the drag brace fold when the NLG retracts. The indication of the lock condition is given by the proximity switches (32−61−00). The drag brace also has provisions for the installation of the safety pins when the aircraft is on the ground. **ON A/C 7003−7067, 7069−7273 Pre VSBM−DT−16040−32−12 C. Torque Link Assembly (1) The torque link assembly has the upper and lower torque link. The upper torque link is attached to the steering collar, and the lower torque link is attached to the axle. The torque link assembly is hinged at the center through a quick−disconnect mechanism which lets the maintenance person disconnect the upper torque link from the lower torque link. When the torque link assembly is disconnected, the upper torque link is spring loaded up against a stop, and the lower torque link is supported by a rubber pad. The torque link assembly has grease fittings used for lubrication. (2) The main function of the torque link assembly is to transmit steering torque from the steering collar to the axle. The torque link assembly is disconnected before the towing operation. **ON A/C 7274−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7273 Post VSBM−DT−16040−32−12 D. Torque Link Assembly (1) The torque link assembly has the upper and lower torque link. The upper torque link is attached to the steering collar, and the lower torque link is attached to the axle. The torque link assembly is hinged at the center through a quick−disconnect mechanism which lets the maintenance person disconnect the upper torque link from the lower torque link. To prevent damage to the NLG when the torque link assembly is disconnected, the torque links are spring loaded. The upper torque link is spring loaded up against a stop, and the lower torque link is spring loaded down and supported by a rubber pad. The torque link assembly has grease fittings used for lubrication. **ON A/C ALL E. NLG Axle (1) The axle is installed on the bottom of the piston subassembly of the shock strut. The axle has a jacking pad used for the jacking of the aircraft, and an uplock pin assembly which is used to keep the NLG in the retracted position. The axle has integral lugs which are used for the installation of the lower torque link. The axle has internal spools located at each end of the axle. These are used as tow−bar attachment points. Master EFFECTIVITY: See Pageblock 32−21−00 page 1 Page 2 32−21−00 Dec 10/2005 C AIRCRAFT MAINTENANCE MANUAL F. 3. 4. NLG Seals (1) There are seals installed on the lower gland of the cylinder subassembly. Operation A. The NLG gives ground directional control of the aircraft. When the extension starts, the uplock assemblies release the NLG. The extension/retraction actuator makes the NLG extend. When the NLG is extended, the shock strut is fully extended and the drag brace locks the NLG in the extended position. During the landing and the taxiing, the shock strut is compressed and absorbs all the shocks. The NLG uses the steering system (32−50−00), the torque link assembly, the axle, and the nosewheel/tire assemblies (32−42−00) to give ground directional control of the aircraft. Component Location Index Refer to Figure 1. COMPONENT NAME NLG shock−strut assembly Drag brace Torque links assembly NLG axle NLG seals QTY 1 1 1 1 2 Master EFFECTIVITY: See Pageblock 32−21−00 page 1 ACCESS/ZONE 714 714 714 714 714 REFERENCE 32−21−01 32−21−05 32−21−10 32−21−15 32−21−20 32−21−00 Page 3 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL NLG EXTENSION/RETRACTION ACTUATOR (32−33−00) DRAG BRACE REAR DOOR ATTACHMENTS DOWNLOCK ASSIST SPRINGS (32−30−00) TORQUE LINKS ASSEMBLY STEERING ACTUATORS (32−52−00) N.L.G. SEALS (INTERNAL) QUICK DISCONNECT N.L.G. SHOCK STRUT ASSEMBLY UPLOCK PIN NITROGEN CHARGE VALVE ram3221000_001.dc, jr/gd, 24/08/92 N.L.G. AXLE NLG System Figure 1 Master EFFECTIVITY: See Pageblock 32−21−00 page 1 32−21−00 Page 4 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL SHOCK STRUT, NOSE LANDING GEAR (NLG) − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the shock strut assembly of the nose landing gear (NLG). TASK 32−21−01−000−801 Removal of the NLG Shock Strut 1. Job Set−Up Information Subtask 32−21−01−943−003 A. Tools and Equipment REFERENCE None specified 460004588 G601R321006−1 DESIGNATION Container, hydraulic fluid Extractor, pivot pin NLG Dolly − MLG and NLG removal and installation support stand Subtask 32−21−01−946−002 B. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 12−12−32−610−804 TASK 29−00−00−910−801 TASK 32−22−01−980−801 TASK 32−42−01−000−801 DESIGNATION Put the Aircraft on Jacks Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − System No. 3 Servicing of the NLG Shock Strut With Jacks Hydraulic Safety Precautions Open and Isolate the Nose−Landing−Gear Forward Doors Removal of the Nosewheel/Tire Assembly 2. Job Set−Up Subtask 32−21−01−941−002 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. Master EFFECTIVITY: See Pageblock 32−21−01 page 401 32−21−01 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−01−910−002 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: B. Subtask 32−21−01−010−001 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the NLG forward doors (Ref. TASK 32−22−01−980−801). WARNING: C. Subtask 32−21−01−863−001 D. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−21−01−865−002 E. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−4 CB NO. A2 F6 F7 F8 G11 A2 F8 F9 G15 P2 P3 B13 NAME HYD PUMP 3B PROX SENS LGC/D1 PROX SENS WOW 1 NOSE STEER HYD SYST AC PUMP CONT 3B HYD PUMP 3A NOSE STEER PROX SENS WOW 2 HYD SYST AC PUMP CONT 3A PROX SENS LGC/D1 PROX SENS LGC/D2 WOW 1 + 2 PROX SENS LGC/D2 Master EFFECTIVITY: See Pageblock 32−21−01 page 401 32−21−01 ZONE 221 221 221 221 221 222 222 222 222 222 222 222 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−01−582−001 F. Put the aircraft on jacks (Ref. TASK 07−11−01−582−801). Subtask 32−21−01−010−002 G. Remove the two nosewheel/tire assemblies (Ref. TASK 32−42−01−000−801). Subtask 32−21−01−614−002 H. Release the nitrogen pressure from the NLG shock strut (Ref. TASK 12−12−32−610−804). 3. Procedure Subtask 32−21−01−840−001 Refer to Figure 401. A. Do the steps that follow to prepare the NLG shock strut (43) for removal: (1) Disconnect the P62 electrical connector (49), the P4GC electrical connector (50), and the P63 electrical connector (51) from the nosewheel well. (2) Install protective plugs/caps on the electrical connectors and their related receptacles. (3) Disconnect each control rod (5) from the NLG shock strut (43) as follows: (a) Remove and discard the cotter pin (1). (b) Remove the nut (2), the washers (3), and the bolt (4). (c) Disconnect the control rods (5) from the NLG shock strut (43). (4) Disconnect the extension/retraction actuator (15) from the NLG shock strut (43) as follows: (a) Remove and discard the cotter pin (6). (b) Remove the nut (7), the washers (8) and (9), the bolt (10), washers (11) and (12), and the retaining plate (13). (c) Carefully remove the actuator pin (14) and disconnect the extension/retraction actuator (15) from the NLG shock strut (43). (5) Disconnect the drag brace (20) from the NLG shock strut (43) as follows: (a) Remove and discard the cotter pins (16). WARNING: BE CAREFUL WHEN YOU DISCONNECT THE SPRING ASSEMBLIES FROM THE DRAG BRACE. THERE IS TENSION IN THESE SPRING ASSEMBLIES. ACCIDENTAL RELEASE OF THIS TENSION CAN CAUSE INJURIES. (b) Remove the nuts (17), the washers (45) and (46), and the spacers (18). Carefully disconnect the spring assemblies (19) from the drag brace (20). (c) Remove and discard the cotter pin (21). (d) Remove the nut (22), the washers (23) and (47), the bolt (24), and the collar (25). Remove the drag brace pin (26) and disconnect the drag brace (20). Master EFFECTIVITY: See Pageblock 32−21−01 page 401 403 32−21−01 SepPage 10/2004 C AIRCRAFT MAINTENANCE MANUAL (6) (7) (8) (9) Put the fluid container below the work area. Disconnect the hydraulic lines (27) and (28) from the swivel assembly (29). Remove and discard the lockwire from the banjo bolts (30). Remove the banjo bolts (30) and disconnect the hydraulic pipes of the swivel assembly (29) from the electrohydraulic module (31). Remove and discard the preformed packings (32). (10) Install protective caps on all open hydraulic lines and/or ports. (11) Remove and discard the lockwire from the screws (33) that attach the swivel assembly (29) to the NLG shock strut (43). (12) Remove the screws (33) and the swivel assembly (29). Subtask 32−21−01−020−001 Refer to Figure 401. B. Do the steps that follow to remove the NLG shock strut (43) form the nosewheel well: (1) Hold the NLG shock strut (43) in position with the NLG dolly support stand. (2) At the bolt (37), remove and discard the cotter pin (34), the nut (35), and the washers (36) and (48). (3) At the bolt (38), remove and discard the cotter pin (34), the nut (35), and the washers (36) and (48) (if installed). (4) Remove the bolts (37) and (38) (with the washers (36) and (48) if installed) from the NLG shock strut (43). (5) Remove the grease insert assemblies from the inner bores of the left and the right trunnion pins (42). NOTE: The grease insert assemblies are an assembly of the grease insert (39) or (40) and the two preformed packings (41). (6) Remove and discard the preformed packings (41) from the grease inserts (39) and (40). (7) Remove the left and the right trunnion pins (42) with the pivot−pin extractor tool. (8) Carefully remove the NLG shock strut (43) from the nosewheel well. Master EFFECTIVITY: See Pageblock 32−21−01 page 401 404 32−21−01 SepPage 10/2004 C AIRCRAFT MAINTENANCE MANUAL 50 49 51 35 34 36 35 34 48 48 36 36 37 48 42 36 38 15 NLG REAR DOOR (REF) 44 16 17 45 46 24 25 48 47 23 43 21 18 5 22 46 19 3 1 2 20 NOTE Refer to the installation procedure for quantity. 18 19 45 17 4 3 16 26 1. Cotter pin. 2. Nut. 3. Washer. 4. Bolt. 5. Control rod. 15. Extension/ retraction actuator. 16. Cotter pin. 17. Nut. 18. Spacer. 19. Spring assembly. 20. Drag brace. 21. Cotter pin. 22. Nut. 23. Washer. 24. Bolt. 25. Collar. 26. Drag brace pin. 34. Cotter pin. 35. Nut. 36. Washer. 37. Bolt. 38. Bolt. 42. Trunnion pin. 43. NLG shock strut. 44. Bushing. 45. Washer. 46. Washer. 47. Washer. 48. Washer. 49. P62 electrical connector. 50. P4GC electrical connector. 51. P63 electrical connector. ram3221004_001.dg, gg/rm, 17/03/05 LEGEND Nose Landing Gear − Removal/Installation Figure 401 (Sheet 1 of 2) Master EFFECTIVITY: See Pageblock 32−21−01 page 401 405 32−21−01 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 43 LEGEND 6. Cotter pin. 7. Nut. 8. Washer. 9. Washer. 10. Bolt. 11. Washer. 12. Washer. 13. Retaining plate. 14. Actuator pin. 27. Hydraulic line. 28. Hydraulic line. 29. Swivel assembly. 30. Banjo bolts. 31. Electrohydraulic module. 32. Preformed packing. 33. Screw. 39. Grease insert. 40. Grease insert. 41. Preformed packing. 42. Trunnion pin. 43. NLG shock strut. 42 41 39 29 27 33 29 6 NOTE 30 Refer to the installation procedure for quantity. 11 32 FW 13 12 28 9 D 7 8 32 32 10 43 40 43 42 31 ram3221004_002.dg, rm, 24/09/01 14 Nose Landing Gear − Removal/Installation Figure 401 (Sheet 2 of 2) Master EFFECTIVITY: See Pageblock 32−21−01 page 401 32−21−01 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−21−01−400−801 Installation of the NLG Shock Strut 1. Job Set−Up Information Subtask 32−21−01−943−001 A. Tools and Equipment REFERENCE None specified None specified G601R321006−1 DESIGNATION Torque wrench, torque range 0 to 50 pound−inches (0 to 10 N·m) Torque wrench, torque range 0 to 200 pound−inches (0 to 20 N·m) Dolly − MLG and NLG removal and installation support stand Subtask 32−21−01−944−001 B. Consumable Materials REFERENCE 02−001 04−005 05−005 06−014 DESIGNATION Hydraulic fluid, phosphate ester base Grease Lockwire Lubricant, hydraulic seal, phosphate ester resistant Subtask 32−21−01−945−001 C. Parts REF 1 2 3 4 6 7 8 9 10 11 12 13 14 16 17 NAME OF PART Cotter pin Nut Washer Bolt Cotter pin Nut Washer Washer Bolt Washer Washer Retaining plate Actuator pin Cotter pin Nut Master EFFECTIVITY: See Pageblock 32−21−01 page 401 QTY 2 2 4 2 1 1 AR AR 1 AR AR 1 1 2 2 IPC SEQUENCE NO. IPC 32−22−00−01−425 IPC 32−22−00−01−420 IPC 32−22−00−01−415 IPC 32−22−00−01−405 IPC 32−33−01−01−075 IPC 32−33−01−01−070 IPC 32−33−01−01−065 IPC 32−33−01−01−060 IPC 32−33−01−01−055 IPC 32−33−01−01−065 IPC 32−33−01−01−060 IPC 32−33−01−01−050 IPC 32−33−01−01−080 IPC 32−21−00−03−075 IPC 32−21−00−03−070 32−21−01 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REF 18 21 22 23 24 25 26 30 32 33 34 35 36 37 38 41 45 46 47 48 NAME OF PART Spacer Cotter pin Nut Washer Bolt Collar Drag brace pin Banjo bolt Preformed packing Screw Cotter pin Nut Washer Bolt Bolt Preformed packing Washer *Refer to text Washer *Refer to text Washer Washer QTY 2 1 1 2 1 1 1 2 4 3 2 2 AR 2 2 4 2* IPC SEQUENCE NO. IPC 32−21−00−03−065 IPC 32−21−05−01−035 IPC 32−21−05−01−030 IPC 32−21−05−01−025 IPC 32−21−05−01−015 IPC 32−21−05−01−040 IPC 32−21−05−01−010 IPC 32−51−00−02−080 IPC 32−51−00−02−085 IPC 32−51−00−02−090 IPC 32−21−00−03−045 IPC 32−21−00−03−040 IPC 32−21−00−03−030 IPC 32−21−00−03−020 IPC 32−21−00−03−025 IPC 32−21−00−04−060 IPC 32−21−00−03−060 2* IPC 32−21−00−03−055 1 AR IPC 32−21−05−01−020 IPC 32−21−00−03−035 Subtask 32−21−01−946−001 D. Reference Information REFERENCE TASK 07−11−01−582−804 TASK 12−12−32−610−804 TASK 12−20−32−640−801 TASK 29−00−00−910−801 TASK 29−10−00−870−803 TASK 32−22−01−980−802 TASK 32−30−00−720−801 TASK 32−33−05−820−801 TASK 32−42−01−400−801 TASK 32−51−00−720−801 DESIGNATION Removal of the Aircraft from Jacks Servicing of the NLG Shock Strut With Jacks Lubrication of the Nose Landing Gear Hydraulic Safety Precautions Bleed Hydraulic System No. 3 Close the Nose−Landing−Gear Forward Doors Functional Test of the Landing Gear Extension/Retraction System Alignment of the NLG Uplock Pin with the NLG Uplock Assembly Installation of the Nosewheel/Tire Assembly Functional Test of the Nosewheel Steering Master EFFECTIVITY: See Pageblock 32−21−01 page 401 408 32−21−01 SepPage 10/2004 C AIRCRAFT MAINTENANCE MANUAL 2. Job Set−Up Subtask 32−21−01−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Subtask 32−21−01−910−001 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: B. 3. Procedure Subtask 32−21−01−420−001 Refer to Figure 401. A. Do the steps that follow to install the NLG shock strut (43): NOTE: In the steps that follow, where a quantity given in the parts reference table (in the Job Set−up part of this procedure) is shown as AR, it is permissible to use: ± a maximum of four washers to align the cotter pin hole ± a maximum of two washers under the bolt head ± a maximum of two washers under the nut. One washer must be used under the nut. NOTE: Where different thicknesses of washers are listed, any combination of thicknesses can be used. (1) Make sure that the trunnion pins (42), the bushings (44), and the related bushings in the nosewheel well are clean. (2) With the NLG shock strut (43) in the dolly support stand, align the inner bores of the bushings (44) at the top of the NLG shock strut (43) with the inner bores of the bushings in the nosewheel well. (3) Lightly lubricate the trunnion pins (42) with 04−005 grease. (4) Insert the trunnion pins (42) into the nose gear bushings (44) and the nose wheel−well bushings. (5) Lightly lubricate the preformed packings (41) with 04−005 grease. Install the preformed packings (41) on the grease inserts (39) and (40). (6) Install the preformed packings (41) on the grease inserts (39) and (40). (7) Install the two grease insert assemblies (39) and (40) into the trunnion pins (42). NOTE: The grease insert (39) is installed in the right trunnion pin (42). (8) Align the bolt holes of the NLG shock strut (43), the trunnion pins (42), and the grease inserts (39) and (40). (9) Lightly lubricate the two bolts (37) and (38) with 04−005 grease. (10) Make sure the total clearance of both gaps between the NLG bushings (44) and the aircraft structure bushings is 0.015−0.030 in. (0.371−0.762 mm). Master EFFECTIVITY: See Pageblock 32−21−01 page 401 409 32−21−01 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL (11) For each trunnion pin assembly, install the two bolts (37) and (38), the washers (36) and (48), and the nut (35). NOTE: The bolt (37) for the right side of the gear is shorter than the bolt (38) for the left side of the gear. Make sure that the bolts (37) and (38) are installed in the correct locations. NOTE: Install the bolts (37) and (38) so that the head of the bolt is adjacent to the forward side of the NLG shock strut (43). (12) Torque the nuts (35) from 40 to 50 lbf·in (4.52 to 5.65 N·m). (13) Safety the nuts (35) with the cotter pins (34). (14) Lightly lubricate the preformed packings (32) with clean 02−001 hydraulic fluid or with 06−014 hydraulic assembly lubricant. (15) Put a preformed packing on each side of the banjo bolt fittings of the swivel assembly (29). (16) Align the two banjo bolt fittings of the swivel assembly (29) with the related ports of the electrohydraulic module (31). NOTE: The ports are identified as P and R in the steering manifold part of the electrohydraulic module (31). (17) Lightly lubricate the screws (33) with 04−005 grease. (18) Align the top of the swivel assembly (29) with the grease insert (39). NOTE: If necessary, you can loosely attach the swivel assembly (29) to the grease insert (39) with a screw (33) to hold it in position. (19) Attach the two banjo bolt fittings of the swivel assembly (29) to the electrohydraulic module (31) with the banjo bolts (30). NOTE: Make sure that the preformed packings (32) are in the correct position. (20) Attach the swivel assembly (29) with the screws (33) to the grease insert (39). (21) Torque the banjo bolts (30) from 140 to 150 lbf·in (15.82 to 16.95 N·m). (22) Safety the banjo bolts (30) with 05−005 lockwire. (23) Torque the screws (33) from 25 to 30 lbf·in (2.8 to 3.4 N·m). (24) Safety the screws (33) with 05−005 lockwire. (25) Remove the protective plugs/caps from the hydraulic lines (27) and (28) and from the swivel assembly (29). (26) Lightly lubricate the threads for the hydraulic lines (27) and (28) on the swivel assembly (29) with clean 02−001 hydraulic fluid or with 06−014 hydraulic assembly lubricant. (27) Connect the hydraulic lines (27) and (28) to the swivel assembly (29). NOTE: Make sure that the hydraulic lines (27) and (28) are connected to the correct ports of the swivel assembly (29). B. Install the disconnected drag brace (20) on the NLG shock strut (43) as follows: (1) Lightly lubricate the inner bore of the bushing at the bottom of the drag brace (20), the inner bores of the related bushings in the lugs on the NLG shock strut (43), and the drag brace pin (26) with 04−005 grease. (2) Align the inner bore of the bushing at the bottom of the drag brace (20) with the inner bores of the related bushings in the lugs on the NLG shock strut (43). Master EFFECTIVITY: See Pageblock 32−21−01 page 401 410 32−21−01 AugPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (3) (4) (5) (6) (7) (8) (9) (10) C. D. E. F. Install the drag brace pin (26). Lightly lubricate the bolt (24) with 04−005 grease. Install the collar (25), the bolt (24), the washers (47) and (23), and the nut (22). Torque the nut (22) from 25 to 30 lbf·in (2.8 to 3.4 N·m). Safety the nut (22) with the cotter pin (21). Install the spring assemblies (19) on the drag brace (20). Install the spacers (18), the washers (45) and (46), and the nuts (17). Adjust the nuts (17) until the ends of the springs have a lateral play of 0.010−0.030 in. (0.25−0.76 mm). NOTE: If the cotter pin hole cannot be aligned with the slot in the nut (17), one or both of the washers (45) and (46) can be removed. Make sure that the specified lateral play is maintained. (11) Safety the nuts (17) with the cotter pins (16). Install the disconnected extension/retraction actuator (15) on the NLG shock strut (43) as follows: (1) Lightly lubricate the inner bore of the aft bushing of the extension/retraction actuator (15), the inner bores of the bushings in the related attachment lugs on the NLG shock strut (43), and the actuator pin (14) with 04−005 grease. (2) Put the extension/retraction actuator (15) between its related attachment lugs on the NLG shock strut (43). (3) Align the inner bores of the bushings. (4) Install the actuator pin (14). (5) Align the hole of the retaining plate (13) with the related hole in the lug of the NLG shock strut (43). (6) Lightly lubricate the bolt (10) with 04−005 grease. (7) Install the bolt (10) with its washers (12) and (11). (8) Install the washers (9) and (8), and the nut (7). (9) Torque the bolt (10) from 25 to 30 lbf·in (2.82 to 3.39 N·m). (10) Safety the nut (7) with the cotter pin (6). Attach the disconnected control rods (5) to the NLG shock strut (43) as follows: (1) Lightly lubricate the two bolts (4) with 04−005 grease. (2) Attach each control rod (5) to the NLG shock strut (43) with the bolt (4), the washers (3), and the nut (2). (3) Safety the nut (2) with the cotter pin (1). Remove the protective plugs/caps from the P62 electrical connector (49), the P4GC electrical connector (50), and the P63 electrical connector (51) and their related receptacles. Connect the P62 electrical connector (49), the P4GC electrical connector (50), and the P63 electrical connector (51) to their related receptacles in the nosewheel well. Master EFFECTIVITY: See Pageblock 32−21−01 page 401 411 32−21−01 SepPage 10/2004 C AIRCRAFT MAINTENANCE MANUAL 4. Close Out Subtask 32−21−01−865−001 A. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−4 CB NO. A2 F6 F7 F8 G11 A2 F8 F9 G15 P2 P3 B13 NAME HYD PUMP 3B PROX SENS LGC/D1 PROX SENS WOW 1 NOSE STEER HYD SYST AC PUMP CONT 3B HYD PUMP 3A NOSE STEER PROX SENS WOW 2 HYD SYST AC PUMP CONT 3A PROX SENS LGC/D1 PROX SENS LGC/D2 WOW 1 + 2 PROX SENS LGC/D2 ZONE 221 221 221 221 221 222 222 222 222 222 222 222 Subtask 32−21−01−640−001 B. Lubricate the NLG (Ref. TASK 12−20−32−640−801). Subtask 32−21−01−410−001 C. Install the nosewheel/tire assemblies (Ref. TASK 32−42−01−400−801). Subtask 32−21−01−614−001 D. Pressurize the shock strut with nitrogen (Ref. TASK 12−12−32−610−804). Subtask 32−21−01−870−001 E. Bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−21−01−820−001 F. Do an alignment of the NLG uplock pin with the NLG uplock assembly (Ref. TASK 32−33−05−820−801). Subtask 32−21−01−720−001 G. Do an functional test of the extension and retraction system (Ref. TASK 32−30−00−720−801). Subtask 32−21−01−720−002 H. Do a functional test of the nosewheel steering system (Ref. TASK 32−51−00−720−801). Master EFFECTIVITY: See Pageblock 32−21−01 page 401 412 32−21−01 SepPage 10/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−01−210−001 I. Examine the hydraulic connections and the work area for leaks. Subtask 32−21−01−586−001 J. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−21−01−410−002 K. Close the NLG forward doors (Ref. TASK 32−22−01−980−802). Subtask 32−21−01−941−001 L. Remove all tools, equipment, safety placards, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−21−01 page 401 413 32−21−01 SepPage 10/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL SHOCK STRUT, NOSE LANDING GEAR − ADJUSTMENT/TEST 1. General A. The maintenance procedure that follows is for the functional test of the nose landing gear (NLG) shock strut. TASK 32−21−01−720−801 Functional Test of the Nose Landing Gear (NLG) Shock Strut Extension 1. Reason for the Job Refer to MRB 32−00−00−11. 2. Job Set−Up Information Subtask 32−21−01−943−005 A. Tools and Equipment REFERENCE 14−6805−8000 DESIGNATION Gauge kit − strut/accumulator nitrogen servicing Subtask 32−21−01−944−002 B. Consumable Materials REFERENCE 05−002 DESIGNATION Nitrogen, technical Subtask 32−21−01−946−003 REFERENCE TASK 12−12−32−610−803 DESIGNATION Servicing (Oil and Nitrogen) of the NLG Shock Strut − A/C on the Ground 3. Procedure Subtask 32−21−01−720−003 Refer to Figure 501 and Figure 502. A. Do a functional check of the NLG shock strut extension as follows: (1) Measure and record the chrome extension of the NLG shock strut (dimension ‘X’). (2) Remove the dust cap from the nitrogen charging valve at the top of the shock strut. (3) Connect the gauge kit to the nitrogen charging valve. (4) Slowly turn the thin nut on the nitrogen charging valve to the open position and read the pressure on the pressure gauge. Master EFFECTIVITY: See Pageblock 32−21−01 page 501 501 32−21−01 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL (5) If the ambient temperature is 41°F to 77°F (5°C to 25°C), refer to the NLG−shock−strut service plate and find the correct extension for the shock strut as follows: (a) On the service plate, find the pressure gauge reading on the vertical scale (PRESSURE GAUGE READING (PSI)). (b) From the pressure reading, go across horizontally to the area (range) between the two lines of the SERVICING CURVE. (c) From this range, between the lines of the SERVICING CURVE, go down vertically to the ‘X’ DIMENSION (INCHES) scale. (d) Record the range from the ‘X’ DIMENSION (INCHES) scale. (6) If the ambient temperature is −65°F to 86°F (−54°C to 30°C), refer to the alternate NLG servicing curve (Refer to Figure 502) and find the correct extension for the shock strut as follows: (a) On the alternate NLG servicing curve, find the pressure gauge reading on the vertical scale (strut pressure (X 10³ PSI)). (b) From the pressure reading, go across horizontally to a point on the servicing curve depending on the ambient temperature. (c) From this point on the servicing curve, go down vertically to the ‘Exposed Chrome (in.)’ scale. (d) Record the reading from the ‘Exposed Chrome (in.)’ scale. (7) If the chrome extension measurement (dimension ‘‘X’’) is in the limits found on the charts, the shock strut extension is good and servicing is not necessary. Do the steps that follow: (a) Close the thin nut. (b) Slowly disconnect the gauge kit from the nitrogen charging valve. (c) Install the dust cap on the nitrogen charging valve. (8) If the extension is not correct, service the NLG shock strut with oil and nitrogen (Ref. TASK 12−12−32−610−803). 4. Close Out Subtask 32−21−01−943−006 A. Remove all tools, equipment and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−21−01 page 501 502 32−21−01 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Dust cap. 2. Nitrogen charging valve. 3. Thin nut. A NOTE X = Chrome Extension. 1 SERVICE PLATE 2 3 COVER B X B A NOSE LANDING GEAR ram1212323_006.dc, pb, 02/10/95 SHOCK STRUT ASSEMBLY Nose Landing Gear (NLG) Shock Strut Extension − Functional Test Figure 501 Master EFFECTIVITY: See Pageblock 32−21−01 page 501 503 32−21−01 DecPage 15/2004 C LOAD ( X 10 3 LBS ) 0 2 4 6 8 10 12 14 16 18 STRUT PRESSURE ( X 103 PSI ) EXPOSED CHROME ( in. ) ram1212323_010.dg, jp, 15/10/99 0.0 0.5 1.0 1.5 2.0 2.5 3.0 0.0 −30 30 2.0 15 −54 0 −15 4.0 6.0 8.0 10.0 12.0 14.0 16.0 AIRCRAFT MAINTENANCE MANUAL Alternate NLG Servicing Curves Figure 502 Master EFFECTIVITY: See Pageblock 32−21−01 page 501 504 32−21−01 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL SHOCK STRUT, NOSE LANDING GEAR (NLG) − INSPECTION/CHECK 1. General A. The maintenance procedure that follows is the detailed inspection of the NLG shock strut extension. TASK 32−21−01−220−801 Detailed Inspection of the NLG Shock Strut Extension 1. Reason for the Job Refer to MRB 32−00−00−11. 2. Job Set−Up Information Subtask 32−21−01−943−004 A. Tools and Equipment REFERENCE 14−6805−8000 DESIGNATION Gauge kit, strut/accumulators nitrogen servicing Subtask 32−21−01−944−004 B. Consumable Materials REFERENCE 05−002 DESIGNATION Nitrogen, technical Subtask 32−21−01−946−004 C. Reference Information REFERENCE TASK 12−12−32−220−802 DESIGNATION Extension Check and Adjustment (with Nitrogen) of the NLG Shock Strut 3. Procedure Subtask 32−21−01−220−001 A. Do the check of the exposed chrome of the NLG shock−strut piston for correct extension as follows: NOTE: This procedure is applicable only if the ambient temperature is 41°F to 77°F (5°C to 25°C). If the ambient temperature is not 41°F to 77°F (5°C to 25°C), refer to TASK 12−12−32−220−802. (1) Measure the extension of the shock strut chrome to get dimension X. (2) Remove the dust cap from the nitrogen charging valve. Master EFFECTIVITY: See Pageblock 32−21−01 page 601 32−21−01 Page 601 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL B. (3) Connect the gauge kit to the nitrogen charging valve. (4) Slowly turn the thin nut on the nitrogen charging valve to the open position and read the pressure on the pressure gauge. (5) Find the shock strut pressure on the side scale of the servicing placard graph. Read the graph to find the permitted extension (dimension X) of the shock strut chrome for the shock strut pressure. (6) If the chrome extension measurement (dimension ‘‘X’’) is in the limits found on the ‘‘X’’ DIMENSION (INCHES) scale, the shock strut extension is good and servicing is not necessary. (7) Close the thin nut. (8) Remove the gauge kit from the nitrogen charging valve. (9) Install the dust cap on the nitrogen charging valve. If the extension is not correct, service the NLG shock strut (Ref. TASK 12−12−32−220−802). 4. Close Out Subtask 32−21−01−943−002 A. Remove all tools, equipment and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−21−01 page 601 32−21−01 Page 602 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL DRAG BRACE, NOSE LANDING GEAR (NLG) − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the nose−landing−gear (NLG) drag brace. The NLG drag brace is connected to the forward side of NLG shock strut and to the NLG wheel−well structure. TASK 32−21−05−000−801 Removal of the NLG Drag Brace 1. Job Set−Up Information Subtask 32−21−05−943−001 A. Tools and Equipment REFERENCE None specified 460004243 DESIGNATION Container, resistant to phosphate ester base hydraulic fluid Extractor − Drag−brace trunnion−pin Subtask 32−21−05−944−001 B. Consumable Materials REFERENCE 05−001 11−004 DESIGNATION Cloths, cleaning, low−lint Alcohol, isopropyl Subtask 32−21−05−946−001 C. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 29−00−00−910−801 TASK 32−22−01−980−801 DESIGNATION Put the Aircraft on Jacks Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions Open and Isolate the Nose−Landing−Gear Forward Doors Master EFFECTIVITY: See Pageblock 32−21−05 page 401 32−21−05 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 2. Job Set−Up Subtask 32−21−05−941−002 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. Subtask 32−21−05−930−001 INSTALL A WARNING PLACARD ON THE LANDING−GEAR CONTROL PANEL. OPERATION OF THE LANDING GEAR CAN CAUSE INJURIES. Install a DO NOT OPERATE THE LANDING GEAR safety placard on the landing−gear control panel in the flight compartment. WARNING: B. Subtask 32−21−05−910−001 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: C. Subtask 32−21−05−010−001 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the nose−landing−gear forward doors (Ref. TASK 32−22−01−980−801). WARNING: D. Subtask 32−21−05−863−002 E. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Master EFFECTIVITY: See Pageblock 32−21−05 page 401 32−21−05 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−05−865−001 F. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−4 CB NO. A2 F6 F7 F8 G11 A2 F8 F9 G15 P2 P3 B13 NAME HYD PUMP 3B PROX SENS LGC/D1 PROX SENS WOW 1 NOSE STEER HYD SYST AC PUMP CONT 3B HYD PUMP 3A NOSE STEER PROX SENS WOW 2 HYD SYST AC PUMP CONT 3A PROX SENS LGC/D1 PROX SENS LGC/D2 WOW 1 + 2 PROX SENS LGC/D2 ZONE 221 221 221 221 221 222 222 222 222 222 222 222 Subtask 32−21−05−582−001 G. Put the aircraft on jacks (Ref. TASK 07−11−01−582−801). 3. Procedure Subtask 32−21−05−020−002 A. Remove the drag brace assembly (1) from the NLG as follows: Subtask 32−21−05−030−003 Refer to Figure 401. B. Disconnect the top end of the NLG extension/retraction actuator from the drag brace assembly (1) as follows: (1) Remove and discard the cotter pin (2). (2) Remove the nut (3), and the washers (4) and (5). (3) Remove the bolt (6), the washers (4) and (5), and the retaining plate (7). (4) Remove the pin (8), and disconnect the extension/retraction actuator from the drag brace (1). (5) With a piece of string or lockwire, safety the end of the actuator to a structural member of the wheel well. Subtask 32−21−05−030−001 Refer to Figure 403. C. Disconnect the electrical connectors (P84) and (P86) of the NLG downlock harnesses, and install protective caps on the connectors and on the receptacles. Master EFFECTIVITY: See Pageblock 32−21−05 page 401 32−21−05 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL D. E. F. Put a container below the hydraulic line connection point. Disconnect the hydraulic line from the drag brace and install protective caps on the lines. Clean all unwanted hydraulic fluid from the work area with a clean cloth and 11−004 alcohol. Subtask 32−21−05−030−002 Refer to Figure 402. G. Disconnect the spring assemblies (10) from the left and right sides of the drag brace (1) as follows: NOTE: The removal procedure for the left spring assembly is given. The removal procedure for the right spring assembly is the same. (1) Remove and discard the cotter pin (11). (2) Remove the nut (12), the washers (13) and (14), and the spacer (15). WARNING: BE CAREFUL WHEN YOU DISCONNECT THE SPRING ASSEMBLY FROM THE DRAG BRACE. THERE IS TENSION ON THE SPRING ASSEMBLY. ACCIDENTAL RELEASE OF THE TENSION CAN CAUSE INJURIES. (3) Carefully disconnect the spring (10) from the drag brace (1). Subtask 32−21−05−020−001 H. Remove the drag brace (1) from the connection point on the NLG shock strut as follows: (1) Remove and discard the cotter pin (16). (2) Remove the nut (17), the washers (18) and (19), and the bolt (20). (3) Remove the collar (21) and the pin (22). (4) Disconnect the drag brace (1) from the NLG shock strut. Subtask 32−21−05−020−003 I. Remove the drag brace (1) from the NLG−wheel−well connection points as follows: NOTE: The removal procedure for the left connection point is given. The removal procedure for the right connection point is the same. (1) Remove and discard the cotter pin (24). (2) Remove the nut (25), and the washers (26) and (27). (3) Remove the lock pin (28) and the cover (29). (4) Through the slot on the forward side of the drag brace, install a drift or pin punch into the bolt holes of the trunnion pin (30) and grease insert (32). (5) Hold the drag brace (1), and slide each trunnion pin (30) into the drag brace. NOTE: If you can not easily slide the trunnion pins (30) from their mounts, install and use the trunnion−pin extraction tool. (6) Carefully remove the drag brace (1). Master EFFECTIVITY: See Pageblock 32−21−05 page 401 32−21−05 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−05−030−004 J. K. L. Remove the trunnion pins (30) from the drag brace (1). Remove the grease inserts (32) from the trunnion pins (30). Remove and discard the preformed packings (33) and (34). Subtask 32−21−05−030−005 Refer to Figure 403. M. If necessary, remove the downlock harnesses from the drag brace (1) as follows: (1) Identify each downlock harness to its left and right position. (2) From each clamp (36), remove the cotter pin (37), the nut (38), the washers (39) and (40), and the bolt (41). (3) On each side of the drag brace (1), cut and discard the lockwire from the bolt (42). (4) From each position, remove the bolt (42), the spacer (43), and the clamp (44). (5) Remove and discard the lockwire from the jamnuts (45) and (46). (6) Remove the jamnuts (45) from each downlock harness proximity−sensor (PS1GA and PS2GA). (7) Remove each PS1GA and PS2GA proximity sensor (with the keywasher (47) and nut (46)) from the mounting bracket, and remove the downlock harnesses from the drag brace (1). Master EFFECTIVITY: See Pageblock 32−21−05 page 401 32−21−05 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 8 7 5 4 6 EXTENSION/RETRACTION ACTUATOR (REF) LEGEND. 3 2 4 5 1 ram3221054_003 .dg, gg, 23/06/97 1. Drag brace. 2. Cotter pin. 3. Nut. 4. Washer. 5. Washer. 6. Bolt. 7. Retaining plate. 8. Pin. Disconnect/Connect Drag Brace and Extension/Retraction Actuator Figure 401 Master EFFECTIVITY: See Pageblock 32−21−05 page 401 32−21−05 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND. 1. Drag brace. 30 10. Spring. 11. Cotter pin. 12. Nut. 13. Washer. 14. Washer. 15. Spacer. 16. Cotter pin. 17. Nut. 18. Washer. 19. Washer. 20. Bolt. 29 21. Collar. 22. Pin. 28 24. Cotter pin. 25. Nut. 26. Washer. 27. Washer. 28. Pin assembly. 29. Cover. 30. Trunion pin. 32. Grease insert. 33. Preformed packings. 34. Preformed packings. 26 27 24 25 30 34 32 21 33 NLG SHOCK STRUT (REF) 20 18 17 16 15 1 14 13 10 22 12 11 ram3221054_002(2).dg, gg, 24/06/97 19 NLG Drag Brace Assembly − Removal/Installation Figure 402 Master EFFECTIVITY: See Pageblock 32−21−05 page 401 32−21−05 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL DOWNLOCK HARNESSES 11 1 LEGEND 1. Drag brace. 36. Clamp. 37. Cotter pin. 38. Nut. 39. Washer. 40. Washer. 41. Bolt. 42. Bolt. 43. Spacer. 44. Clamp. 45. Jamnut. 46. Jamnut. 47. Keywasher. 41 39 40 36 41 39 40 36 38 40 39 41 39 40 36 40 PROTECTIVE SLEEVE (TYPICAL 6 PLACES) 42 39 38 41 39 44 37 43 45 37 40 36 40 39 38 43 37 BRACKET (REF) 47 ram3221054_001(3).dg, gg, 23/06/97 44 42 46 NLG Downlock Harnesses − Removal/Installation Figure 403 Master EFFECTIVITY: See Pageblock 32−21−05 page 401 32−21−05 Page 408 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−21−05−400−801 Installation of the NLG Drag Brace 1. Job Set−Up Information Subtask 32−21−05−943−002 A. Tools and Equipment REFERENCE None specified DESIGNATION Torque wrench, torque range 0−150 pound−inches (0−17 N·m) Subtask 32−21−05−944−002 B. Consumable Materials REFERENCE 04−005 05−004 DESIGNATION Grease Lockwire Subtask 32−21−05−945−001 C. Parts REF 2 3 4 5 6 11 12 13 14 15 16 17 18 19 20 24 25 26 27 28 29 NAME OF PART Cotter pin Nut Washer Washer Bolt Cotter pin Nut Washer Washer Spacer Cotter Pin Nut Washer Washer Bolt Cotter Pin Nut Washer Washer Pin assembly Cover Master EFFECTIVITY: See Pageblock 32−21−05 page 401 QTY 1 1 2 2 1 2 2 2 2 2 1 1 1 1 1 2 2 2 2 2 2 IPC SEQUENCE NO. IPC 32−33−01−01−040 IPC 32−33−01−01−035 IPC 32−33−01−01−030 IPC 32−33−01−01−025 IPC 32−33−01−01−020 IPC 32−21−00−03−075 IPC 32−21−00−03−070 IPC 32−21−00−03−060 IPC 32−21−00−03−055 IPC 32−21−00−03−065 IPC 32−21−05−01−035 IPC 32−21−05−01−030 IPC 32−21−05−01−025 IPC 32−21−05−01−020 IPC 32−21−05−01−015 IPC 32−21−05−01−070 IPC 32−21−05−01−065 IPC 32−21−05−01−055 IPC 32−21−05−01−060 IPC 32−21−05−01−050 IPC 32−21−05−01−080 32−21−05 Page 409 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REF 33 34 36 37 38 39 40 41 42 43 44 45 46 47 NAME OF PART Preformed packing Preformed packing Clamp Cotter pin Nut Washer Washer Bolt Bolt Spacer Clamp Jam nut Jam nut Keywasher QTY 4 4 4 4 4 8 8 4 2 2 2 2 2 2 IPC SEQUENCE NO. IPC 32−21−05−01−095 IPC 32−21−05−01−090 IPC 32−21−00−05−170 IPC 32−21−00−05−200 IPC 32−21−00−05−195 IPC 32−21−00−05−185 IPC 32−21−00−05−190 IPC 32−21−00−05−175 IPC 32−21−00−05−180 IPC 32−21−00−05−205 IPC 32−21−00−05−170 IPC 32−61−05−02−080 IPC 32−61−05−02−080 IPC 32−61−05−02−075 Subtask 32−21−05−946−002 D. Reference Information REFERENCE TASK 07−11−01−582−804 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−20−32−640−801 TASK 29−10−00−870−803 TASK 32−00−00−790−801 TASK 32−22−01−980−801 TASK 32−22−01−980−802 TASK 32−30−00−720−801 TASK 32−61−00−740−801 TASK 51−26−00−110−801 DESIGNATION Removal of the Aircraft from Jacks Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Lubrication of the Nose Landing Gear Bleed Hydraulic System No. 3 External Leak Check of the Landing Gear Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors Functional Test of the Landing Gear Extension/Retraction System Power−Up Test of the PSS Solvent Cleaning 2. Job Set−Up Subtask 32−21−05−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Master EFFECTIVITY: See Pageblock 32−21−05 page 401 32−21−05 Page 410 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−05−110−001 B. Make sure that all of the drag brace components, and component mounting areas of the NLG, are clean. If necessary, clean the applicable parts and areas (Ref. TASK 51−26−00−110−801). 3. Procedure Subtask 32−21−05−430−003 Refer to Figure 403. A. If removed, install the downlock harnesses on the drag brace as follows: (1) Install the jamnuts (46) on the downlock harness proximity−sensors (PS1GA and PS2GA). (2) Put the PS1GA and PS2GA proximity sensors (with the keywasher (47) and the nut (46) installed) of the left and right downlock harnesses through the mounting holes of the bracket. NOTE: Make sure that the left and right downlock harnesses are installed on the correct sides of the drag brace. (3) Install the jamnuts (45), but do not adjust the PS1GA and PS2GA proximity sensors at this time. Tighten the jamnuts (45) by hand. NOTE: Make sure that the tab on the keywasher (47) correctly engages in the alignment hole in the bracket. (4) On the sides of the drag brace (1), attach each downlock harness with the clamp (44), the spacer (43), and bolt (42). NOTE: There are protective heat−shrink sleeves installed at specific locations on the harnesses. For the correct location of each clamp, install them on the protective sleeves. (5) Safety the bolts (42) with 05−004 lockwire. (6) Install the clamps (36) over the protective sleeves on the downlock harnesses. (7) Attach each clamp (36) to the drag brace hydraulic−line with the bolt (41), the washers (39) and (40), and the nut (38). NOTE: Use a maximum of two washers (39) or (40) under the bolt head and two washers (39) or (40) under the nut, as required, to align the cotter pin hole. (8) Torque each nut (38) to 10−15 pound−inches (1.13−1.7 N·m). (9) Safety the nuts (38) with the cotter pins (37). Subtask 32−21−05−430−004 Refer to Figure 402. B. Install the grease inserts (32) and the trunnion pins (30) in the drag brace (1) as follows: NOTE: The installation procedure for left side is given. The installation procedure for the right side is the same. Master EFFECTIVITY: See Pageblock 32−21−05 page 401 32−21−05 Page 411 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (1) Lubricate the preformed packings (34) with 04−005 grease and install them in the bolt hole of the grease insert (32). (2) Lubricate the preformed packings (33) with 04−005 grease and install them on the grease insert (32). (3) Carefully install the grease insert (32), with the lock pin holes first, into the trunnion pin (30). NOTE: Before you install the grease insert (32), turn it to align the lockpin holes with the lock pin holes in the trunnion pin (30). (4) Apply a thin layer of 04−005 grease to the trunnion pin (30). (5) Install the trunnion pin (30), with the lock pin holes first, into the drag brace (1). NOTE: Before you install the trunnion pin (30), turn it to align the lockpin holes with the slot and lock pin hole in the drag brace (1). (6) Push the trunnion pin (30) into the drag brace until the outer end of the trunnion pin is smooth with, or recessed from, the outer face of the drag brace bushing. Subtask 32−21−05−420−001 C. Install the drag brace assembly (1) to the NLG−wheel−well connection points as follows: (1) Put the drag brace (1) in position in the NLG−wheel−well, with the extension/retraction actuator connection−point on the left side. (2) Align the trunnion pins (30) with the wheel−well mounting holes. (3) Install a drift, or pin punch, through the drag brace slots, and through the lock pin holes of the trunnion pins (30) and grease inserts (32). NOTE: Carefully put the drift or pin punch into the grease inserts to prevent damage to the preformed packings. (4) Slide each trunnion pin (30) into the wheel−well mounting holes. (5) Install the lock pins (28) as follows: NOTE: The installation procedure for the left lock pin is given. The installation procedure for the right lock pin is the same. (a) Install the cover (29) on the lock pin (28). Make sure that the lock tab on the cover is against the flat side of the lock pin head. (b) Apply a thin layer of 04−005 grease to the threads and shank of the lock pin (28). (c) Carefully install the lockpin (28) through the drag brace slot and through the holes of the trunnion pin (30) and grease insert (32). NOTE: Make sure that the cover (29) is correctly engaged in the drag brace slot. The lock tab on the cover goes against the flat side of the lock pin head and the assembly goes installed with the lock tab outboard. (d) Install the washers (27) and (26), and the nut (25). NOTE: Use a maximum of two washers (26) or (27) under the nut, as required, to align the cotter pin hole. Install a minimum of one washer under the nut. (e) Torque the nut (25) to 40−50 pound−inches (4.5−5.7 N·m). Master EFFECTIVITY: See Pageblock 32−21−05 page 401 32−21−05 Page 412 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (f) Safety the nut (25) with the cotter pin (24). Subtask 32−21−05−420−002 D. Install the drag brace (1) to the connection point on the NLG shock strut as follows: (1) Install a thin layer of 04−005 grease to the pin (22). (2) Align the holes of the drag brace (1) and the connection point on the NLG shock strut. (3) Install the pin (22) from the left side of the NLG. Make sure that the flat side of the head is against the machined flat on the NLG. (4) Install the collar (21) on the pin (22) and align the bolt holes. (5) Install the bolt (20) down through the collar (21) and pin (22). (6) Install the washers (19) and (18), and the nut (17). (7) Torque the nut (17) to 25−30 pound−inches (2.8−3.4 N·m). (8) Safety the nut (17) with the cotter pin (16). Subtask 32−21−05−430−002 E. Install the spring assemblies (10) on the left and right sides of the drag brace (1) as follows: NOTE: The installation procedure for the left spring assembly is given. The installation procedure for the right spring assembly is the same. (1) Install the end of the spring (10) over the drag brace bolt. NOTE: The face of the bushing, that is installed in the end of the spring, goes inboard. (2) Install the spacer (15), the washers (14) and (13), and the nut (12). (3) Adjust the nut (12) until the lateral play of the spring, on the drag brace bolt, is 0.010−0.030 inch (0.25−0.76 mm). (4) Safety the nut (12) with the cotter pin (11). Subtask 32−21−05−430−005 Refer to Figure 403. F. Remove the protective caps and install the hydraulic line to the hydraulic connection point on the drag brace (1). G. Remove the protective caps and connect the NLG downlock harness electrical−connectors P84 and P86 to their respective receptacles at FS 212. Subtask 32−21−05−410−003 Refer to Figure 401. H. Connect the top end of the NLG extension/retraction actuator to the drag brace assembly (1) as follows: (1) Align the actuator end with the connection point on the drag brace (1). (2) Apply a thin layer of 04−005 grease to the pin (8). Master EFFECTIVITY: See Pageblock 32−21−05 page 401 32−21−05 Page 413 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (3) Install the pin (8). (4) Install the retaining plate (7), the washers (5) and (4), and the bolt (6). NOTE: Make sure that the flat sides on the head of the pin (8) are correctly engaged with the contour of the retaining plate (7). (5) Install the washers (5) and (4), and the nut (3). (6) Torque the nut (3) to 25−30 pound−inches (2.8−3.4 N·m). (7) Safety the nut (3) with the cotter pin (2). Subtask 32−21−05−820−001 Refer to Figure 403. I. Adjust the NLG downlock−harness proximity sensors PS1GA and PS2GA as follows: (1) Make sure that the NLG is at the fully down and locked position. (2) Install the NLG lockpin in the drag brace (1). (3) Adjust the jamnuts (45) and (46) to get a clearance of 0.060−0.070 inch (1.52−1.78 mm) between the face of each PS1GA and PS2GA proximity sensor and its related target. (4) Torque each jamnut (45) to 110−120 pound−inches (12.43−13.56 N·m). (5) Make sure that the sensor/target clearances have not changed. (6) Safety the jamnuts (45) and (46) together with 05−004 lockwire. 4. Close Out Subtask 32−21−05−640−001 A. Lubricate the NLG drag brace (Ref. TASK 12−20−32−640−801). Subtask 32−21−05−865−002 B. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−4 CB NO. A2 F6 F7 F8 G11 A2 F8 F9 G15 P2 P3 B13 NAME HYD PUMP 3B PROX SENS LGC/D1 PROX SENS WOW 1 NOSE STEER HYD SYST AC PUMP CONT 3B HYD PUMP 3A NOSE STEER PROX SENS WOW 2 HYD SYST AC PUMP CONT 3A PROX SENS LGC/D1 PROX SENS LGC/D2 WOW 1 + 2 PROX SENS LGC/D2 Master EFFECTIVITY: See Pageblock 32−21−05 page 401 32−21−05 ZONE 221 221 221 221 221 222 222 222 222 222 222 222 Page 414 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−05−870−001 C. Bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−21−05−869−002 D. Close the NLG forward doors (Ref. TASK 32−22−01−980−802). Subtask 32−21−05−720−001 E. Do a functional test of the landing−gear extension/retraction system (Ref. TASK 32−30−00−720−801). Subtask 32−21−05−010−003 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the nose−landing−gear forward doors (Ref. TASK 32−22−01−980−801). WARNING: F. Subtask 32−21−05−790−001 G. Examine the work area and the hydraulic connections for leaks (Ref. TASK 32−00−00−790−801). Subtask 32−21−05−210−002 H. Do a visual inspection of the drag brace assembly for general condition and correct operation. Make sure that the electrical harnesses are not twisted or damaged. Subtask 32−21−05−490−001 I. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Subtask 32−21−05−582−002 J. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Master EFFECTIVITY: See Pageblock 32−21−05 page 401 32−21−05 Page 415 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−05−869−003 K. Close the NLG forward doors (Ref. TASK 32−22−01−980−802). Subtask 32−21−05−941−001 L. Remove all tools, equipment, safety placards, and unwanted materials from the work area. Subtask 32−21−05−740−001 M. Do a power−up test of the proximity sensor system (Ref. TASK 32−61−00−740−801). Master EFFECTIVITY: See Pageblock 32−21−05 page 401 32−21−05 Page 416 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL ASSEMBLY, TORQUE LINK − MAINTENANCE PRACTICES 1. General A. The maintenance procedure that follows is for the operational test of the nose landing gear (NLG) torque−link assembly. TASK 32−21−10−710−801 Operational Test of the Torque Link Assembly 1. Job Set−Up Information Subtask 32−21−10−946−005 A. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−20−32−640−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Lubrication of the Nose Landing Gear 2. Job Set−Up Subtask 32−21−10−941−005 WARNING: A. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). 3. Procedure **ON A/C 7003−7067, 7069−7273 Pre VSBM−DT−16040−32−12 Subtask 32−21−10−710−005 A. Do an operational test of the torque−link assembly as follows: WARNING: HOLD THE TOP TORQUE LINK WHEN YOU RELEASE THE QUICK DISCONNECT PINS. THE TOP TORQUE LINK IS SPRING LOADED AND WILL MOVE UP QUICKLY. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT. (1) Pull the quick−disconnect handles and make sure that the torque link assembly disconnects smoothly. (2) Make sure that, when released, the quick−disconnect handles go back to their initial position. Master EFFECTIVITY: See Pageblock 32−21−10 page 201 32−21−10 Page 201 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (3) Make sure that the bottom torque link lowers freely and the top torque link goes up by spring tension. (4) Connect the torque links and make sure that the torque−link quick−disconnect assembly engages smoothly. **ON A/C 7274−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7273 Post VSBM−DT−16040−32−12 Subtask 32−21−10−710−007 B. Do an operational test of the torque−link assembly as follows: WARNING: HOLD THE TOP TORQUE LINK WHEN YOU RELEASE THE QUICK DISCONNECT PINS. THE TOP TORQUE LINK IS SPRING LOADED AND WILL MOVE UP QUICKLY. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT. (1) Pull the quick−disconnect handles and make sure that the torque link assembly disconnects smoothly. (2) Make sure that, when released, the quick−disconnect handles go back to their initial position. (3) Make sure that the bottom torque link lowers freely and the top torque link goes up by spring tension. (4) Rotate the lower torque link by hand to its maximum vertical position. Release the lower torque link and make sure that: ± The torsion spring on the NLG jacking pad can move the lower torque link to approximately 10 degrees aft of vertical ± The lower torque link continues to to rotate until it hits its lower stop. (5) Connect the torque links and make sure that the torque−link quick−disconnect assembly engages smoothly. **ON A/C ALL Subtask 32−21−10−640−003 C. If the torque link assembly does not smoothly release and engage, inspect it for condition and damage. If no damage is found, lubricate the quick−disconnect assembly (Ref. TASK 12−20−32−640−801) and do the operational test again. Master EFFECTIVITY: See Pageblock 32−21−10 page 201 202 32−21−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL ASSEMBLY, TORQUE LINK − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the torque link assembly and NLG torque link quick release assembly. The torque link assembly is installed on the nose landing gear (NLG). TASK 32−21−10−000−801 Removal of the Torque Link Assembly 1. Job Set−Up Information Subtask 32−21−10−946−006 A. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−22−01−980−801 TASK 32−42−01−000−801 DESIGNATION Put the Aircraft on Jacks Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Open and Isolate the Nose−Landing−Gear Forward Doors Removal of the Nosewheel/Tire Assembly 2. Job Set−Up Subtask 32−21−10−490−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. Master EFFECTIVITY: See Pageblock 32−21−10 page 401 32−21−10 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL WARNING: B. IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. If open, isolate the nose−landing−gear forward doors from hydraulic system No. 3 (Ref. TASK 32−22−01−980−801). Subtask 32−21−10−941−002 C. Install a DO NOT OPERATE warning tag on the steering handwheel control unit and the landing−gear control lever. Subtask 32−21−10−865−001 D. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−2 CB NO. F8 F8 NAME NOSE STEER NOSE STEER ZONE 221 222 Subtask 32−21−10−582−001 E. Put the aircraft on jacks (Ref. TASK 07−11−01−582−801). Subtask 32−21−10−010−001 F. Remove the two nose wheel/tire assemblies (Ref. TASK 32−42−01−000−801). 3. Procedure **ON A/C 7003−7067, 7069−7273 Pre VSBM−DT−16040−32−12 Subtask 32−21−10−020−002 Refer to Figure 401. A. Do the steps that follow to remove the torque link assembly (18): WARNING: HOLD THE TOP TORQUE LINK WHEN YOU RELEASE THE QUICK DISCONNECT PINS. THE TOP TORQUE LINK IS SPRING LOADED AND WILL MOVE UP QUICKLY. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT. (1) Pull the quick−disconnect pins on torque link assembly (18) to disconnect the upper and the lower torque links. Master EFFECTIVITY: See Pageblock 32−21−10 page 401 32−21−10 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (2) Remove and discard the cotter pin (1) from the bolt (5). (3) Remove the nut (2), and the washers (3) and/or (4) from the bolt (5). NOTE: There can be more than one washer on the side of the nut (2). (4) Remove the bolt (5) with the countersunk washer (6) from the jacking pad (7) and the torque pin (8). (5) Hold the lower torque link and the jacking pad (7). Remove the torque pin (8) to disconnect the lower torque link and the jacking pad (7) from the axle assembly (9). (6) Remove and discard the cotter pin (10) from the bolt (14). (7) Remove the nut (11), and the washers (12) and/or (13) from the bolt (14). NOTE: There can be more than one washer on the side of the nut (11). (8) Remove the bolt (14) with the washer (15) from the NLG main fitting that holds the torque pin (16) in position. (9) Hold the top torque link. Remove the torque pin (16), the torsion spring (17), and the upper torque link from the NLG. **ON A/C ALL Subtask 32−21−10−020−006 Refer to Figure 403. NOTE: The steps that follow are for the removal of the NLG torque link quick release assembly. This procedure is only applicable to remove the quick release assembly from a removed upper torque link assembly. B. If necessary do the steps that follow to remove the NLG torque link quick release assembly (2) from the upper torque link: WARNING: USE THE APPLICABLE SAFETY EQUIPMENT WHEN YOU DO THIS PROCEDURE. THE QUICK RELEASE ASSEMBLY IS UNDER SPRING PRESSURE. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURY TO YOUR EYES AND OTHER BODY TISSUES. (1) Use a punch and lift the edges of the lock washer (1) installed on the quick release assembly (2). (2) Remove the lock washer (1). (3) Remove the quick release assembly (2). **ON A/C 7274−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7273 Post VSBM−DT−16040−32−12 Subtask 32−21−10−020−003 Refer to Figure 402. C. Do the steps that follow to remove the torque link assembly (20): WARNING: HOLD THE TOP TORQUE LINK WHEN YOU RELEASE THE QUICK DISCONNECT PINS. THE TOP TORQUE LINK IS SPRING LOADED AND WILL MOVE UP QUICKLY. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT. (1) Pull the quick−disconnect pins on torque link assembly (20) to disconnect the upper Master EFFECTIVITY: See Pageblock 32−21−10 page 401 403 32−21−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (2) (3) (4) (5) (6) (7) (8) (9) (10) (11) and the lower torque links. Remove and discard the cotter pin (1) from the bolt (6). Remove the nut (2), the washers (3) and/or (4), from the bolt (6). NOTE: There can be more than one washer on the side of the nut (2). Make sure that the lower torque link is in a position that causes the least amount of torsion in the torsion spring (11) that is installed on the jacking pad (8). Remove the bracket (5) from the bolt (6). Remove the bolt (6) with the countersunk washer (7) from the jacking pad (8) and the torque pin (9). Hold the lower torque link and the jacking pad (8). Remove the torque pin (9) to disconnect the lower torque link and the jacking pad (8) from the axle assembly (10). If required for other maintenance, remove the torsion spring (11) from the jacking pad (8). Remove and discard the cotter pin (12) from the bolt (16). Remove the nut (13), the washers (14) and/or (15) from the bolt (16). NOTE: There can be more than one washer on the side of the nut (13). Remove the bolt (16) with the washer (17) from the NLG main fitting that holds the torque pin (18) in position. Hold the top torque link. Remove the torque pin (18), the torsion spring (19), and the upper torque link from the NLG. **ON A/C ALL Subtask 32−21−10−020−005 Refer to Figure 403. NOTE: The steps that follow are for the removal of the NLG torque link quick release assembly. This procedure is only applicable to remove the quick release assembly from a removed upper torque link assembly. D. If necessary do the steps that follow to remove the NLG torque link quick release assembly (2) from the upper torque link: WARNING: USE THE APPLICABLE SAFETY EQUIPMENT WHEN YOU DO THIS PROCEDURE. THE QUICK RELEASE ASSEMBLY IS UNDER SPRING PRESSURE. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURY TO YOUR EYES AND OTHER BODY TISSUES. (1) Use a punch and lift the edges of the lock washer (1) installed on the quick release assembly (2). (2) Remove the lock washer (1). (3) Remove the quick release assembly (2). Master EFFECTIVITY: See Pageblock 32−21−10 page 401 32−21−10 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL NOTES 14 15 16 D FW 17 1 If necessary use washer(s) (3 or 4) as required to align the slots of the nut (2) with the cotter pin hole of the bolt (5). A maximum of two washers on the nut side are permitted. 2 If necessary, use washer(s) (12 or 13) as required to align the slots of the nut (11) with the cotter pin hole of the bolt (14). A maximum of two washers on the nut side are permitted. 2 13 12 11 10 FW D LEGEND 18 9 1 2 3 1 ram3221104_001(3).dg, dm/jp, 04/11/98 1. Cotter pin. 2. Nut. 3. Washer. 4. Washer. 5. Bolt. 6. Washer. 7. Jacking pad. 8. Torque pin. 9. Axle assembly. 10. Cotter pin. 11. Nut. 12. Washer. 13. Washer. 14. Bolt. 15. Washer. 16. Torque pin. 17. Torsion spring. 18. Torque link assembly. 4 7 4 6 5 8 Torque Link Assembly − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−21−10 page 401 32−21−10 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL NOTES 16 17 18 1 If necessary use washer(s) (3 or 4) as required to align the slots of the nut (2) with the cotter pin hole of the bolt (6). A maximum of two washers on the nut side are permitted. 2 If necessary, use washer(s) (14 or 15) as required to align the slots of the nut (13) with the cotter pin hole of the bolt (16). A maximum of two washers on the nut side are permitted. D FW 19 2 15 14 13 FW LEGEND D 20 10 1 2 11 3 1 4 5 8 7 6 9 ram3221104_002.dg, dm/jp, 04/11/98 1. Cotter pin. 2. Nut. 3. Washer. 4. Washer. 5. Bracket. 6. Washer. 7. Washer. 8. Jacking pad. 9. Torque pin. 10. Axle assembly. 11. Torsion spring. 12. Cotter pin. 13. Nut. 14. Washer. 15. Washer. 16. Bolt. 17. Washer. 18. Torque pin. 19. Torsion spring. 20. Torque link assembly. 12 Torque Link Assembly − Removal/Installation Figure 402 Master EFFECTIVITY: See Pageblock 32−21−10 page 401 32−21−10 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND A 1. Lock washer. 2. Quick release assembly. UPPER TORQUE LINK (REF) 2 1 LOWER TORQUE LINK (REF) 1 ram3221104_003.dg, lr, 28/05/03 2 A NLG Quick Release Assembly − Removal/Installation Figure 403 Master EFFECTIVITY: See Pageblock 32−21−10 page 401 32−21−10 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−21−10−400−801 Installation of the Torque Link Assembly 1. Job Set−Up Information Subtask 32−21−10−943−002 A. Tools and Equipment REFERENCE None specified DESIGNATION Torque wrench, 25−30 pound−inches (2.9−3.3 N·m) Subtask 32−21−10−944−001 B. Consumable Materials REFERENCE None specified 04−005 DESIGNATION Red paint Grease **ON A/C 7003−7067, 7069−7273 Pre VSBM−DT−16040−32−12 Subtask 32−21−10−945−001 C. Parts REF 1 2 3 4 5 6 10 11 12 13 14 15 NAME OF PART Cotter pin Nut Washer Washer Bolt Countersunk washer Cotter pin Nut Washer Washer Bolt Washer QTY 1 1 1 1 1 1 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−21−00−02−085 IPC 32−21−00−02−080 IPC 32−21−00−02−075 IPC 32−21−00−02−070 IPC 32−21−00−02−060 IPC 32−21−00−02−065 IPC 32−21−00−02−045 IPC 32−21−00−02−040 IPC 32−21−00−02−030 IPC 32−21−00−02−035 IPC 32−21−00−02−020 IPC 32−21−00−02−025 **ON A/C 7274−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7273 Post VSBM−DT−16040−32−12 Subtask 32−21−10−945−002 D. Parts Master EFFECTIVITY: See Pageblock 32−21−10 page 401 408 32−21−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL REF 1 2 3 4 6 7 12 13 14 15 16 17 NAME OF PART Cotter pin Nut Washer Washer Bolt Countersunk washer Cotter pin Nut Washer Washer Bolt Washer QTY 1 1 1 1 1 1 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−21−00−02−085 IPC 32−21−00−02−080 IPC 32−21−00−02−077 IPC 32−21−00−02−072 IPC 32−21−00−02−062 IPC 32−21−00−02−065 IPC 32−21−00−02−045 IPC 32−21−00−02−040 IPC 32−21−00−02−030 IPC 32−21−00−02−035 IPC 32−21−00−02−020 IPC 32−21−00−02−025 2 IPC 32−21−00−02−010 **ON A/C ALL Subtask 32−21−10−945−003 E. Parts 1 Lock Washer Subtask 32−21−10−946−002 F. Reference Information REFERENCE TASK 07−11−01−582−804 TASK 12−20−32−640−801 TASK 32−21−10−710−801 TASK 32−22−01−980−802 TASK 32−42−01−400−801 TASK 32−51−00−710−801 TASK 32−61−05−220−801 TASK 32−61−05−820−801 DESIGNATION Removal of the Aircraft from Jacks Lubrication of the Nose Landing Gear Operational Test of the Torque Link Assembly Close the Nose−Landing−Gear Forward Doors Installation of the Nosewheel/Tire Assembly Operational Test of the Nosewheel Steering System − Torque Link Assembly Connected Clearance Check of the Landing Gear Proximity Sensors Adjustment of the Landing Gear Proximity Sensors Master EFFECTIVITY: See Pageblock 32−21−10 page 401 32−21−10 Page 409 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 2. Procedure Subtask 32−21−10−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Subtask 32−21−10−420−005 Refer to Figure 403. NOTE: The steps that follow are for the installation of the NLG torque link quick release assembly. This procedure applicable to install the quick release assembly on a upper torque link assembly (to rebuild the upper torque link assembly if it is with out the Quick Release Assembly). B. If necessary do the steps that follow to install the NLG torque link quick release assembly (2) on the upper torque link: WARNING: USE THE APPLICABLE SAFETY EQUIPMENT WHEN YOU DO THIS PROCEDURE. THE QUICK RELEASE ASSEMBLY IS UNDER SPRING PRESSURE. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURY TO YOUR EYES AND OTHER BODY TISSUES. (1) Install the quick release assembly (2) on the upper torque link. (2) Install the lock washer (1). NOTE: Make sure the lock washer engages the slots in the upper torque link assembly. (3) Use a 0.187 to 0.240 in. (4.75 to 6.10 mm) diameter punch and dent the edges of the lock washer (1) into the slots of the quick release assembly (2). (4) Fill the two lubrication fittings with grease (04−005). **ON A/C 7003−7067, 7069−7273 Pre VSBM−DT−16040−32−12 Subtask 32−21−10−420−001 Refer to Figure 401. C. Attach the upper torque link to the NLG as follows: (1) Put the torsion spring (17) in position between the mounting holes on the NLG main fitting. Make sure that the center of the torsion spring is in the mounting groove of the NLG main fitting when it is installed. (2) Align the top mounting holes of the torque link assembly (18), the torsion spring (17), and the mounting holes on the NLG main fitting. Install the torque pin (16). (3) Install the washer (15) on the bolt (14). (4) Align the cross−holes of the torque pin (16) with the related holes in the NLG main fitting and install the bolt (14). (5) Install the washers (13) and (12), and also the nut (11) on the bolt (14). NOTE: To align the cotter pin in the bolt shank with the slot in the nut, use a maximum of two washers (13) and/or (12) on the side of the nut (11). Use a minimum of one washer (13) and/or (12). Master EFFECTIVITY: See Pageblock 32−21−10 page 401 32−21−10 Page 410 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (6) Torque the nut (11) to 25−30 pound−inches (2.86−3.32 N·m). (7) Safety the nut (11) with the cotter pin (10). Subtask 32−21−10−420−002 D. Attach the lower torque link to the NLG as follows: (1) Align the lower mounting holes of the lower torque link, the axle assembly (9), and the jacking pad (7). Install the torque pin (8). NOTE: Make sure that the anti−rotation pads of the jacking pad (7) are located to the left side of the NLG when it is installed. (2) Install the countersunk washer (6) on the bolt (5). (3) Align the cross−holes of the torque pin (8) with the related holes in the jacking pad (7) and install the bolt (5). NOTE: Make sure that the bolt (5) is installed with the head of the bolt on the aft side of the jacking pad (7). (4) Install the washers (4) and (3), and also the nut (2) on the bolt (5). NOTE: To align the cotter pin in the bolt shank with the slot in the nut, use a maximum of two washers (4) and/or (3) on the side of the nut (2). Use a minimum of one washer (4) and/or (3). (5) Torque the nut (2) to 25−30 pound−inches (2.86−3.32 N·m). (6) Safety the nut (2) with the cotter pin (1). **ON A/C 7274−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7273 Post VSBM−DT−16040−32−12 Subtask 32−21−10−420−003 Refer to Figure 402. E. Attach the upper torque link to the NLG as follows: (1) Put the torsion spring (19) in position between the mounting holes on the NLG main fitting. Make sure that the center of the torsion spring (19) is in the mounting groove of the NLG main fitting when it is installed. (2) Align the top mounting holes of the upper torque link, the torsion spring (19) and the mounting holes on the NLG main fitting. Install the torque pin (18). (3) Install the washer (15) on the bolt (16). (4) Align the cross−holes of the torque pin (18) with the related holes in the NLG main fitting and install the bolt (16). (5) Install the washers (15) and (14), and also the nut (13) on the bolt (16). NOTE: To align the cotter pin in the bolt shank with the slot in the nut, use a maximum of two washers (15) and/or (14) on the side of the nut (13). Use a minimum of one washer (15) and/or (14). (6) Torque the nut (13) to 25−30 pound−inches (2.86−3.32 N·m). (7) Safety the nut (13) with the cotter pin (12). Master EFFECTIVITY: See Pageblock 32−21−10 page 401 411 32−21−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−10−420−004 F. Install the lower torque link to the NLG as follows: (1) If it was removed in the removal task, install the torsion spring (11) over the R/H side of the jacking pad (8). Make sure that: ± The horizontal arm of the spring is on the top of the jacking pad (8) near the front edge ± The vertical arm of the spring points up. (2) Align the lower mounting holes of the lower torque link, the axle assembly (10), and the jacking pad (8). Make sure that the vertical arm of the torsion spring (11) is located between the lower torque link and the axle assembly (10). Install the torque pin (9). NOTE: Make sure that the anti−rotation pads of the jacking pad (8) are located to the left side of the NLG when it is installed. (3) Install the countersunk washer (7) on the bolt (6). (4) Align the cross−holes of the torque pin (9) and the jacking pad (8) and Install the bolt (6). NOTE: Make sure that the bolt (6) is installed with the head of the bolt on the aft side of the jacking pad (8). (5) Install the bracket (5) on the bolt (6). Make sure that: ± The horizontal flange of the bracket (5) points aft ± The vertical flange points forward ± The horizontal flange of the bracket (5) is on top of the horizontal arm of the torsion spring (11). (6) Install the washers (4) and (3), and also the nut (2) on the bolt (6). NOTE: To align the cotter pin in the bolt shank with the slot in the nut, use a maximum of two washers (4) and/or (3) on the side of the nut (2). Use a minimum of one washer (4) and/or (3). (7) Torque the nut (2) to 25−30 pound−inches (2.86−3.32 N·m). (8) Safety the nut (2) with the cotter pin (1). **ON A/C ALL Subtask 32−21−10−840−001 G. Connect the upper and the lower torque links. Make sure that the quick−disconnect handles are correctly engaged. Subtask 32−21−10−930−001 H. Apply a red paint stripe adjacent to the nuts (2) and (11) and their respective bolts (6) and (13). Master EFFECTIVITY: See Pageblock 32−21−10 page 401 32−21−10 Page 412 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. Close Out Subtask 32−21−10−640−001 A. Lubricate the torque link assembly of the nose landing gear (Ref. TASK 12−20−32−640−801). Subtask 32−21−10−710−001 B. Do an operational test of the torque link assembly (Ref. TASK 32−21−10−710−801). Subtask 32−21−10−220−001 C. Do a clearance check of the NLG centered/extended proximity sensor (Ref. TASK 32−61−05−220−801). Subtask 32−21−10−410−001 D. Install the nose wheel/tire assemblies (Ref. TASK 32−42−01−400−801). Subtask 32−21−10−582−002 E. Remove the aircraft from jacks (Ref. TASK 07−11−01−582−804). Subtask 32−21−10−865−002 F. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−2 CB NO. F8 F8 NAME NOSE STEER NOSE STEER ZONE 221 222 Subtask 32−21−10−941−001 G. Remove all the tools, equipment, and unwanted materials from the area. Subtask 32−21−10−090−001 H. If open, close the NLG forward doors (Ref. TASK 32−22−01−980−802). Subtask 32−21−10−710−006 I. Do an operational test of the nosewheel steering system (Ref. TASK 32−51−00−710−801). Master EFFECTIVITY: See Pageblock 32−21−10 page 401 32−21−10 Page 413 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL ASSEMBLY, TORQUE LINK − ADJUSTMENT/TEST 1. General A. The maintenance procedure that follows is for the shimming of the nose landing gear (NLG) Shock Strut Torque Links. TASK 32−21−10−820−801 Alignment of the NLG Shock Strut Torque Links. 1. General A. This task is to replace or rework the torque links when the maximum permitted total wear of the torque link bushings has been reached. This shimming procedure permits aircraft to remain in service until the next schedule inspection. The shims can be locally manufactured. B. The structural and the functional integrity of the shock strut is not affected by the shimming procedure. 2. Job Set−Up Information Subtask 32−21−10−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Feeler Gauges Subtask 32−21−10−944−002 B. Consumable Materials REFERENCE 08−037 DESIGNATION Adhesive, epoxy resin, metal to metal structural bonding Subtask 32−21−10−946−001 C. Reference Information REFERENCE CMM 32−20−04 DESIGNATION Nose Landing Gear Component Maintenance Manual 3. Job Set−Up Subtask 32−21−10−220−003 Refer to Figure 501. Master EFFECTIVITY: See Pageblock 32−21−10 page 501 32−21−10 Page 501 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL A. Do the inspection of the three joints as follow: NOTE: The three joints are defined as: 1. The upper joint is between the upper torque link and the steering collar. 2. The apex joint is between the upper torque link and the lower torque link. 3. The lower joint is between the lower torque link and the axle fitting NOTE: There are two gaps at each joints and are defined as: 1. The left hand side (LHS) gap. 2. The right hand side (RHS) gap. (1) Measure both gaps at the same time for the three joints and record the dimensions (Dim.) as A to F in the table that follows: JOINT Upper Torque Link (UTL) Lower Torque Link (LTL) UTL−Steering collar (Upper Joint) UTL − LTL (Apex Joint) LTL − Axle fitting (Lower Joint) LHS GAP RHS GAP Dimensions A Dimensions B Dimensions C Dimensions D Dimensions E Dimensions F Joint sub−Total (LHS GAP + RHS GAP) = Assembly Clearance Dimensions G (=Dim. A + Dim. B) Dimensions H (=Dim. C + Dim. D) Dimensions J (=Dim. E + Dim. F) (a) Acceptance limits and rework criteria: 1 Any individual joint sub−total Assembly Clearance (Dim. G, Dim. H or Dim. J) less than 0.012 in. (0.30 mm) is acceptable for continued service. 2 Any individual joint sub−total Assembly Clearance (Dim. G, Dim. H or Dim. J) between 0.012 in. and 0.020 in. (0.30 mm to 0.51 mm) is beyond allowable limits. Add shims as per the steps described in this procedure, Para A. 3 Any individual joint sub−total Assembly Clearance (Dim. G, Dim. H or Dim. J) greater than 0.020 in. (0.51 mm) is beyond allowable limits. Replace the bushings as per the steps in this procedure, Para B. 4. Procedure Subtask 32−21−10−820−001 Refer to Figure 501 and 502. Master EFFECTIVITY: See Pageblock 32−21−10 page 501 32−21−10 Page 502 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL A. If shimming is necessary do the steps that follow: (1) To determine the thickness of the shim required for LHS and RHS joints refer to the table that follows: NOTE: The shim thickness should reduce the individual joint sub−total Assembly Clearance to 0.004 in. (0.102 mm). Joint Upper Joint Apex Joint Lower Joint ACTUAL SHIM THICKNESS REQUIRED PER SIDE Side in. mm LHS ((Dim.G−0.004) / 2) ((Dim. G−0.102) / 2) ±0.001 ±0.025 Dim. K RHS ((Dim.G−0.004) / 2) ((Dim. G−0.102) / 2) ±0.001 ±0.025 Dim. L LHS ((Dim. H−0.004) / 2) ((Dim. H−0.102) / 2) ±0.001 ±0.025 Dim. M RHS ((Dim. H−0.004) / 2) ((Dim. H−0.102) / 2) ±0.001 ±0.025 Dim. N LHS Dim. P RHS Dim. Q ((Dim. J−0.004) / 2) ±0.001 ((Dim. J−0.102) / 2) ±0.025 ((Dim. J−0.004) / 2) ±0.001 ((Dim. J−0.102) / 2) ±0.025 (2) Do the installation of shims as follows: (a) For UTL steering collar joint remove the upper torque link pin (Ref. TASK 32−21−10−000−801). 1 Install the shim (thickness Dim. K) on the LHS upper torque link bushing. 2 Install the shim (thickness Dim. L) on the RHS upper torque link bushing. 3 Install the upper torque link pin(Ref. TASK 32−21−10−400−801). (b) For UTL−LTL (Apex Joint) separate the upper and lower torque links through the quick release mechanism 1 Pull out, at the same time, the two quick−disconnect handles to disconnect the upper torque link from the lower torque link 2 Apply a thin film of adhesive to the bushing flange faces. 3 Install the shim (thickness Dim. M) on the LHS upper torque link bushing. 4 Install the shim (thickness Dim. N) on the RHS upper torque link bushing. 5 Reconnect the upper and lower torque links apex joint. 6 Pull fully out and hold the two quick−disconnect handles. 7 Align the pivot of the upper torque link with the pivot of the lower torque link. 8 Release the quick−disconnect handles. Make sure that the two quick−disconnect pins engage fully with the pivot of the lower torque link. Master EFFECTIVITY: See Pageblock 32−21−10 page 501 32−21−10 Page 503 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (c) B. For LTL−Axle fitting joint remove the lower torque link pin(Ref TASK 32−21−10−000−801. 1 Install the shim (thickness Dim. P) on the LHS lower torque link bushing. 2 Install the shim (thickness Dim. Q) on the RHS lower torque link bushing. 3 Install the lower torque link pin(Ref. TASK 32−21−10−000−801. If the bushing replacement is necessary, do the step that follows: (1) Measure the fits and clearances of the components (Ref. CMM 32−20−04) Master EFFECTIVITY: See Pageblock 32−21−10 page 501 32−21−10 Page 504 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL BUSHING (7−95) X2 STEERING COLLAR (7−90) A A B BUSHING (4−195) X2 UPPER TORQUE LINK (4−215) BUSHING (4−200) X2 C D LOWER TORQUE LINK (4−95) BUSHING (4−105) BUSHING (4−100) X2 E F AXLE FITTING (4−420) ram3221105_002.dg, lr, 17/02/03 BUSHING (4−425) X2 A Alignment of the NLG Shock Strut Torque Links (Shimming Procedure) Figure 501 Master EFFECTIVITY: See Pageblock 32−21−10 page 501 32−21−10 Page 505 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL OUTSIDE DIAMETER INSIDE DIAMETER MATERIAL STAINLESS STEEL PER AMS−DTL−22499/3 (MIL−S−22499, COMPOSITION 3, TYPE 1, CLASS 2) PEELABLE SHIMS OUTSIDE DIAMETER ± 0.010 in. Upper Joint Apex Joint Lower Joint 1.625 1.250 1.5 ± 0.25 mm 41.28 31.75 38.10 INSIDE DIAMETER ± 0.002 in. 1.145 0.620 1.145 ± 0.05 mm 29.08 15.75 29.08 THICKNESS ± 0.001 in. ± 0.025 mm 0.002 0.050 0.004 0.100 0.006 0.150 0.002 0.050 0.004 0.100 0.006 0.150 0.002 0.050 0.004 0.100 0.006 0.150 ram3221105_001.dg, rm/ds, 06/03/03 LOCATION Shim Thickness Requirement for the NLG Shock Strut Torque Links Figure 502 Master EFFECTIVITY: See Pageblock 32−21−10 page 501 32−21−10 Page 506 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED AXLE ASSEMBLY, NOSE LANDING GEAR (NLG) − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the nose landing gear (NLG) axle assembly. The NLG axle assembly is installed on the bottom of the NLG shock strut. TASK 32−21−15−000−801 Removal of the NLG Axle Assembly 1. Job Set−Up Information Subtask 32−21−15−943−002 A. Tools and Equipment REFERENCE None specified None specified DESIGNATION Flat pan − 1 gallon (3.78 L) Plastic scraper Subtask 32−21−15−946−001 B. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−42−01−000−801 DESIGNATION Put the Aircraft on Jacks Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Removal of the Nosewheel/Tire Assembly 2. Job Set−Up Subtask 32−21−15−941−002 A. Install a DO NOT OPERATE warning tag on the steering−handwheel control module and the landing−gear control lever. Subtask 32−21−15−865−001 B. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−2 CB NO. F8 F8 NAME NOSE STEER NOSE STEER Master EFFECTIVITY: See Pageblock 32−21−15 page 401 32−21−15 ZONE 221 222 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−15−582−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). WARNING: C. D. Subtask 32−21−15−010−001 E. Remove the nosewheel/tire assemblies (Ref. TASK 32−42−01−000−801). Subtask 32−21−15−840−001 F. Put a flat pan under the NLG shock strut piston to collect any hydraulic fluid leakage. Subtask 32−21−15−614−001 OBEY THE SAFETY PRECAUTIONS THAT FOLLOW WHEN YOU DO WORK WITH HIGH−PRESSURE GAS NITROGEN: ± USE A FACE SHIELD ± USE SAFETY GOGGLES ± CLOSE THE VALVES ON THE PIPING AND THE TANKS WHEN THEY ARE NOT USED OR WHEN EMPTY ± GO TO AN AREA THAT HAS A GOOD FLOW OF CLEAN AIR AND GET MEDICAL AID IF YOU BREATHE IN GAS NITROGEN NITROGEN CAN CAUSE SUFFOCATION AND DEATH WHEN IT IS BREATHED IN. WARNING: RELEASE THE PRESSURE FROM THE NLG SHOCK STRUT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS. G. Do the steps that follow to release the nitrogen pressure from the NLG shock strut: (1) Open the valve cover (25) on the diaphragm assembly at the bottom of the shock strut and remove the dust cap from the nitrogen charge valve. WARNING: DO NOT DEFLATE THE STRUT TOO QUICKLY. YOU CAN CAUSE A SPRAY OF OIL. THIS CAN CAUSE INJURIES TO PERSONS. (2) Slowly loosen the thin nut on the nitrogen charge valve and let the shock strut fully deflate. WARNING: Subtask 32−21−15−140−001 H. I. Use a plastic scraper to remove unwanted sealant from around the top and bottom joint of the NLG axle assembly (9) at the shock strut piston and at the joint between the shock strut piston and the diaphragm assembly. Use a plastic scraper to remove unwanted sealant from the head of the axle pin (13), the washers (14) and (15), the spacers (12), and the nut (11). Master EFFECTIVITY: See Pageblock 32−21−15 page 401 32−21−15 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. Procedure **ON A/C 7003−7067, 7069−7273 Pre VSBM−DT−16040−32−12 Subtask 32−21−15−030−001 Refer to Figure 401. A. Do the steps that follow to remove the lower torque link: WARNING: HOLD THE TOP TORQUE LINK WHEN YOU RELEASE THE QUICK DISCONNECT PINS. THE TOP TORQUE LINK IS SPRING LOADED AND WILL MOVE UP QUICKLY. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT. (1) Pull the quick−disconnect pins on torque link assembly to disconnect the upper and the lower torque links. (2) Remove and discard the cotter pin (1) from the bolt (6). (3) Remove the nut (2), and the washers (3) and/or (4) from the bolt (6). NOTE: There can be more than one washer on the side of the nut (2). (4) Remove the bolt (6) with the countersunk washer (5), from the jacking pad (8) and the torque pin (7). (5) Hold the lower torque link and the jacking pad (8). Remove the torque pin (7) and the jacking pad (8), to disconnect the lower torque link from the NLG axle assembly (9). **ON A/C 7274−7501 and ON A/C 7003−7067, 7069−7273 Post VSBM−DT−16040−32−12 Subtask 32−21−15−030−004 Refer to Figure 402. B. Do the steps that follow to remove the lower torque link: WARNING: HOLD THE TOP TORQUE LINK WHEN YOU RELEASE THE QUICK DISCONNECT PINS. THE TOP TORQUE LINK IS SPRING LOADED AND WILL MOVE UP QUICKLY. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT. (1) Pull the quick−disconnect pins on torque link assembly to disconnect the upper and the lower torque links. (2) Remove and discard the cotter pin (1) from the bolt (6). (3) Remove the nut (2), and the washers (3) and/or (4) from the bolt (6). NOTE: There can be more than one washer on the side of the nut (2). (4) Make sure that the lower torque link is in a position that causes the least amount of torsion in the torsion spring (26) that is installed on the jacking pad (8). Remove the bracket (25) from the bolt (6). (5) Remove the bolt (6) with the countersunk washer (5), from the jacking pad (8) and the torque pin (7). (6) Hold the lower torque link and the jacking pad (8). Remove the torque pin (7) and the jacking pad (8), to disconnect the lower torque link from the NLG axle assembly (9). Master EFFECTIVITY: See Pageblock 32−21−15 page 401 32−21−15 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (7) If required for other maintenance, remove the torsion spring (26) from the jacking pad (8). **ON A/C 7003−7067, 7069−7501 Subtask 32−21−15−030−002 C. If you will replace the NLG axle assembly (9) with a new assembly, do the steps that follow: (1) Pull the quick−disconnect pins on torque link assembly to disconnect the upper and the lower torque links. (2) Remove and discard the cotter pin (16). (3) Remove the nut (18), the washer (19), and the uplock pin (17). (4) Remove and discard the lockwire from the bolts (20). (5) Remove the bolts (20), the washers (21), the uplock bracket (22), and the uplock spacer (23). **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED Subtask 32−21−15−020−002 D. Remove the NLG axle pin (13) from the shock strut piston as follows: (1) Remove and discard the cotter pin (10). (2) Remove the nut (11), the washers (14) and (15), (as installed), and the spacer washer (12) from the pin (13). WARNING: MAKE SURE THAT THE SHOCK STRUT NITROGEN PRESSURE IS FULLY RELEASED BEFORE YOU DO THE STEP THAT FOLLOWS. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT. (3) With the shock strut piston fully deflated, remove the pin (13) with the other spacer washer (12) from the axle assembly (9). Subtask 32−21−15−030−003 THE FLOATING PISTON MIGHT COME OUT OF THE NLG AXLE ON THE REMOVAL OF THE NLG AXLE DIAPHRAGM. IF YOU ARE NOT CAREFUL , YOU MAY DAMAGE THE AIRCRAFT AND THE EQUIPMENT. Remove the components that follow from the bottom of the NLG shock strut: (1) Carefully remove the diaphragm assembly from the shock strut piston. (2) Remove the tee seal (24) and related backing rings from the diaphragm assembly. NOTE: The tee seal (24) is an assembly of a tee seal and two backing rings. CAUTION: E. Subtask 32−21−15−020−003 F. Remove the NLG axle assembly (9) from the shock strut piston. Master EFFECTIVITY: See Pageblock 32−21−15 page 401 32−21−15 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND NOTES 1 14. Washer. 15. Washer. 16. Cotter pin. 17. Uplock pin. 18. Nut. 19. Washer. 20. Bolt. 2 21. Washer. 22. Uplock bracket. 23. Uplock spacer. 24. Tee seal. 25. Valve cover. 1. Cotter pin. 2. Nut. 3. Washer. 4. Washer. 5. Washer. 6. Bolt. 7. Torque pin. 8. Jacking pad. 9. Axle assembly. 10. Cotter pin. 11. Nut. 12. Spacer. 13. Pin. A 20 22 1 15 12 18 23 Make sure that the radius of each back−up ring fits against the related radius of the tee seal (24). 17 19 16 If necessary, use washer(s) (3 or 4) as required to align the slots of the nut (2) with the cotter pin hole of the nut (6). A maximum of two washers on the nut side are permitted. 3 SHOCK STRUT PISTON (REF) 21 Add a maximum of two washers (14) as required on the side of the nut (11) to align the slots of the nut with the cotter pin hole of the pin (13). 10 14 11 9 12 13 OU D 3 FLOATING PISTON (REF) 24 B 2 1 2 3 4 B 25 BACK−UP RING (REF) D TB FW 5 8 DIAPHRAGM ASSEMBLY (REF) 6 7 LOWER TORQUE LINK (REF) A ram3221154_001.dg, rm/ds, 02/02/03 BACK−UP RING (REF) NLG Axle Assembly − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−21−15 page 401 32−21−15 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND NOTES 1 14. Washer. 15. Washer. 16. Cotter pin. 17. Uplock pin. 18. Nut. 19. Washer. 20. Bolt. 2 21. Washer. 22. Uplock bracket. 23. Uplock spacer. 24. Tee seal. 25. Valve cover. 26. Bracket. 27. Torsion spring. 1. Cotter pin. 2. Nut. 3. Washer. 4. Washer. 5. Washer. 6. Bolt. 7. Torque pin. 8. Jacking pad. 9. Axle assembly. 10. Cotter pin. 11. Nut. 12. Spacer. 13. Pin. A Add a maximum of two washers (14) as required on the side of the nut (11) to align the slots of the nut with the cotter pin hole of the pin (13). If necessary, use washer(s) (3 or 4) as required to align the slots of the nut (2) with the cotter pin hole of the nut (6). A maximum of two washers on the nut side are permitted. 3 21 20 22 SHOCK STRUT PISTON (REF) 17 1 19 12 18 23 16 Make sure that the radius of each back−up ring fits against the related radius of the tee seal (24). 15 10 14 11 9 12 13 3 FLOATING PISTON (REF) 24 B 1 2 3 27 26 5 25 B BACK−UP RING (REF) OU D 4 D TB FW 2 8 DIAPHRAGM ASSEMBLY (REF) 6 7 LOWER TORQUE LINK (REF) A ram3221154_002.dg, rm/jp, 03/11/98 BACK−UP RING (REF) NLG Axle Assembly − Removal/Installation Figure 402 Master EFFECTIVITY: See Pageblock 32−21−15 page 401 32−21−15 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−21−15−400−801 Installation of the NLG Axle Assembly 1. Job Set−Up Information Subtask 32−21−15−943−003 A. Tools and Equipment REFERENCE None specified None specified DESIGNATION Torque wrench 0 to 200 pound−inches (0 to 22.6 N·m) Plastic scraper Subtask 32−21−15−944−001 B. Consumable Materials REFERENCE 02−002 05−005 06−002 06−028 09−009 09−023 11−007 16−003 or equivalent DESIGNATION Hydraulic fluid, petroleum base Lockwire Petrolatum Compound, corrosion−preventative, solvent cutback, cold application Compound, sealing and coating, corrosion inhibitive Compound, sealing and coating, corrosion inhibitive Methyl ethyl keytone (MEK) Red paint **ON A/C 7003−7067, 7069−7273 Pre VSBM−DT−16040−32−12 Subtask 32−21−15−945−001 C. Parts REF 1 2 3 4 5 6 10 11 12 13 NAME OF PART Cotter pin Nut Washer Washer Countersunk washer Bolt Cotter pin Nut Spacer washer Pin Master EFFECTIVITY: See Pageblock 32−21−15 page 401 QTY 1 1 1 1 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−21−00−02−085 IPC 32−21−00−02−080 IPC 32−21−00−02−075 IPC 32−21−00−02−070 IPC 32−21−00−02−065 IPC 32−21−00−02−060 IPC 32−21−00−02−125 IPC 32−21−00−02−120 IPC 32−21−00−02−105 IPC 32−21−00−02−100 32−21−15 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REF 14 15 16 18 19 20 21 24 NAME OF PART QTY Washer 1 Washer 1 Cotter pin 1 Nut 1 Washer 1 Bolt 2 Washer 2 Tee seal assembly (with two backup rings) 1 IPC SEQUENCE NO. IPC 32−21−00−02−110 IPC 32−21−00−02−115 IPC 32−21−00−02−165 IPC 32−21−00−02−160 IPC 32−21−00−02−155 IPC 32−21−00−02−170 IPC 32−21−00−02−155 IPC 32−21−00−04−005 **ON A/C 7274−7501 and ON A/C 7003−7067, 7069−7273 Post VSBM−DT−16040−32−12 Subtask 32−21−15−945−002 D. Parts REF 1 2 3 4 5 6 10 11 12 13 14 15 16 18 19 20 21 24 NAME OF PART QTY Cotter pin 1 Nut 1 Washer 1 Washer 1 Countersunk washer 1 Bolt 1 Cotter pin 1 Nut 1 Spacer washer 1 Pin 1 Washer 1 Washer 1 Cotter pin 1 Nut 1 Washer 1 Bolt 2 Washer 2 Tee seal assembly (with two backup rings) 1 IPC SEQUENCE NO. IPC 32−21−00−02−085 IPC 32−21−00−02−080 IPC 32−21−00−02−077 IPC 32−21−00−02−072 IPC 32−21−00−02−065 IPC 32−21−00−02−062 IPC 32−21−00−02−125 IPC 32−21−00−02−120 IPC 32−21−00−02−105 IPC 32−21−00−02−100 IPC 32−21−00−02−110 IPC 32−21−00−02−115 IPC 32−21−00−02−165 IPC 32−21−00−02−160 IPC 32−21−00−02−155 IPC 32−21−00−02−170 IPC 32−21−00−02−155 IPC 32−21−00−04−005 **ON A/C 7003−7067, 7069−7501 Subtask 32−21−15−946−002 E. Reference Information Master EFFECTIVITY: See Pageblock 32−21−15 page 401 32−21−15 Page 408 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REFERENCE TASK 07−11−01−582−804 TASK 12−12−32−610−804 TASK 12−20−32−640−801 TASK 32−21−10−710−801 TASK 32−21−10−820−801 TASK 32−21−30−400−801 TASK 32−33−05−820−801 TASK 32−42−01−400−801 TASK 51−23−00−100−801 TASK 51−23−00−390−804 TASK 51−23−00−390−808 TASK 51−23−00−390−815 TASK 51−26−00−110−801 DESIGNATION Removal of the Aircraft from Jacks Servicing (Oil and Nitrogen) of the NLG Shock Strut − Aircraft on Jacks Lubrication of the Nose Landing Gear Operational Test of the Torque Link Assembly Alignment of the NLG Shock Strut Torque Link Installation of the NLG Sliding Member Alignment of the NLG Uplock Pin with the NLG Uplock Assembly Installation of the Nosewheel/Tire Assembly Preparation of Surfaces for Sealant Bead Seal Sealant Procedure Application of Sealant with Brush Curing of Sealant Solvent Cleaning **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED 2. Job Set−Up Subtask 32−21−15−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. 3. Procedure **ON A/C 7003−7067, 7069−7273 Pre VSBM−DT−16040−32−12 Subtask 32−21−15−430−001 Refer to Figure 401. A. If you install a new NLG axle assembly (9), install the components that were removed from the removed NLG axle assembly (9) as follows: (1) Put the uplock spacer (23) between the uplock bracket (22) and the axle assembly (9). Make sure that the serrated surface of the uplock spacer (23) faces forward. (2) Install the uplock bracket (22) with the bolts (20) and the washers (21). Make sure that the serrated surfaces of the uplock spacer (23) and the uplock bracket (22) are correctly engaged. NOTE: For the initial alignment with the uplock assembly, install the uplock bracket (22) so that it is centered on the uplock spacer (23). Make sure that there are an equal number of serrations visible at the top and the bottom of the uplock bracket (22). Master EFFECTIVITY: See Pageblock 32−21−15 page 401 32−21−15 Page 409 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (3) Temporarily tighten the bolts (20). NOTE: Do not torque or safety the bolts (20) with lockwire at this time. This will be done when you do the functional test of the NLG uplock assembly (4) Install the uplock pin (17), the washer (19), and the nut (18). (5) Temporarily tighten the nut (18). Make sure that the uplock pin (17) is free to rotate. NOTE: Do not safety the nut (18) with the cotter pin (16) at this time. This will be done when you do the functional test of the NLG uplock assembly. **ON A/C 7274−7501 and ON A/C 7003−7067, 7069−7273 Post VSBM−DT−16040−32−12 Subtask 32−21−15−430−006 Refer to Figure 402. B. If you install a new NLG axle assembly (9), install the components that were removed from the removed NLG axle assembly (9) as follows: (1) Put the uplock spacer (23) between the uplock bracket (22) and the axle assembly (9). Make sure that the serrated surface of the uplock spacer (23) faces forward. (2) Install the uplock bracket (22) with the bolts (20) and the washers (21). Make sure that the serrated surfaces of the uplock spacer (23) and the uplock bracket (22) are correctly engaged. NOTE: For the initial alignment with the uplock assembly, install the uplock bracket (22) so that it is centered on the uplock spacer (23). Make sure that there are an equal number of serrations visible at the top and the bottom of the uplock bracket (22). (3) Temporarily tighten the bolts (20). NOTE: Do not torque or safety the bolts (20) with lockwire at this time. This will be done when you do the functional test of the NLG uplock assembly. (4) Install the uplock pin (17), the washer (19), and the nut (18). (5) Temporarily tighten the nut (18). Make sure that the uplock pin (17) is free to rotate. NOTE: Do not safety the nut (18) with the cotter pin (16) at this time. This will be done when you do the functional test of the NLG uplock assembly. **ON A/C 7003−7067, 7069−7501 Subtask 32−21−15−110−002 C. D. Make sure that the mating surfaces of the shock strut and the NLG axle assembly (9) are clean before you install the NLG axle assembly (Ref. TASK 51−26−00−110−801). Make sure that the bore of the shock strut piston and also the diaphragm assembly are clean before you install the diaphragm assembly (Ref. TASK 51−26−00−110−801). Master EFFECTIVITY: See Pageblock 32−21−15 page 401 32−21−15 Page 410 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED Subtask 32−21−15−150−001 E. F. Remove any unwanted sealant (Ref. TASK 51−23−00−100−801) that remains on the components that follow: ± The pin (13) ± The washers (14) and (15) ± The spacers (12) ± The nut (11). At the same time, also remove any unwanted sealant that remains from the area where the spacers (12) touch the NLG axle assembly (9) and also on the bottom of the shock strut at the joint between the shock strut piston and the diaphragm assembly. Use a clean low−lint cloth that is moist with 11−007 methyl ethyl keytone (MEK) to remove any remaining sealant and unwanted contamination. Subtask 32−21−15−430−002 G. H. If necessary to install the floating piston (Ref. TASK 32−21−30−400−801 Job Set−Up para D). Install the components that follow in the bottom of the NLG shock strut: (1) Lightly lubricate a serviceable tee seal (24) with 02−002 hydraulic fluid or 06−002 petrolatum. (2) Install the tee seal (24) and related backing rings on the diaphragm assembly. Make sure that the radius of the backing rings fit the radius of the tee seal (24). NOTE: A replacement tee seal (24) is an assembly of a tee seal and two backing rings. (3) Carefully put the diaphragm assembly into the shock strut piston and align the holes in the diaphragm assembly with their related holes in the NLG shock strut. Subtask 32−21−15−420−001 I. J. K. L. M. N. Apply a thin layer of 06−028 corrosion−preventative compound to the mating surfaces of the NLG axle assembly (9) and the shock strut piston. Install the NLG axle assembly (9) on the shock strut piston and align the mounting holes. Remove any unwanted corrosion−preventative compound. Install the pin (13) with the spacer (12) through the NLG axle assembly (9), the shock strut piston, and the diaphragm assembly from the left side of the landing gear. Install the other spacer (12), the washer (15) the washer(s) (14), and the nut (11). NOTE: Use a maximum of two washers (14) if necessary to align the slot in the nut (11) with the cotter pin hole in the pin (13) correctly when the nut (11) is torqued. Put a minimum of one washer (15) on the side of the nut. Torque the nut (11) to 140 to 160 pound−inches (15.8 to 18.0 N·m). Safety the nut (11) with the cotter pin (10). Master EFFECTIVITY: See Pageblock 32−21−15 page 401 32−21−15 Page 411 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7003−7067, 7069−7273 Pre VSBM−DT−16040−32−12 Subtask 32−21−15−430−003 Refer to Figure 401. NOTE: If necessary to shim the NLG shock strut torque links (Ref. TASK 32−21−10−820−801). O. Install the lower torque link to the NLG as follows: (1) Align the mounting holes of the lower torque link, the NLG axle assembly (9), and the jacking pad (8). NOTE: Make sure that the anti−rotation pads of the jacking pad (8) are located to the left side of the NLG. (2) Install the torque pin (7). (3) Install the countersunk washer (5) on the bolt (6). (4) Align the cross−holes of the torque pin (7) and the jacking pad (8). Install the bolt (6) (facing forward) with the washers (5), (4), and (3), and the nut (2). (5) Install the washers (4) and/or (3), and also the nut (2). NOTE: Use a maximum of two washers (4) or (3) on the side of the nut if necessary to align the hole in the bolt (6) with the slot in the nut (2) when you torque the nut (6). Put a minimum of one washer (4) or (3) on the side of the nut. (6) Torque the nut (2) to 25 to 30 pound−inches (2.86 to 3.3 N·m). (7) Safety the nut (2) with the cotter pin (1). **ON A/C 7274−7501 and ON A/C 7003−7067, 7069−7273 Post VSBM−DT−16040−32−12 Subtask 32−21−15−430−005 Refer to Figure 402. NOTE: If necessary to shim the NLG shock strut torque links (Ref. TASK 32−21−10−820−801). P. Install the lower torque link to the NLG as follows: (1) If it was removed in the removal task, install the torsion spring (26) over the R/H side of the jacking pad (8). Make sure that: ± The horizontal arm of the spring is on the top of the jacking pad (8) near the front edge ± The vertical arm of the spring points up. (2) Align the lower mounting holes of the lower torque link, the NLG axle assembly (9), and the jacking pad (8). Make sure that the vertical arm of the torsion spring (26) is located between the lower torque link and the NLG axle assembly (9). Install the torque pin (7). NOTE: Make sure that the anti−rotation pads of the jacking pad (8) are located to the left side of the NLG. (3) Install the torque pin (7). Master EFFECTIVITY: See Pageblock 32−21−15 page 401 32−21−15 Page 412 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (4) Install the countersunk washer (5) on the bolt (6). (5) Align the cross−holes of the torque pin (7) and the jacking pad (8) and install the bolt (6) facing forward. (6) Install the bracket (25) the bolt (6). Make sure that: ± The horizontal flange of the bracket (25) points aft ± The vertical flange points forward ± The horizontal flange of the bracket (25) is on top of the horizontal arm of the torsion spring (26). (7) Install the washers (4) and/or (3), and also the nut (2). NOTE: Use a maximum of two washers (4) or (3) on the side of the nut if necessary to align the hole in the bolt (6) with the slot in the nut (2) when you torque the nut (6). Put a minimum of one washer (4) or (3) on the side of the nut. (8) Torque the nut (2) to 25 to 30 pound−inches (2.86 to 3.3 N·m). (9) Safety the nut (2) with the cotter pin (1). **ON A/C 7003−7067, 7069−7501 Subtask 32−21−15−840−002 Q. Connect the upper and the lower torque links. Make sure that the quick−disconnect handles are correctly engaged. **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED Subtask 32−21−15−930−001 R. Apply a torque stripe of 16−003 red paint adjacent to the nut (2) and at the end of the bolt (6). Subtask 32−21−15−390−001 Refer to Figure 403. S. Put a bead seal of 09−009 sealant fully around the top and the bottom joints between the axle assembly (9) and the shock strut piston (Ref. TASK 51−23−00−390−804). T. Put a bead seal of 09−009 sealant on the joint between the diaphragm assembly and the shock strut piston (Ref. TASK 51−23−00−390−804). NOTE: 09−009 sealant is preferred. If a faster cure time is required, refer to TASK 51−23−00−390−815 for alternate sealants. Subtask 32−21−15−390−002 Refer to Figure 403. U. Apply a brush coat of 09−023 sealant on the head of the axle pin (13), the washers (14) and (15), the spacers (12), and the nut (11). Include the area where the washers touch the axle assembly (9) (Ref. TASK 51−23−00−390−808). Master EFFECTIVITY: See Pageblock 32−21−15 page 401 32−21−15 Page 413 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 4. Close Out Subtask 32−21−15−640−001 A. Lubricate the torque link assembly (Ref. TASK 12−20−32−640−801). Subtask 32−21−15−614−002 B. Service the NLG shock strut with hydraulic oil and nitrogen (Ref. TASK 12−12−32−610−803) no matter if the floating piston is removed in the shock strut piston assembly. Subtask 32−21−15−710−001 C. Do an operational test of the torque link assembly (Ref. TASK 32−21−10−710−801). Subtask 32−21−15−410−002 D. Install the nosewheel/tire assembly (Ref. TASK 32−42−01−400−801). Subtask 32−21−15−865−002 E. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−2 CB NO. F8 F8 NAME NOSE STEER NOSE STEER ZONE 221 222 Subtask 32−21−15−720−002 F. Do the alignment of the NLG uplock pin (Ref. TASK 32−33−05−820−801). Subtask 32−21−15−586−002 G. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−21−15−941−001 H. Remove all the tools, equipment, warning tags, and unwanted materials from the area. Master EFFECTIVITY: See Pageblock 32−21−15 page 401 32−21−15 Page 414 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL D FW A A SEALING AND COATING COMPOUND 0.150 in. MAX (3.81 mm MAX) SEALING AND COATING COMPOUND APPLY SEALING AND COATING COMPOUND ALL AROUND WHERE PISTON/DIAPHRAGM INDICATED JOINT VALVE COVER (REF) PIN (REF) ram3221154_003.dg, jc, 16/04/01 AXLE/PISTON JOINT NLG Axle − Sealing Figure 403 Master EFFECTIVITY: See Pageblock 32−21−15 page 401 32−21−15 Page 415 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL AXLE ASSEMBLY, NOSE LANDING GEAR (NLG) − INSPECTION/CHECK 1. General A. The maintenance procedure that follows is for the detailed inspection of the nose−landing−gear (NLG) axle assembly. TASK 32−21−15−220−801 Detailed Inspection of the NLG Axle Assembly 1. Reason for the Job Refer to MRB 32−00−00−15. 2. Job Set−Up Information Subtask 32−21−15−946−003 A. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−42−01−000−801 TASK 32−42−01−400−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Removal of the Nose Wheel/Tire Assembly Installation of the Nose Wheel/Tire Assembly 3. Job Set−Up Subtask 32−21−15−941−004 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. Subtask 32−21−15−010−003 B. Remove the applicable nosewheel/tire assemblies (Ref. TASK 32−42−01−000−801). 4. Procedure Subtask 32−21−15−210−001 A. Do a visual inspection of the NLG axle as follows: (1) Examine the NLG axle for: ± Damage ± Security of attachment ± Corrosion Master EFFECTIVITY: See Pageblock 32−21−15 page 601 32−21−15 Page 601 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL ± Unsatisfactory color caused by heat. (2) Examine the threads of the NLG axle for damage. (3) Examine the inner sleeves for damage. (4) Examine the sealing compound on the joint between the diaphragm assembly (in the bottom of the shock strut) and the shock strut piston for damage. **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED (5) Examine the sealing compound around the top and the bottom joints between the NLG axle and the shock strut piston for damage. **ON A/C ALL 5. Close Out Subtask 32−21−15−410−001 A. Install the nosewheel/tire assemblies (Ref. TASK 32−42−01−400−801). Subtask 32−21−15−941−003 B. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−21−15 page 601 32−21−15 Page 602 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL SPARE SEALS, NLG LOWER BEARING − MAINTENANCE PRACTICES 1. General A. The maintenance procedures that follow are for the replacement of the nose landing gear (NLG) lower−bearing tee−seal (referred to as the ‘‘tee seal’’in this procedure). The tee seal is installed between the top of the NLG lower bearing and the NLG shock strut piston. The spare tee seal is installed on the external surface of the NLG lower bearing. TASK 32−21−20−960−801 Replacement of the Tee Seal with the Spare Tee Seal 1. Job Set−Up Information Subtask 32−21−20−943−001 A. Tools and Equipment REFERENCE G601R101222−1 Model 0504 None specified None specified DESIGNATION Cover − NLG wheels Jack, nose gear axle Brush Container, hydraulic fluid Subtask 32−21−20−944−001 B. Consumable Materials REFERENCE 02−002 05−004 06−002 DESIGNATION Hydraulic fluid, petroleum base Lockwire Petrolatum Subtask 32−21−20−945−002 C. Parts REF 2 3 4 7 9 12 NAME OF PART Preformed packing Bolt Washer Headed pin Tee seal (see note below) Spare tee seal NOTE: QTY 1 2 2 3 1 1 IPC SEQUENCE NO. IPC 32−21−00−04−045 IPC 32−21−00−04−013 IPC 32−21−00−04−012 IPC 32−21−00−04−020 IPC 32−21−00−04−030 IPC 32−21−00−04−025 The tee seal (9) is an assembly of a tee seal and two sets of the inner and outer back−up rings (10) and (11). Master EFFECTIVITY: See Pageblock 32−21−20 page 201 32−21−20 Page 201 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−20−946−001 D. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−12−32−610−804 TASK 32−00−00−790−801 TASK 32−42−01−000−801 TASK 32−42−01−400−801 TASK 51−26−00−110−801 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Servicing (Oil and Nitrogen) of the NLG Shock Strut − Aircraft on Jacks External Leak Check of the Landing Gear Removal of the Nosewheel/Tire Assembly Installation of the Nosewheel/Tire Assembly Solvent Cleaning 2. Job Set−Up Subtask 32−21−20−867−001 A. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Subtask 32−21−20−582−001 B. Lift the aircraft on the jacks until the nose landing gear is fully extended and the nose wheels are clear of the ground (Ref. TASK 07−11−01−582−801). Subtask 32−21−20−863−001 RELEASE THE PRESSURE OF THE SHOCK STRUT SLOWLY. YOU CAN CAUSE A SPRAY OF OIL. THIS CAN CAUSE INJURIES. C. Release the nitrogen pressure from the NLG shock strut (Ref. TASK 12−12−32−610−804). WARNING: MAKE SURE THAT THE NITROGEN CHARGE IS FULLY RELEASED FROM THE SHOCK STRUT BEFORE THE OIL FILLER PLUG IS REMOVED. IF YOU DO NOT DO THIS, INJURIES CAN OCCUR. CAUTION: RELEASE THE OIL FILLER PLUG SLOWLY. THERE CAN POSSIBLY BE AIR PRESSURE ON THE OIL SIDE OF THE FLOATING PISTON IF THE PISTON IS LEAKING. D. Remove and discard the lockwire from the oil filler plug (1) at the top of the NLG main fitting. E. Remove the oil filler plug (1) and discard the preformed packing (2). WARNING: Master EFFECTIVITY: See Pageblock 32−21−20 page 201 32−21−20 Page 202 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−20−030−001 DO NOT LET HYDRAULIC FLUID GET ON THE NLG TIRES. HYDRAULIC FLUID CAN CAUSE DAMAGE TO THE NLG TIRES. Install protective covers on the NLG wheel assemblies or remove the NLG wheel assemblies (Ref. TASK 32−42−01−000−801) to make sure that the NLG tires will not be contaminated with hydraulic fluid and also to get access to the work area. (1) Put the hydraulic fluid container below the nose landing gear. NOTE: The NLG shock strut contains approximately 0.75 gallons (2.8 L) of hydraulic fluid. Some of this hydraulic fluid will be released at the bottom of the NLG main fitting (5) as the lower bearing (4) is lowered on the shock strut piston. Make sure that the container is large enough to contain this volume. CAUTION: F. Subtask 32−21−20−582−002 G. Put the nose−gear axle jack below the jacking pad of the nose landing gear. Lift the axle of the nose landing gear approximately 1 inch (2.5 cm) from its fully extended position. NOTE: The nose−gear axle jack will keep the shock strut piston in position when the lower bearing is removed from the NLG main fitting. It is possible that the shock strut piston can move out of the NLG main fitting if it is not held in position. 3. Procedure Subtask 32−21−20−960−001 Refer to Figure 201. A. Replace the tee seal (9) with the spare tee seal (12) as follows: (1) Remove and discard the lockwire from the bolts (3). (2) Remove the two bolts (3) and the two washers (4) that attach the retaining collar (5) to the two locking segments (6). (3) Lower the retaining collar (5). (4) Remove the two locking segments (6) from the NLG main fitting. (5) Attach lockwire to the two removal holes in the lower bearing. (6) Pull the lockwire and lower the lower bearing approximately to the middle of the shock strut piston. Make sure that the lower bearing is fully removed from the NLG main fitting. NOTE: Make sure that there is a spare tee seal (12) installed in the upper external groove on the lower bearing. If the spare tee seal (12) has been used or has been damaged, it will be necessary to remove and replace it (Ref. TASK 32−21−20−000−801 and TASK 32−21−20−400−801). Master EFFECTIVITY: See Pageblock 32−21−20 page 201 32−21−20 Page 203 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−20−110−002 B. C. Clean the shock strut piston and the lower bearing of any unwanted contaminants (Ref. TASK 51−26−00−110−801). Apply a light coating of clean 02−002 hydraulic fluid with a brush to the external surfaces of the shock strut piston and the lower bearing. Subtask 32−21−20−960−002 D. Continue to replace the tee seal (9) with the spare tee seal (12) as follows: (1) Remove the three headed pins (7) from the lower bearing and the spacer ring (8). (2) Move the lower bearing down slightly to get access to the spacer ring (8), the tee seal (9), and the two sets of the inner and outer back−up rings (10) and (11), that are installed in the top of the lower bearing. (3) Move apart the spacer ring (8), the two sets of the inner and outer back−up rings (10) and (11), and the tee seal (9). (4) Cut, remove, and discard the tee seal (9). NOTE: Do not damage the two sets of the inner and outer back−up rings (10) and (11) on each side of the tee seal (9) when you remove the tee seal (9). If the inner and outer back−up rings (10) and (11) are damaged, it will be necessary to remove and replace them (Ref. TASK 32−21−20−000−801 and TASK 32−21−20−400−801). (5) Carefully move the spare tee seal (12) from the upper external groove on the lower bearing and put it in position on the shock strut piston below the inner and outer back−up rings (10) and (11). (6) Lightly lubricate the spare tee seal (12) with 02−002 hydraulic fluid or 06−002 petrolatum. Carefully move the spare tee seal (12) to the correct position between the two sets of the inner and outer backup rings (10) and (11). NOTE: Make sure that the radius of each back−up ring (10) (white colored) is installed against the radius of the tee seal (9). (7) Move the lower bearing up until it collects the spare tee seal (12) (with the two sets of the inner and outer back−up rings (10) and (11)), and the spacer ring (8) that are installed on the shock strut piston. NOTE: Align the holes in the spacer ring (8) with the holes in the lower bearing. (8) Install the three headed pins (7). NOTE: Apply a heavy layer of 06−002 petrolatum to the three headed pins (7) to make installation easier. (9) Carefully continue to move the lower bearing up into the NLG main fitting until it touches the lower cam in the NLG main fitting. Rotate the lower bearing until The alignment protrusions on the lower bearing engage their respective slots in the lower cam. The lower bearing will move up slightly when it is correctly engaged. (10) Install the two locking segments (6) into the NLG main fitting. (11) Move the retaining collar (5) up along the piston, attach it to the locking segments (6) with the two bolts (3), and the two washers (4). (12) Torque the bolts (3) to 20−25 pound−inches (2.26−2.28 N·m). Master EFFECTIVITY: See Pageblock 32−21−20 page 201 32−21−20 Page 204 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (13) Safety the bolts (3) with 05−004 lockwire. (14) Remove the nose−gear axle jack below the jacking pad of the nose landing gear. (15) Apply a small quantity of 02−002 hydraulic fluid to the external chrome surfaces of the shock strut piston with a brush. (16) Remove the hydraulic fluid container from the work area. (17) Remove the protective covers from the nose landing gear wheels or install the nose landing gear wheels if they where removed for access (Ref. TASK 32−42−01−400−801). 4. Close Out Subtask 32−21−20−614−001 A. Service the nose landing gear with hydraulic fluid and nitrogen (Ref. TASK 12−12−32−610−804). Make sure that you install a new preformed packing (2) on the oil filler plug (1). Subtask 32−21−20−586−001 B. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−21−20−210−001 C. Examine the area at the bottom of the NLG main fitting adjacent to the shock strut piston for leaks (Ref. TASK 32−00−00−790−801). Subtask 32−21−20−941−001 D. Remove all tools, equipment, safety placards, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−21−20 page 201 32−21−20 Page 205 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL NOTE 1 1 Make sure that the radius of the inner back−up ring (10) fits against the radius of the tee seal (9). 2 Make sure that the alignment protrusions on the lower bearing are correctly engaged in the lower cam when the lower bearing is installed. A NLG MAIN FITTING (REF) B 2 2 A ALIGNMENT PROTRUSION (REF) 8 C 11 7 12 10 1 9 10 1 11 C 1. Oil filter plug. 2. Preformed packing. 3. Bolt. 4. Washer. 5. Retaining collar. 6. Locking segment. 7. Headed pin. 8. Spacer ring. 9. Tee seal. 10. Inner back−up ring. 11. Outer back−up ring. 12. Spare tee seal. LOWER BEARING (REF) 3 6 4 SHOCK STRUT PISTON (REF) 6 5 B ram3221202_001(3).dg, rm, 18/04/97 LEGEND NLG Lower Bearing Spare Tee Seal − Maintenance Practices Figure 201 Master EFFECTIVITY: See Pageblock 32−21−20 page 201 32−21−20 Page 206 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL SEALS, NLG LOWER BEARING − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the nose landing gear (NLG) lower bearing seals (referred to as the ‘preformed packing’ and the ‘tee seal’ in this procedure). The seals are installed on the internal and external surfaces of the lower bearing in the main fitting of the NLG. NOTE: This procedure is applicable to aircraft that have the NLG with a separate removable axle installed. For aircraft that have the one−piece (integral) axle/shock−strut piston installed, shop maintenance procedures are used to remove/install the NLG lower bearing seals. Refer to the Messier−Dowty CMM 32−20−04 for the procedures to remove and replace the NLG lower bearing seals. **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED TASK 32−21−20−000−801 Removal of the Lower Bearing Seals of the NLG Shock Strut 1. Job Set−Up Information Subtask 32−21−20−943−002 A. Tools and Equipment REFERENCE None specified DESIGNATION Flat pan − 1 gallon (3.78 L) Subtask 32−21−20−946−002 B. Reference Information REFERENCE TASK 32−21−15−000−801 DESIGNATION Removal of the NLG Axle Assembly 2. Job Set−Up Subtask 32−21−20−010−001 WARNING: A. RELEASE THE PRESSURE FROM THE NLG SHOCK STRUT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS. Remove the NLG axle assembly (Ref. TASK 32−21−15−000−801). Master EFFECTIVITY: See Pageblock 32−21−20 page 401 32−21−20 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−20−680−001 B. Put a flat pan in position below the NLG shock strut. NOTE: The NLG shock strut contains approximately 0.75 gallons (2.8 L) of hydraulic fluid. Some of this hydraulic fluid will be released at the bottom of the NLG main fitting as the lower bearing is lowered on the shock strut piston. Make sure that the flat pan is large enough to contain this volume. Refer to Figure 401. C. Remove and discard the lockwire from the oil filler plug (1) at the top of the NLG main fitting. WARNING: MAKE SURE THAT THE NITROGEN CHARGE IS FULLY RELEASED FROM THE SHOCK STRUT BEFORE THE OIL FILLER PLUG IS REMOVED. IF YOU DO NOT DO THIS, INJURIES CAN OCCUR. CAUTION: RELEASE THE OIL FILLER PLUG SLOWLY. THERE CAN POSSIBLY BE AIR PRESSURE ON THE OIL SIDE OF THE FLOATING PISTON IF THE PISTON IS LEAKING. D. Remove the oil filler plug (1) and discard the preformed packing (2). 3. Procedure Subtask 32−21−20−020−003 Refer to Figure 401. A. Remove the lower bearing from the shock strut piston as follows: (1) Remove and discard the lockwire from the two bolts (3). (2) Lift the shock strut piston approximately 1 inch (2.5 cm) from its fully extended position. (3) Remove the two bolts (3) and the two washers (4) that attach the retaining collar (5) to the two locking segments (6). NOTE: Hold the shock strut piston in position when the retaining collar (5) and the lower bearing is removed from the NLG main fitting. It is possible that the shock strut piston can move out of the NLG main fitting if it is not held in position. (4) Lower the retaining collar (5) and remove it from the shock strut piston. (5) Remove the two locking segments (6) from the NLG main fitting. (6) Attach lockwire to the two removal holes on the lower bearing. (7) Pull the lockwire and lower the lower bearing approximately to the middle of the shock strut piston. Make sure that the lower bearing is fully removed from the NLG main fitting. Subtask 32−21−20−030−003 B. Remove the tee seal (9) and the related two sets of the inner and outer back−up rings (11) and (12) from the lower bearing as follows: (1) Remove the three headed pins (7) that secure the spacer ring (8) in the lower bearing. Master EFFECTIVITY: See Pageblock 32−21−20 page 401 32−21−20 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (2) Move the lower bearing down slightly to get access to the spacer ring (8), the tee seal (9), and the two sets of the inner and outer back−up rings (11) and (12), that are installed in the top of the lower bearing. (3) Move the spacer ring (8), the two sets of the inner and outer back−up rings (11) and (12), and the tee seal (9) apart. Subtask 32−21−20−020−004 C. D. E. F. Remove the components that follow from the shock strut piston: NOTE: It is not necessary to remove the spare tee seal (15) from the upper external groove in the lower bearing unless it is damaged. ± the lower bearing ± the tee seal (9) and the related two sets of the inner and outer back−up rings (11) and (12) ± the spacer ring (8). Discard the tee seal (9). Remove and discard the preformed packing (10) from the lower external groove in the lower bearing. NOTE: Do not damage the retainers (13) on each side of the preformed packing (10) when you remove it. It is not necessary to remove the retainers (13) from the lower bearing unless they are damaged. If you suspect that the excluder (14) is unserviceable, remove the excluder (14) from the groove in the retaining collar (5). Master EFFECTIVITY: See Pageblock 32−21−20 page 401 32−21−20 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL NOTE 1 1 Make sure that the radius of the inner back−up ring (11) fits against the radius of the tee seal (9). 2 Make sure that the alignment protrusions on the lower bearing are correctly engaged in the lower cam when the lower bearing is installed. A NLG MAIN FITTING (REF) B 2 2 A ALIGNMENT PROTRUSION (REF) 8 C 12 9 13 11 1 12 C 1. Oil filter plug. 2. Preformed packing. 3. Bolt. 4. Washer. 5. Retaining collar. 6. Locking segment. 7. Headed pin. 8. Spacer ring. 9. Tee seal. 10. Preformed packing. 11. Inner back−up ring. 12. Outer back−up ring. 13. Retainer. 14. Excluder. 15. Spare tee seal. 10 13 LOWER BEARING (REF) 3 6 4 6 SHOCK STRUT PISTON (REF) 14 B 5 ram3221204_001(1).dg, rm, 15/04/97 LEGEND 7 15 11 1 NLG Lower Bearing Seals − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−21−20 page 401 32−21−20 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−21−20−400−801 Installation of the Lower Bearing Seals of the NLG Shock Strut 1. Job Set−Up Information Subtask 32−21−20−943−003 A. Tools and Equipment REFERENCE None specified DESIGNATION Torque wrench 0 to 50 pound−inches (0 to 5.65 N·m) Subtask 32−21−20−944−002 B. Consumable Materials REFERENCE 05−004 02−002 06−002 DESIGNATION Lockwire Hydraulic fluid Petrolatum Subtask 32−21−20−945−001 C. Parts Tools and Equipment REF 2 3 4 7 9 10 13 14 15 NAME OF PART Preformed packing Bolt Washer Headed pin Tee seal (see note below) Preformed packing Retainer Excluder Spare tee seal NOTE: QTY 1 2 2 3 1 1 2 1 1 IPC SEQUENCE NO. IPC 32−21−00−02−092 IPC 32−21−00−04−055 IPC 32−21−00−04−060 IPC 32−21−00−04−021 IPC 32−21−00−04−025 IPC 32−21−00−04−010 IPC 32−21−00−04−015 IPC 32−21−00−04−008 IPC 32−21−00−04−030 The tee seal (9) is an assembly of a tee seal and two sets of the inner and outer back−up rings (11) and (12). Subtask 32−21−20−946−003 D. Reference Information REFERENCE TASK 32−21−15−400−801 TASK 51−26−00−110−801 DESIGNATION Installation of the NLG Axle Assembly Solvent Cleaning Master EFFECTIVITY: See Pageblock 32−21−20 page 401 32−21−20 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 2. Job Set−Up Subtask 32−21−20−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Subtask 32−21−20−110−001 B. C. Clean the shock strut piston and the lower bearing of any unwanted contaminants (Ref. TASK 51−26−00−110−801). Apply a light coating of clean 02−002 hydraulic fluid with a brush to the internal and external surfaces of the shock strut piston and the lower bearing. 3. Procedure Subtask 32−21−20−430−001 Refer to Figure 401. A. Lightly lubricate a new tee seal (9) with clean 02−002 hydraulic fluid or 06−002 petrolatum. B. Install the spacer ring (8), on to the shock strut piston and hold it in position. C. Install the tee seal (9) on the shock strut piston. NOTE: The tee seal (9) is an assembly of a tee seal and two sets of the inner and outer back−up rings (11) and (12). Make sure that they are installed in the correct order. NOTE: Make sure that the radius of each back−up ring (11) (white colored) is installed against the radius of the tee seal (9). D. If it was removed in the removal task (or it had been used before to replace the tee seal (9)), install a new spare tee seal (15) in the upper external groove on the lower bearing. Make sure that it is lightly lubricated with 02−002 hydraulic fluid or 06−002 petrolatum. NOTE: Install only the tee seal in the groove. Do not install the two sets of the inner and outer back−up rings (11) and (12) that is supplied with the new spare tee seal (15). E. Install the preformed packing (10), on the lower bearing as follows: (1) If they were removed in the removal task, install the two retainers (13) in the lower external groove in the lower bearing. (2) Lightly lubricate a new preformed packing (10) with clean 02−002 hydraulic fluid or 06−002 petrolatum. Install the new preformed packing (10) between the retainers (13) on the lower bearing. F. If it was removed in the removal task, install a new excluder (14) on the retaining collar (5). Subtask 32−21−20−420−001 G. Install the lower bearing on to the shock strut piston. Move it up until it collects the tee seal (9) (with the two sets of the inner and outer back−up rings (11) and (12)), and the spacer ring (8) that are installed on the shock strut piston. NOTE: Align the holes in the spacer ring (8) with the holes in the lower bearing. Master EFFECTIVITY: See Pageblock 32−21−20 page 401 32−21−20 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL H. I. J. K. L. M. Install the three headed pins (7). NOTE: Apply a heavy layer of 06−002 petrolatum to the three headed pins (7) to make installation easier. Carefully continue to move the lower bearing up into the NLG main fitting until it touches the lower cam in the NLG main fitting. Rotate the lower bearing until The alignment protrusions on the lower bearing engage their respective slots in the lower cam. The lower bearing will move up slightly when it is correctly engaged. Install the two locking segments (6) into the NLG main fitting. Move the retaining collar (5) up along the piston, attach it to the locking segments (6) with the two bolts (3), and the two washers (4). Torque the bolts (3) to 20 to 25 pound−inches (2.26 to 2.28 N·m). Safety the bolts (3) with 05−004 lockwire. 4. Close Out Subtask 32−21−20−410−001 A. Install the axle assembly (Ref. TASK 32−21−15−400−801). Subtask 32−21−20−941−002 B. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−21−20 page 401 32−21−20 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL SEALS, NLG FLOATING PISTON − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the seals (referred to as the ‘tee seals’ in this procedure) and the wear rings from the nose landing gear (NLG) floating piston. The floating piston is installed in the internal bore of the NLG shock−strut piston. TASK 32−21−25−000−801 Removal of the Floating Piston Seals of the NLG Shock Strut 1. Job Set−Up Information Subtask 32−21−25−943−001 A. Tools and Equipment REFERENCE CAT5643−5B None specified DESIGNATION Extractor, floating piston (Messier−Dowty) Flat pan − 1 gallon (3.78 L) Subtask 32−21−25−946−001 B. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−42−01−000−801 DESIGNATION Put the Aircraft on Jacks Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Removal of the Nosewheel/Tire Assembly 2. Job Set−Up **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED Refer to Figure 401. **ON A/C WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON INSTALLED Refer to Figure 402. **ON A/C ALL Subtask 32−21−25−941−001 A. Install the applicable warning tags on the steering−handwheel control module and the LDG GEAR control handle. Master EFFECTIVITY: See Pageblock 32−21−25 page 401 32−21−25 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−25−865−001 B. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−2 CB NO. F8 F8 NAME NOSE STEER NOSE STEER ZONE 221 222 Subtask 32−21−25−582−001 C. Put the aircraft on jacks (Ref. TASK 07−11−01−582−801). Subtask 32−21−25−010−001 D. Remove the nosewheel/tire assembly (Ref. TASK 32−42−01−000−801). Subtask 32−21−25−490−001 WARNING: E. F. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Put a flat pan under the NLG shock strut piston to collect any hydraulic fluid leakage. NOTE: The NLG shock strut contains approximately 0.75 gallons (2.8 L) of hydraulic fluid. Some of this hydraulic fluid will be released at the bottom of the NLG shock strut as the floating piston is removed from the shock strut piston. Make sure that the container is large enough to contain this volume. Subtask 32−21−25−614−001 OBEY THE SAFETY PRECAUTIONS THAT FOLLOW WHEN YOU DO WORK WITH HIGH−PRESSURE GAS NITROGEN: ± USE A FACE SHIELD ± USE SAFETY GOGGLES ± CLOSE THE VALVES ON THE PIPING AND THE TANKS WHEN THEY ARE NOT USED OR WHEN EMPTY ± GO TO AN AREA THAT HAS A GOOD FLOW OF CLEAN AIR AND GET MEDICAL AID IF YOU BREATHE IN GAS NITROGEN NITROGEN CAN CAUSE SUFFOCATION AND DEATH WHEN IT IS BREATHED IN. WARNING: RELEASE THE PRESSURE FROM THE NLG SHOCK STRUT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS. G. Do the steps that follow to release the nitrogen pressure from the NLG shock strut piston: (1) Open the valve cover (1) on the diaphragm assembly at the bottom of the shock strut and remove the dust cap from the nitrogen charge valve (2). WARNING: Master EFFECTIVITY: See Pageblock 32−21−25 page 401 32−21−25 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL WARNING: DO NOT DEFLATE THE STRUT TOO QUICKLY. YOU CAN CAUSE A SPRAY OF OIL. THIS CAN CAUSE INJURIES TO PERSONS. (2) Slowly loosen the thin nut (3) on the nitrogen charge valve (2) and let the shock strut fully deflate. Subtask 32−21−25−030−001 H. Remove and discard the lockwire from the oil filler plug (4) at the top of the NLG main fitting. WARNING: MAKE SURE THAT THE NITROGEN CHARGE IS FULLY RELEASED FROM THE SHOCK STRUT BEFORE THE OIL FILLER PLUG IS REMOVED. IF YOU DO NOT DO THIS, INJURIES CAN OCCUR. CAUTION: RELEASE THE OIL FILLER PLUG SLOWLY. THERE CAN POSSIBLY BE AIR PRESSURE ON THE OIL SIDE OF THE FLOATING PISTON IF THE PISTON IS LEAKING. I. Remove the oil filler plug (4) and discard the preformed packing (5). **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED 3. Procedure Refer to Figure 401. Subtask 32−21−25−140−003 A. Use a plastic scraper to remove unwanted sealant from the head of the axle pin (6), the washers (7) and (8), the spacer washers (9), and the nut (10). Also remove the sealant on the bottom of the shock strut at the joint between the shock strut piston and the diaphragm assembly. Subtask 32−21−25−010−002 B. Remove the diaphragm assembly from the shock strut piston as follows: (1) Remove and discard the cotter pin (11) from the nut (10). (2) Remove the nut (10), the washers (7) and (8), (as installed), and the spacer washer (9) from the axle pin (6). WARNING: MAKE SURE THAT THE SHOCK STRUT NITROGEN PRESSURE IS FULLY RELEASED BEFORE YOU DO THE STEP THAT FOLLOWS. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT. (3) With the shock strut piston fully deflated, remove the axle pin (6) with the other spacer washer (9) from the axle assembly (12). (4) Carefully remove the diaphragm assembly from the shock strut piston. Subtask 32−21−25−020−001 C. Remove the floating piston from the shock strut piston as follows: (1) Install the threaded rod−end of the floating piston extractor fully into the bottom of the floating piston. Master EFFECTIVITY: See Pageblock 32−21−25 page 401 32−21−25 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (2) Remove the floating piston from the bore of the shock strut piston with the floating piston extractor. NOTE: It is possible that some back pressure will be felt during removal. Be prepared for 02−002 hydraulic fluid to flow from the bore of the shock strut piston when the floating piston is removed. Subtask 32−21−25−030−002 D. E. F. Remove and discard the tee seal (13) and related backing rings from the diaphragm assembly. NOTE: The tee seal (13) is an assembly of a tee seal and two backing rings. Remove and discard the tee seal (14) and related backing rings from the floating piston. NOTE: The tee seal (14) is an assembly of a tee seal with two inner backing rings and two outer backing rings. Remove and discard the two wear rings (15) from the floating piston. **ON A/C WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON INSTALLED 4. Procedure Refer to Figure 402. Subtask 32−21−25−140−002 A. Use a plastic scraper to remove unwanted sealant from the head of the bolt (6), the washers (7) and (8), and the nut (9). Also remove the sealant on the bottom of the shock strut at the joint between the shock strut piston and the diaphragm assembly. Subtask 32−21−25−010−003 B. Remove the diaphragm assembly from the shock strut piston as follows: (1) Remove and discard the cotter pin (10) from the nut (9). (2) Remove the nut (9), the washers (7) and (8) (as installed), from the bolt (6). WARNING: MAKE SURE THAT THE SHOCK STRUT NITROGEN PRESSURE IS FULLY RELEASED BEFORE YOU DO THE STEP THAT FOLLOWS. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT. (3) With the shock strut piston fully deflated, remove the bolt (6) with the washers (8) and (7) (as installed), from the axle/shock strut assembly (11). (4) Carefully remove the diaphragm assembly from the shock strut piston. Subtask 32−21−25−020−002 C. Remove the floating piston from the shock strut piston as follows: (1) Install the threaded rod−end of the floating piston extractor fully into the bottom of the floating piston. (2) Remove the floating piston from the bore of the shock strut piston with the floating Master EFFECTIVITY: See Pageblock 32−21−25 page 401 32−21−25 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL piston extractor. NOTE: It is possible that some back pressure will be felt during removal. Be prepared for 02−002 hydraulic fluid to flow from the bore of the shock strut piston when the floating piston is removed. Subtask 32−21−25−030−003 D. E. F. G. Remove and discard the tee seal (12) and related backing rings from the groove near the top of the the diaphragm assembly. NOTE: The tee seal (12) is an assembly of a tee seal and two backing rings. Remove and discard the preformed packing (13) from the groove near the bottom of the diaphragm assembly. Remove and discard the tee seal (14) and related backing rings from the floating piston. NOTE: The tee seal (14) is an assembly of a tee seal with two inner backing rings and two outer backing rings. Remove and discard the two wear rings (15) from the floating piston. Master EFFECTIVITY: See Pageblock 32−21−25 page 401 32−21−25 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 4 5 A LEGEND NLG MAIN FITTING (REF) 1. Valve cover. 2. Nitrogen charge valve. 3. Thin nut. 4. Oil filler plug. 5. Preformed packing. 6. Axle pin. 7. Washer. 8. Washer. 9. Spacer washer. 10. Nut. 11. Cotter pin. 12. NLG axle assembly. 13. Tee seal. 14. Tee seal. 15. Wear ring. D FW SHOCK STRUT PISTON (REF) 12 7 1 FLOATING PISTON (REF) 15 Use a maximum of two washers (7) as required on the side of the nut (10) to align the slots of the nut (10) with the cotter pin hole of the bolt (6). Use a minimum of one washer (8). 9 3 13 DUST CAP (REF) 14 DIAPHRAGM ASSEMBLY (REF) UP D B UT O 6 1 15 1 B VALVE COVER OPENED FOR CLARITY A B ram3221254_001.dg, rm/ik, 19/04/01 2 9 10 NOTE 1 8 11 Replacement of the NLG Floating Piston Seals Figure 401 Master EFFECTIVITY: See Pageblock 32−21−25 page 401 32−21−25 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 4 5 A LEGEND 1. Valve cover. 2. Nitrogen charge valve. 3. Thin nut. 4. Oil filler plug. 5. Preformed packing. 6. Bolt. 7. Washer. 8. Washer. 9. Nut. 10. Cotter pin. 11. Axle/shock strut piston assembly. 12. Tee seal. 13. Preformed packing. 14. Tee seal. 15. Wear ring. D FW SHOCK STRUT PISTON (REF) 8 10 11 9 NOTE 7 Use a maximum of two washers (7) as required on the side of the nut (9) to align the slots of the nut (9) with the cotter pin hole of the bolt (6). Use a minimum of one washer (8). 2 6 12 UP OU 8 7 3 DUST CAP (REF) D TB 1 FLOATING PISTON (REF) 15 13 14 DIAPHRAGM ASSEMBLY (REF) 15 1 1 B VALVE COVER OPENED FOR CLARITY A B ram3221254_002.dg, rm/ik, 19/04/01 1 NLG MAIN FITTING (REF) Replacement of the NLG Floating Piston Seals Figure 402 Master EFFECTIVITY: See Pageblock 32−21−25 page 401 32−21−25 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL TASK 32−21−25−400−801 Installation of the Floating Piston Seals of the NLG Shock Strut 1. Job Set−Up Information Subtask 32−21−25−943−002 A. Tools and Equipment REFERENCE None specified None specified None specified DESIGNATION Brush Torque wrench 0 to 200 pound−inches (0 to 22.6 N·m) Plastic scraper Subtask 32−21−25−944−001 B. Consumable Materials REFERENCE 02−002 06−002 09−009 09−023 11−007 DESIGNATION Hydraulic fluid, petroleum base Petrolatum Compound, sealing and coating, corrosion inhibitive Compound, sealing and coating, corrosion inhibitive Methyl ethyl keytone (MEK) **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED Subtask 32−21−25−945−001 C. Parts REF 5 6 7 8 9 10 11 13 14 15 NAME OF PART Preformed packing Axle pin Washer Washer Spacer washer Nut Cotter pin Tee seal assembly (with two backup rings) Tee seal assembly (with two inner backup rings and two outer backup rings) Wear ring Master EFFECTIVITY: See Pageblock 32−21−25 page 401 QTY 1 1 A/R 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−21−00−04−045 IPC 32−21−00−02−100 IPC 32−21−00−02−110 IPC 32−21−00−02−115 IPC 32−21−00−02−105 IPC 32−21−00−02−120 IPC 32−21−00−02−125 IPC 32−21−00−04−005 IPC 32−21−00−04−040 2 IPC 32−21−00−04−037 32−21−25 Page 408 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON INSTALLED Subtask 32−21−25−945−002 D. Parts REF 5 6 7 8 9 10 12 13 14 15 NAME OF PART Preformed packing Bolt Washer Washer Nut Cotter pin Tee seal assembly (with two backup rings) Preformed packing Tee seal assembly (with two inner backup rings and two outer backup rings) Wear ring QTY 1 1 A/R 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−21−00−04−045 IPC 32−21−00−02−180 IPC 32−21−00−02−185 IPC 32−21−00−02−190 IPC 32−21−00−02−195 IPC 32−21−00−02−200 IPC 32−21−00−04−005 IPC 32−21−00−04−004 IPC 32−21−00−04−040 2 IPC 32−21−00−04−037 **ON A/C ALL Subtask 32−21−25−946−002 E. Reference Information REFERENCE TASK 07−11−01−582−804 TASK 12−12−32−610−804 TASK 12−20−32−640−801 TASK 32−42−01−400−801 TASK 51−23−00−100−801 TASK 51−23−00−390−804 TASK 51−23−00−390−808 TASK 51−23−00−390−815 TASK 51−26−00−110−801 DESIGNATION Removal of the Aircraft from Jacks Servicing (Oil and Nitrogen) of the NLG Shock Strut − Aircraft on Jacks Lubrication of the Nose Landing Gear Installation of the Nosewheel/Tire Assembly Preparation of Surfaces for Sealant Bead Seal Sealant Procedure Application of Sealant with Brush Curing of Sealant Solvent Cleaning 2. Job Set−Up Subtask 32−21−25−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Master EFFECTIVITY: See Pageblock 32−21−25 page 401 32−21−25 Page 409 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−25−110−001 B. Make sure that the floating piston and diaphragm assembly are clean before you install the seals (Ref. TASK 51−26−00−110−801). **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED 3. Procedure Refer to Figure 401. Subtask 32−21−25−150−003 A. B. Remove any unwanted sealant (Ref. TASK 51−23−00−100−801) that remains on the components that follow: ± The axle pin (6) ± The washers (7) and (8) ± The spacer washers (9) ± The nut (10). At the same time, also remove any unwanted sealant that remains from the area where the spacer washers (9) touch the NLG axle assembly (12) and also on the bottom of the shock strut at the joint between the shock strut piston and the diaphragm assembly. Use a clean low−lint cloth that is moist with 11−007 methyl ethyl keytone (MEK) to remove any remaining sealant and unwanted contamination. Subtask 32−21−25−430−003 C. Install the components that follow on the floating piston and on the diaphragm assembly: (1) Lightly lubricate a serviceable tee seal (13) with 02−002 hydraulic fluid or 06−002 petrolatum. (2) Install the tee seal (13) and related backing rings on the diaphragm assembly. Make sure that the radius of the backing rings fit the radius of the tee seal (13). NOTE: A tee seal (13) is an assembly of a tee seal and two backing rings. (3) Lightly lubricate a serviceable tee seal (14) with 02−002 hydraulic fluid or 06−002 petrolatum. (4) Install the tee seal (14) and related inner and outer backing rings in the middle groove of the floating piston. Make sure that the radius of the backing rings fit the radius of the tee seal (14). NOTE: A tee seal (14) is an assembly of a tee seal with two inner backing rings and two outer backing rings. (5) Install two serviceable wear rings (15) in the upper and the lower grooves of the floating piston. Master EFFECTIVITY: See Pageblock 32−21−25 page 401 32−21−25 Page 410 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−25−110−004 D. Make sure that you clean the bore of the shock strut piston and also the floating piston and the diaphragm assembly of any unwanted contamination before you install the floating piston and the diaphragm assembly (Ref. TASK 51−26−00−110−801). Subtask 32−21−25−420−003 E. Install the floating piston in the shock strut piston as follows: (1) Lightly lubricate the bore of the shock strut piston with 02−002 hydraulic fluid to make installation of the floating piston and the diaphragm assembly easier. (2) Install the threaded rod−end of the floating piston extractor fully into the bottom of the floating piston. (3) Use the floating piston extractor to fully insert the floating piston into the bore of the shock strut piston. Subtask 32−21−25−410−004 F. G. H. I. J. Carefully put the diaphragm assembly into the shock strut piston and align the holes in the diaphragm assembly with their related holes in the NLG axle. Install the axle pin (6) with the spacer washer (9) through the NLG axle assembly (12), the shock strut piston, and the diaphragm assembly from the left side of the landing gear. Install the other spacer washer (9), the washer (8), the washer(s) (7), and the nut (10). NOTE: Use a maximum of two washers (7) if necessary to align the slot in the nut (10) with the cotter pin hole in the axle pin (6) correctly when the nut (10) is torqued. Torque the nut (10) to 140 to 160 pound−inches (15.8 to 18.0 N·m). Safety the nut (10) with the cotter pin (11). Subtask 32−21−25−390−003 Refer to Figure 403. K. Apply a brush coat of 09−023 sealant on the head of the axle pin (6), the washers (7) and (8), the spacer washers (9), and the nut (10). Include the area where the washers touch the NLG axle assembly (12) (Ref. TASK 51−23−00−390−808). L. Apply a bead of 09−009 sealant at the bottom of the shock strut at the joint between the shock strut piston and the diaphragm assembly (Ref. TASK 51−23−00−390−804). NOTE: 09−009 sealant is preferred. If a faster cure time is required, refer to TASK 51−23−00−390−815 for alternate sealants. **ON A/C WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON INSTALLED 4. Procedure Refer to Figure 402. Master EFFECTIVITY: See Pageblock 32−21−25 page 401 32−21−25 Page 411 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−25−150−002 A. B. Remove any unwanted sealant (Ref. TASK 51−23−00−100−801) that remains on the components that follow: ± The bolt (6) ± The washers (7) and (8) ± The nut (9). At the same time, also remove any unwanted sealant that remains from the area where the washers (7) touch the axle/shock strut piston assembly (11) and also on the bottom of the shock strut at the joint between the axle/shock strut piston assembly (11) and the diaphragm assembly. Use a clean low−lint cloth that is moist with 11−007 methyl ethyl keytone (MEK) to remove any remaining sealant and unwanted contamination. Subtask 32−21−25−430−002 C. Install the components that follow on the floating piston and on the diaphragm assembly: (1) Lightly lubricate a serviceable tee seal (12) with 02−002 hydraulic fluid or 06−002 petrolatum. (2) Install the tee seal (12) and related backing rings in the groove near the top of the diaphragm assembly. Make sure that the radius of the backing rings fit the radius of the tee seal (12). NOTE: A tee seal (12) is an assembly of a tee seal and two backing rings. (3) Lightly lubricate a serviceable preformed packing (13) with 02−002 hydraulic fluid or 06−002 petrolatum. (4) Install the preformed packing (13) in the groove near the bottom of the diaphragm assembly. (5) Lightly lubricate a serviceable tee seal (14) with 02−002 hydraulic fluid or 06−002 petrolatum. (6) Install the tee seal (14) and related inner and outer backing rings in the middle groove of the floating piston. Make sure that the radius of the backing rings fit the radius of the tee seal (14). NOTE: A tee seal (14) is an assembly of a tee seal with two inner backing rings and two outer backing rings. (7) Install two serviceable wear rings (15) in the upper and the lower grooves of the floating piston. Subtask 32−21−25−110−003 D. Make sure that you clean the bore of the axle/shock strut piston assembly (11) and also the floating piston and the diaphragm assembly of any unwanted contamination before you install the floating piston and the diaphragm assembly (Ref. TASK 51−26−00−110−801). Master EFFECTIVITY: See Pageblock 32−21−25 page 401 32−21−25 Page 412 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−25−420−002 E. Install the floating piston in the axle/shock strut piston assembly (11) as follows: (1) Lightly lubricate the bore of the axle/shock strut piston assembly (11) with 02−002 hydraulic fluid to make installation of the floating piston and the diaphragm assembly easier. (2) Install the threaded rod−end of the floating piston extractor fully into the bottom of the floating piston. (3) Use the floating piston extractor to fully insert the floating piston into the bore of the axle/shock strut piston assembly (11). Subtask 32−21−25−410−003 F. G. H. I. J. K. Carefully put the diaphragm assembly into the axle/shock strut piston assembly (11). Align the holes in the diaphragm assembly with the related holes in the axle/shock strut piston assembly (11). Install the washers (8) and (7) on the bolt (6). Install the bolt (6) through the axle/shock strut piston assembly (11) and the diaphragm assembly from the left side of the landing gear. Install the other washer (8), the washer(s) (7), and the nut (9). NOTE: Use a maximum of two washers (7) if necessary to align the slot in the nut (9) with the cotter pin hole in the bolt (6) correctly when the nut (9) is torqued. Torque the nut (10) to 140 to 160 pound−inches (15.8 to 18.0 N·m). Safety the nut (10) with the cotter pin (11). Subtask 32−21−25−390−002 Refer to Figure 404. L. Apply a brush coat of 09−023 sealant on the head of the bolt (6), the washers (7) and (8), and the nut (9). Include the area where the washers touch the axle/shock strut piston assembly (11) (Ref. TASK 51−23−00−390−808). M. Apply a bead of 09−009 sealant at the bottom of the shock strut at the joint between the shock strut piston and the diaphragm assembly (Ref. TASK 51−23−00−390−804). NOTE: 09−009 sealant is preferred. If a faster cure time is required, refer to TASK 51−23−00−390−808 for alternate sealants. **ON A/C ALL 5. Close Out Subtask 32−21−25−614−002 A. Pressurize the NLG shock strut with nitrogen (Ref. TASK 12−12−32−610−803). Subtask 32−21−25−640−001 B. Apply a small quantity of 02−002 hydraulic fluid with a brush to the exposed chrome surfaces of the shock strut piston. Master EFFECTIVITY: See Pageblock 32−21−25 page 401 32−21−25 Page 413 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−25−410−002 C. Install the nosewheel/tire assembly (Ref. TASK 32−42−01−400−801). Subtask 32−21−25−586−001 D. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−21−25−865−002 E. Close the circuit breakers that follow: CB PANEL CBP−1 CBP−2 CB NO. F8 F8 NAME NOSE STEER NOSE STEER ZONE 221 222 Subtask 32−21−25−941−002 F. G. Remove the warning tags from the steering−handwheel control module and the LDG GEAR control handle. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−21−25 page 401 32−21−25 Page 414 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL D FW A SEALING AND COATING COMPOUND A 0.150 in. MAX (3.81 mm MAX) SEALING AND COATING COMPOUND APPLY SEALING AND COATING COMPOUND ALL AROUND WHERE PISTON/DIAPHRAGM INDICATED JOINT VALVE COVER (REF) PIN (REF) ram3221154_003.dg, jc, 16/04/01 AXLE/PISTON JOINT NLG Shock Strut Piston, Diaphragm, and Axle − Sealing Figure 403 Master EFFECTIVITY: See Pageblock 32−21−25 page 401 32−21−25 Page 415 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL D FW A LEGEND A 6. Bolt. 7. Washer. 8. Washer. 9. Nut. NOTE Apply grease to the faying surface of the diaphragm assembly between the tee seal and the bottom of the diaphragm assembly. PISTON/DIAPHRAGM JOINT APPLY SEALING AND COATING COMPOUND ALL AROUND WHERE INDICATED VALVE COVER (REF) 9 6 8 7 ram3221254_003.dg, jc/rm, 18/02/03 SEALING AND COATING COMPOUND NLG Integral Axle/Shock Strut Piston and Diaphragm − Sealing Figure 404 Master EFFECTIVITY: See Pageblock 32−21−25 page 401 32−21−25 Page 416 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL ASSEMBLY, NLG SLIDING MEMBER − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow give the steps for the removal and the installation of the sliding member assembly (referred to as the ‘shock strut piston’ in this procedure) of the nose landing gear (NLG). The sliding member assembly is composed of all of the NLG internal components that are contained within the NLG main fitting. NOTE: A locally manufactured shop aid (or a tool that is equivalent in function to the hydraulic schematic in Figure 406) will be required to correctly service the NLG with 02−002 hydraulic fluid after the shock strut piston is installed. The use of this shop aid will make sure that any trapped air that remains in the NLG (after assembly) is removed. An example of the components may be required to assemble the shop aid (referred to as the ‘NLG air purge tool’ in this procedure) are given in the installation procedure and an illustration is provided. B. For the nitrogen gas pressure in the shock strut piston to be measured accurately after the NLG is assembled in the installation TASK, the procedure that follows must be done in a controlled ambient temperature of 59 to 95 °F (15 to 35 °C). C. The steps are also given to disassemble the shock strut piston (and also to assemble it again) after it is removed from the NLG main fitting. NOTE: Special tools are identified in these steps that will be required if the NLG shock strut is to be disassembled after it is removed. These tools are available from Messier−Dowty. NOTE: These steps must be done on a bench with a vise that is large enough to securely hold the DST100−32 holding blocks. NOTE: At an out station (or to reduce the removal/installation time), a different serviceable shock strut piston (that has been pre−assembled) can be installed in the NLG main fitting. TASK 32−21−30−000−801 Removal of the NLG Sliding Member 1. Job Set−Up Information Subtask 32−21−30−943−001 **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED A. Tools and Equipment NOTE: Special tools are identified in this procedure, but (where noted), alternate tools that have been determined by the operator as being equivalent can be used. REFERENCE CAT5643−12C DESIGNATION Torque wrench adaptor (Messier−Dowty) (required only if the shock strut piston will be disassembled after removal) Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REFERENCE CAT5643−5B or equivalent (see note in the procedure) CAT5643−7B DST100−32 DESIGNATION Extractor, floating piston (Messier−Dowty) Torque wrench adaptor (Messier−Dowty) (required only if the shock strut piston will be disassembled after removal) Holding blocks (Messier−Dowty) (required only if the shock strut piston will be disassembled after removal) **ON A/C WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON INSTALLED B. Tools and Equipment NOTE: Special tools are identified in this procedure, but (where noted), alternate tools that have been determined by the operator as being equivalent can be used. REFERENCE CAT5643−12C CAT5643−5B or equivalent (see note in the procedure) CAT5643−7B DST100−32 None specified None specified None specified None specified None specified DESIGNATION Torque wrench adaptor (required only if the shock strut piston will be disassembled after removal) Extractor, floating piston Torque wrench adaptor (required only if the shock strut piston will be disassembled after removal) Holding blocks (required only if the shock strut piston will be disassembled after removal) Wrench, adjustable, 3 inch (7.5 cm) adjustable range (required only if the shock strut piston will be disassembled after removal) Brush, synthetic bristle 0.5 inch (12 mm) wide Flat pan or bucket − 1 gallon (3.78 L) minimum capacity Scraper, non−ferrous Strap wrench Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL Subtask 32−21−30−944−001 C. Consumable Materials REFERENCE 02−002 02−003 05−054 11−007 DESIGNATION Hydraulic fluid, petroleum base Landing gear shock strut fluid, anti−wear Cloth, crocus (polishing) Methyl Ethel Ketone (MEK) Subtask 32−21−30−946−001 **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED D. Reference Information REFERENCE TASK 32−21−15−000−801 DESIGNATION Removal of the NLG Axle Assembly **ON A/C WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON INSTALLED E. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−42−01−000−801 DESIGNATION Put the Aircraft on Jacks Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Removal of the Nosewheel/Tire Assembly **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED 2. Job Set−Up Subtask 32−21−30−010−001 A. Remove the axle from the NLG (Ref. TASK 32−21−15−000−801). NOTE: There is approximately 20 inches (50 cm) of shock strut piston in the NLG main fitting with the NLG in the fully extended position. Make sure that there will be enough clearance under the NLG main fitting for the shock strut piston to be removed. Subtask 32−21−30−030−001 **ON A/C 7003−7067, 7069−7273 Pre VSBM−DT−16040−32−12 Refer to Figure 403. **ON A/C 7274−7501 and ON A/C 7003−7067, 7069−7273 Post VSBM−DT−16040−32−12 Refer to Figure 404. Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7003−7067, 7069−7501 B. Remove the floating piston from the shock strut piston as follows: (1) Install the threaded rod−end of the CAT5643−5B floating piston extractor (or equivalent) fully into the bottom of the floating piston. A slide−hammer that is approximately 30 inches (15 cm) long and has a 1/4−28 NF thread can be used if the CAT5643−5B floating piston extractor is not available. (2) Remove the floating piston from the bore of the shock strut piston with the floating piston extractor. NOTE: It is possible that some back pressure will be felt during removal. Be prepared for 02−002 hydraulic fluid to flow from the bore of the shock strut piston when the floating piston is removed. C. Remove and discard the tee seal (14) and related backing rings from the middle groove of the floating piston. NOTE: The tee seal (14) is an assembly of a tee seal with two inner backing rings and two outer backing rings. D. If they are visibly damaged, remove and discard the two wear rings (15) from the upper and the lower grooves of the floating piston. NOTE: It is not necessary to remove the two wear rings (15) from the floating piston unless they are damaged. **ON A/C WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON INSTALLED 3. Job Set−Up Subtask 32−21−30−941−001 A. Install a DO NOT OPERATE warning tag on the steering−handwheel control module and the landing−gear control lever. Subtask 32−21−30−865−001 B. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−2 CB NO. F8 F8 NAME NOSE STEER NOSE STEER ZONE 221 222 Subtask 32−21−30−582−001 WARNING: C. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL D. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). NOTE: There is approximately 20 inches (50 cm) of shock strut piston in the NLG main fitting with the NLG in the fully extended position. Make sure that there will be enough clearance under the NLG main fitting for the shock strut piston to be removed. Subtask 32−21−30−010−002 E. Remove the nosewheel/tire assemblies (Ref. TASK 32−42−01−000−801). Subtask 32−21−30−840−001 F. Put a flat pan or bucket under the shock strut piston to collect any hydraulic fluid leakage. NOTE: The NLG shock strut contains approximately 0.75 gallons (2.8 L) of hydraulic fluid. Some of this hydraulic fluid will be released at the bottom of the NLG shock strut as the floating piston is removed from the shock strut piston. Make sure that the container is large enough to contain this volume. Subtask 32−21−30−614−001 Refer to Figure 401. WARNING: OBEY THE SAFETY PRECAUTIONS THAT FOLLOW WHEN YOU DO WORK WITH HIGH−PRESSURE GAS NITROGEN: ± USE A FACE SHIELD ± USE SAFETY GOGGLES ± CLOSE THE VALVES ON THE PIPING AND THE TANKS WHEN THEY ARE NOT USED OR WHEN EMPTY ± GO TO AN AREA THAT HAS A GOOD FLOW OF CLEAN AIR AND GET MEDICAL AID IF YOU BREATHE IN GAS NITROGEN NITROGEN CAN CAUSE SUFFOCATION AND DEATH WHEN IT IS BREATHED IN. WARNING: RELEASE THE PRESSURE FROM THE NLG SHOCK STRUT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS. G. Do the steps that follow to release the nitrogen pressure from the NLG shock strut: (1) Open the valve cover on the diaphragm assembly at the bottom of the shock strut piston and make sure that the thin nut (3) on the nitrogen charge valve (2) is fully closed. (2) Remove the dust cap (1) from the nitrogen charge valve (2). WARNING: DO NOT DEFLATE THE STRUT TOO QUICKLY. YOU CAN CAUSE A SPRAY OF OIL. THIS CAN CAUSE INJURIES TO PERSONS. (3) Slowly loosen the thin nut (3) on the nitrogen charge valve (2) and let the shock strut fully deflate. (4) Remove and discard the lockwire from the nitrogen charge valve (2) in the diaphragm assembly. (5) Loosen the nitrogen charge valve (2) in the diaphragm assembly a small amount. As the nitrogen charge valve (2) is loosened, look and listen for a nitrogen/hydraulic Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL fluid mixture escaping from the bleed port in the nitrogen charge valve (2). (6) If present, allow the nitrogen pressure to bleed off and then continue to remove the nitrogen charge valve (2) from the diaphragm assembly. (7) Remove and discard the preformed packing (4) from the nitrogen charge valve (2). (8) Remove and discard the lockwire from the oil filler plug (5) at the top of the NLG main fitting. WARNING: MAKE SURE THAT THE NITROGEN CHARGE IS FULLY RELEASED FROM THE SHOCK STRUT BEFORE THE OIL FILLER PLUG IS REMOVED. IF YOU DO NOT DO THIS, INJURIES CAN OCCUR. CAUTION: RELEASE THE OIL FILLER PLUG SLOWLY. THERE CAN POSSIBLY BE AIR PRESSURE ON THE OIL SIDE OF THE FLOATING PISTON IF THE PISTON IS LEAKING. (9) Loosen the oil filler plug (5) in the oil filler port a small amount. As the oil filler plug (5) is loosened, look and listen for a nitrogen/hydraulic fluid mixture escaping from the bleed port in the oil filler plug (5). (10) If present, allow the nitrogen pressure to bleed off and then continue to remove the oil filler plug (5) from the oil filler port. (11) Remove and discard the preformed packing (6) from the oil filler plug (5). Subtask 32−21−30−140−001 Refer to Figure 402. H. Use a non−ferrous scraper to remove unwanted sealant from around the joint between the shock strut piston and the diaphragm assembly. I. Use a non−ferrous scraper to remove unwanted sealant from the head of the bolt, the washers, and the nut that secures the diaphragm assembly to the axle of the shock strut piston. Subtask 32−21−30−030−002 **ON A/C 7003−7067, 7069−7273 Pre VSBM−DT−16040−32−12 Refer to Figure 403. **ON A/C 7274−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7273 Post VSBM−DT−16040−32−12 Refer to Figure 404. **ON A/C WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON INSTALLED WARNING: HOLD THE TOP TORQUE LINK WHEN YOU RELEASE THE QUICK DISCONNECT PINS. THE TOP TORQUE LINK IS SPRING LOADED AND WILL MOVE UP QUICKLY. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT. J. Pull the quick−disconnect pins on torque link assembly to disconnect the lower torque link (16) from the upper torque link (17). K. Remove the diaphragm assembly from the shock strut piston as follows: (1) Remove and discard the cotter pin (10) from the nut (9). (2) Remove the nut (9), the washers (7) and (8) (as installed), from the bolt (6). Master EFFECTIVITY: See Pageblock 32−21−30 page 401 406 32−21−30 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL WARNING: L. M. N. O. P. MAKE SURE THAT THE SHOCK STRUT NITROGEN PRESSURE IS FULLY RELEASED BEFORE YOU DO THE STEP THAT FOLLOWS. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT. CAUTION: THE FLOATING PISTON MIGHT COME OUT OF THE NLG AXLE ON THE REMOVAL OF THE NLG AXLE DIAPHRAGM. IF YOU ARE NOT CAREFUL , YOU MAY DAMAGE THE AIRCRAFT AND THE EQUIPMENT. (3) With the shock strut piston fully deflated, remove the bolt (6) and the washers (8) and (7) (as installed), from the shock strut piston. (4) Carefully remove the diaphragm assembly from the shock strut piston. NOTE: If necessary, you may need to do the steps that follow to make the removal of the diaphragm assembly easier: (a) Install a strap wrench on the shock strut piston to keep it from turning. If necessary, use crocus paper (or equivalent) under the strap to protect the surface of the shock strut piston. Put the smooth surface of the crocus paper against the shock strut piston. (b) Use a wrench (at the vertical surface where the nitrogen charge valve (2) was removed) to gently twist the diaphragm assembly. Use a wrench with wide contact surfaces (such as an adjustable wrench) so that you do not damage the vertical surfaces of the diaphragm assembly. Remove and discard the tee seal (12) and related backing rings from the groove near the top of the diaphragm assembly. NOTE: The tee seal (12) is an assembly of a tee seal and two backing rings. Remove and discard the preformed packing (13) from the groove near the bottom of the diaphragm assembly. Remove the floating piston from the shock strut piston as follows: (1) Install the threaded rod−end of the CAT5643−5B floating piston extractor (or equivalent) fully into the bottom of the floating piston. A slide−hammer that is approximately 30 inches (15 cm) long and has a 1/4−28 NF thread can be used if the floating piston extractor is not available. (2) Remove the floating piston from the bore of the shock strut piston with the floating piston extractor. NOTE: It is possible that some back pressure will be felt during removal. Be prepared for 02−002 hydraulic fluid to flow from the bore of the shock strut piston when the floating piston is removed. Remove and discard the tee seal (14) and related backing rings from the middle groove of the floating piston. NOTE: The tee seal (14) is an assembly of a tee seal with two inner backing rings and two outer backing rings. If they are visibly damaged, remove and discard the two wear rings (15) from the upper and the lower grooves of the floating piston. NOTE: It is not necessary to remove the two wear rings (15) from the floating piston unless they are damaged. Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7003−7067, 7069−7273 Pre VSBM−DT−16040−32−12 Q. If the shock strut piston that is to be removed is not the same one that will be installed again in the installation procedure, do the steps that follow to remove the lower torque link (16), the jacking pad (24), and the uplock bracket (32): WARNING: HOLD THE TOP TORQUE LINK WHEN YOU RELEASE THE QUICK DISCONNECT PINS. THE TOP TORQUE LINK IS SPRING LOADED AND WILL MOVE UP QUICKLY. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT. (1) Pull the quick−disconnect pins on torque link assembly to disconnect the lower torque link (16) from the upper torque link (17). (2) Remove and discard the cotter pin (18) from the bolt (22). (3) Remove the nut (19), and the washers (20) and/or (21) from the bolt (22). NOTE: There can be more than one washer adjacent to the nut (19). (4) Remove the bolt (22) with the washer (21) and the countersunk washer (23), that attaches the jacking pad (24) to the torque pin (25). (5) Hold the lower torque link (16) and the jacking pad (24). Remove the torque pin (25) to disconnect the lower torque link (16) and the jacking pad (24) from the attachment lugs on bottom of the shock strut piston. (6) Remove and discard the cotter pin (26). (7) Remove the nut (28), the washer (29), and the uplock pin (27). (8) Remove and discard the lockwire from the bolts (30). (9) Remove the bolts (30), the washers (31), the uplock bracket (32), and the uplock spacer (33). **ON A/C 7274−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7273 Post VSBM−DT−16040−32−12 R. If the shock strut piston that is to be removed is not the same one that will be installed again in the installation procedure, do the steps that follow to remove the lower torque link (16), the jacking pad (25), and the uplock bracket (34): WARNING: HOLD THE TOP TORQUE LINK WHEN YOU RELEASE THE QUICK DISCONNECT PINS. THE TOP TORQUE LINK IS SPRING LOADED AND WILL MOVE UP QUICKLY. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT. (1) Pull the quick−disconnect pins on torque link assembly to disconnect the lower torque link (16) from the upper torque link (17). (2) Remove and discard the cotter pin (18) from the bolt (23). (3) Remove the nut (19), and the washers (20) and/or (21) from the bolt (23). NOTE: There can be more than one washer on the side of the nut (19). (4) Make sure that the lower torque link (16) is in a position that causes the least amount of torsion in the torsion spring (27) that is installed on the jacking pad (25). (5) Remove the bracket (22) from the bolt (23). (6) Remove the bolt (23) with the countersunk washer (24), that attaches the jacking pad (25) to the torque pin (26). Master EFFECTIVITY: See Pageblock 32−21−30 page 401 408 32−21−30 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (7) Hold the lower torque link (16) and the jacking pad (25). Remove the torque pin (26) to disconnect the lower torque link (16) and the jacking pad (25) from the attachment lugs on bottom of the shock strut piston. (8) If required for other maintenance, remove the torsion spring (27) from the jacking pad (25). (9) Remove and discard the cotter pin (28). (10) Remove the nut (30), the washer (31), and the uplock pin (29). (11) Remove and discard the lockwire from the bolts (32). (12) Remove the bolts (32), the washers (33), the uplock bracket (34), and the uplock spacer (35). **ON A/C ALL 4. Procedure Refer to Figure 405. Subtask 32−21−30−020−001 A. Do the steps that follow to remove the shock strut piston from the NLG main fitting: (1) Remove and discard the lockwire from the two bolts (40). (2) Lift the shock strut piston approximately 1 inch (2.5 cm) from its fully extended position. (3) Remove the two bolts (40) and the two washers (41) that attach the retaining collar (42) to the two locking segments (43). NOTE: Hold the shock strut piston in position when the retaining collar (42) is disconnected from the NLG main fitting. It is possible that the shock strut piston can move out of the NLG main fitting if it is not held in position. (4) Lower the retaining collar (42) on the shock strut piston away from the NLG main fitting. (5) Remove the two locking segments (43) from the NLG main fitting. (6) Rotate the shock strut piston so that its axle is 90 degrees to the centerline of the aircraft. NOTE: The horizontal surfaces of the lower cam and the upper cam will be adjacent to each other as the shock strut piston is removed from the NLG main fitting. In this position the shock strut piston will not have a tendency to rotate as you remove it. (7) Carefully begin to remove the shock strut piston from the NLG main fitting. As the shock strut piston is removed from the NLG main fitting, make sure that the two pins (45) are removed from the lower cam (46) and that the two halves of the upper bearing (47) are removed from the upper cam (48). NOTE: The NLG main fitting contains approximately 0.75 gallons (2.8 L) of hydraulic fluid. Some of this hydraulic fluid will be released at the bottom of the NLG main fitting when the NLG shock strut piston is removed. Make sure that the container is large enough to contain this volume. Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 409 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−30−030−003 B. If the disassembly of the shock strut piston is required for other maintenance (to replace the excluder (44), or the tee seals (61), (66), or (69), or the preformed packing (70) for example) remove the applicable components that follow from the shock strut piston: NOTE: The steps that follow must be done on a bench with a vise that is large enough to securely hold the DST100−32 holding blocks. Other special tools are required. (1) Put the shock strut piston between the two DST100−32 holding blocks and securely clamp the two holding blocks in the bench vise. (2) Do the steps that follow to remove the taxi valve seat (49), the taxi valve (50), and the spring (51) from the taxi valve body (52): NOTE: The taxi valve (50) and the taxi valve seat (49) are matched parts and must be kept together. (a) Use a punch and lift the deformed edges of the cup washer (53). (b) Use the CAT5643−7B and CAT5643−12C torque wrench adapters and remove the taxi valve seat (49). (c) Remove the cup washer (53). (d) Remove the taxi valve (50) and the spring (51). (3) Do the steps that follow to remove the taxi valve body (52) from the top of the shock strut piston: (a) Use a punch and lift the deformed edges of the cup washer (54). (b) Use the CAT5643−12C torque wrench adapter and remove the locknut (55). (c) Remove the cup washer (54). (d) Move the taxi valve body (52) down to get access to the retaining ring (56). (e) Remove the retaining ring (56) from the groove in the top of the shock strut piston. (f) Remove the taxi valve body (52) from the top of the shock strut piston. (4) Remove the upper cam (48), the lower cam (46), and the lower bearing (57) as follows: (a) Push the upper cam (48) towards the top of the shock strut piston and remove the retaining ring segments (58) and the two pins (59). (b) Remove the upper cam (48), from the shock strut piston. (c) Remove the rebound ring (60) from the external groove in the upper cam (48). (d) Remove and discard the tee seal (61) from the internal groove in the upper cam (48). NOTE: The tee seal (61) is an assembly of the tee seal (61) and two sets of inner back−up rings (62) and outer back−up rings (63). When you remove the tee seal (61), do not damage the inner and outer back−up rings (62) and (63) on each side of the tee seal (61). It is not necessary to discard the inner and outer back−up rings (62) and (63) unless they are damaged. (e) Remove the lower cam (46). Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 410 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (f) Remove the lower bearing (57). (5) Remove the components that follow from the lower bearing (57): (a) Remove the three headed pins (64) that secure the spacer ring (65) in the lower bearing (57). (b) Remove the spacer ring (65), the tee seal (66), and (if required) the related back−up rings (67) and (68) from the top of the lower bearing (57). Discard the tee seal (66). NOTE: The tee seal (66) is an assembly of the tee seal (66) and two sets of inner back−up rings (67) and outer back−up rings (68). When you remove the tee seal (66), do not damage the inner and outer back−up rings (67) and (68) on each side of the tee seal (66). It is not necessary to discard the inner and outer back−up rings (67) and (68) unless they are damaged. NOTE: If it is installed, it is not necessary to remove the spare tee seal (69) from the upper external groove in the lower bearing (57) unless it is damaged. (c) Remove the preformed packing (70) from the lower external groove in the lower bearing (57). Discard the preformed packing (70). NOTE: When you remove the preformed packing (70), do not damage the two back−up rings (71) on each side of the preformed packing (70). It is not necessary to remove the back−up rings (71) from the lower bearing (57) unless they are damaged. (6) Remove the retaining collar (42) from the shock strut piston. (7) If you suspect that the excluder (44) is unserviceable, remove the excluder (44) from the groove in the retaining collar (42). Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 411 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Dust cap. 2. Nitrogen charge valve. 3. Thin nut. 4. Preformed packing. 5. Oil filler plug. 6. Preformed packing. 7. MS28778−4 preformed packing. 8. AN815−4D union. A NOTE X = Chrome Extension. 8 7 5 6 C SERVICE PLATE C 1 2 4 SHOCK STRUT ASSEMBLY X VALVE COVER B B A NOSE LANDING GEAR ram1212323_002.dg, pt/pw, 29/08/02 DIAPHRAGM ASSEMBLY 3 Oil and Nitrogen Servicing of the NLG Shock Strut Figure 401 Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 412 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL D FW A LEGEND A 6. Bolt. 7. Washer. 8. Washer. 9. Nut. NOTE Apply grease to the faying surface of the diaphragm assembly between the tee seal and the bottom of the diaphragm assembly. PISTON/DIAPHRAGM JOINT APPLY SEALING AND COATING COMPOUND ALL AROUND WHERE INDICATED VALVE COVER (REF) 9 6 8 7 ram3221254_003.dg, jc/rm, 18/02/03 SEALING AND COATING COMPOUND NLG Integral Axle/Shock Strut Piston and Diaphragm − Sealing Figure 402 Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 413 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 4 5 A LEGEND 1. Valve cover. 2. Nitrogen charge valve. 3. Thin nut. 4. Oil filler plug. 5. Preformed packing. 6. Bolt. 7. Washer. 8. Washer. 9. Nut. 10. Cotter pin. 11. Axle/shock strut piston assembly. 12. Tee seal. 13. Preformed packing. 14. Tee seal. 15. Wear ring. D FW SHOCK STRUT PISTON (REF) 8 10 11 9 NOTE 7 Use a maximum of two washers (7) as required on the side of the nut (9) to align the slots of the nut (9) with the cotter pin hole of the bolt (6). Use a minimum of one washer (8). 2 6 12 UP OU 8 7 3 DUST CAP (REF) D TB 1 FLOATING PISTON (REF) 15 13 14 DIAPHRAGM ASSEMBLY (REF) 15 1 1 B VALVE COVER OPENED FOR CLARITY A B ram3221254_002.dg, rm/ik, 19/04/01 1 NLG MAIN FITTING (REF) NLG Attaching Components − Removal/Installation Figure 403 (Sheet 1 of 2) Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 414 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL QUICK− DISCONNECT PINS (REF) 17 FW D SHOCK STRUT PISTON (REF) D FW 16 LEGEND 16. Lower torque link. 17. Upper torque link. 18. Cotter pin. 19. Nut. 20. Washer. 21. Washer. 22. Bolt. 23. Countersink washer. 24. Jacking pad. 25. Torque pin. 26. Cotter pin. 27. Uplock pin. 28. Nut. 29. Washer. 30. Bolt. 31. Washer. 32. Uplock bracket. 33. Uplock spacer. 18 19 20 21 21 23 24 22 25 27 30 31 32 FW D 29 28 If necessary, use washer(s) (20 or 21) as required to align the slots of the nut (19) with the cotter pin hole of the bolt (22). A maximum of two washers on the nut side are permitted. 26 33 ram3221304_001.dg, rm, 25/07/02 NOTE NLG Attaching Components − Removal/Installation Figure 403 (Sheet 2 of 2) Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 415 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 4 5 A LEGEND 1. Valve cover. 2. Nitrogen charge valve. 3. Thin nut. 4. Oil filler plug. 5. Preformed packing. 6. Bolt. 7. Washer. 8. Washer. 9. Nut. 10. Cotter pin. 11. Axle/shock strut piston assembly. 12. Tee seal. 13. Preformed packing. 14. Tee seal. 15. Wear ring. D FW SHOCK STRUT PISTON (REF) 8 10 11 9 NOTE 7 Use a maximum of two washers (7) as required on the side of the nut (9) to align the slots of the nut (9) with the cotter pin hole of the bolt (6). Use a minimum of one washer (8). 2 6 12 UP OU 8 7 3 DUST CAP (REF) D TB 1 FLOATING PISTON (REF) 15 13 14 DIAPHRAGM ASSEMBLY (REF) 15 1 1 B VALVE COVER OPENED FOR CLARITY A B ram3221254_002.dg, rm/ik, 19/04/01 1 NLG MAIN FITTING (REF) NLG Attaching Components − Removal/Installation Figure 404 (Sheet 1 of 2) Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 416 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL QUICK− DISCONNECT PINS (REF) 17 FW D SHOCK STRUT PISTON (REF) D FW 16 LEGEND 16. Lower torque link. 17. Upper torque link. 18. Cotter pin. 19. Nut. 20. Washer. 18 19 21. Washer. 20 21 22. Bracket. 22 23. Bolt. 24. Countersink washer. 25. Jacking pad. 26. Torque pin. 27. Torsion spring. 28. Cotter pin. 29. Uplock pin. 30. Nut. 31. Washer. 32. Bolt. 33. Washer. 34. Uplock bracket. 35. Uplock spacer. 27 26 25 24 23 29 32 33 34 FW D 31 If necessary, use washer(s) (20 or 21) as required to align the slots of the nut (19) with the cotter pin hole of the bolt (23). A maximum of two washers on the nut side are permitted. 28 35 ram3221304_002.dg, rm, 20/08/02 30 NOTE NLG Attaching Components − Removal/Installation Figure 404 (Sheet 2 of 2) Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 417 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 59 58 A 47 LEGEND 60 40. Bolt. 41. Washer. 42. Retaining collar. 43. Locking segment. 44. Excluder. 45. Pin. 46. Lower cam. 47. Upper bearing. 48. Upper cam. 57. Lower bearing. 58. Retaining ring segment. 59. Pin. 60. Rebound ring. 65 61. Tee seal. 62. Inner back−up ring. 63. Outer back−up ring. 64. Headed pin. 65. Spacer ring. 69 66. Tee seal. 71 67. Inner back−up ring. 70 68. Outer back−up ring. 69. Tee seal (spare). 71 70. Preformed packing. 40 71. Back−up ring. 41 NOTES 2 Make sure that the radius of the inner back−up ring fits against the radius of the tee seal. 63 62 46 61 62 45 63 57 64 68 43 67 66 67 44 Make sure that the alignment protrusions on the lower bearing (57) are correctly engaged in the lower cam (46) when the lower bearing (57) is installed. 68 42 A SHOCK STRUT PISTON (REF) ram3221304_003.dg, rm, 20/08/02 1 48 Shock Strut Piston − Removal/Installation Figure 405 (Sheet 1 of 2) Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 418 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 55 49 51 53 49 54 50 56 51 50 53 55 52 54 TAXI VALVE ASSEMBLY (SHOWN ASSEMBLED) 56 52 SHOCK STRUT PISTON (REF) LEGEND 49. Taxi valve seat. 50. Taxi valve. 51. Spring. 52. Taxi valve body. 53. Cup washer. 54. Cup washer. 55. Locknut. 56. Retaining ring. The taxi valve (50) and the taxi valve body (52) are matched parts and must be kept together. ram3221304_004.dg, rm, 20/08/02 NOTE Shock Strut Piston − Removal/Installation Figure 405 (Sheet 2 of 2) Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 419 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−21−30−400−801 Installation of the NLG Sliding Member 1. Job Set−Up Information Subtask 32−21−30−943−002 A. Tools and Equipment NOTE: Special tools are identified in this procedure, but (where noted), alternate tools that have been determined by the operator as being equivalent can be used. REFERENCE CAT5643−12C CAT5643−13C CAT5643−14D CAT5643−15D CAT5643−4B or equivalent (see note in the procedure) CAT5643−6B CAT5643−7B CTR200−538 DST100−32 G601R121611−1 None specified None specified None specified None specified None specified None specified DESIGNATION Torque wrench adaptor (required only if the shock strut piston was disassembled in the removal procedure) Torque wrench adaptor (required only if the shock strut piston was disassembled in the removal procedure) Alignment tool Alignment tool Installation tool, floating piston Split guide Torque wrench adaptor (required only if the shock strut piston was disassembled in the removal procedure) Servicing cart, high/low pressure nitrogen gas Holding blocks (required only if the shock strut piston was disassembled in the removal procedure) Kit, nitrogen charging adapter Bench with vise (required only if the shock strut piston was disassembled in the removal procedure) Brush, synthetic bristle 0.5 inch (12 mm) wide Brush, artists, fine tip Punch, spherical end − 0.187 to 0.240 inch (4.75 to 6.10 mm) (required only if the shock strut piston was disassembled in the removal procedure) Scraper, non−ferrous Torque wrench 0 to 50 pound−inches (0 to 5.65 N·m) Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 420 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REFERENCE None specified None specified None specified PF54124−3PWS 14−6804−8000 14−6805−8000 753D1100 B. DESIGNATION Torque wrench 0 to 200 pound−inches (0 to 22.6 N·m) Torque wrench 0 to 800 pound−inches (0 to 96.0 N·m) (required only if the shock strut piston was disassembled in the removal procedure) Torque wrench 0 to 2100 pound−inches (0 to 237 N·m) (required only if the shock strut piston was disassembled in the removal procedure) Service unit, 2 U.S. gallons (7.6 liters) Regulator, strut/accumulator service Kit, charging and gauging, strut/accumulator Jack, NLG axle Shop aids NOTE: A locally manufactured shop aid (or a tool that is equivalent in function to the hydraulic schematic in Figure #406) is identified in this procedure and will be required to correctly service the NLG with 02−002 hydraulic fluid after the shock strut piston is installed. The parts (and their source of supply) listed in the table that follows are examples of those components that will be necessary to build the shop aid, but are not mandatory. Alternate parts that have been determined by the operator as being equivalent in function can be used. The parts must be rated for 1000 PSI (6895 kPa) minimum and be acceptable for use with petroleum based hydraulic fluid. The gauge should have an accuracy of ±2% at 250 PSI (1724 kPa). Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 421 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL PART NUMBER ITEM PART QTY (see note) 1 Selector valve − 2 position, 1 6W567 3 way, petroleum base (Prince Hydraulics P/N hydraulic fluid compatible SS−2A1D 2 Pressure gauge − 1000 PSI 1 5A044 (6895 kPa), 1/4 inch NPT (Ametek gauge) connection, 3−2−3% 5WK78 accuracy (Ashcroft gauge) 3 Reducer bushing − 1/2 inch 4 2F437 male NPTF / 1/4 inch (Aeroquip P/N 2081−8−4S) female NPTF 4 Hose adaptor − JIC 7/16−20 2 4HM21 flare tube end / 1/4 inch (Aeroquip P/N 2021−4−4S) male NPTF 5 Hose assembly − high 1 3F805 pressure, 1/4 inch I.D., 48 (Aeroquip HI−PAC hose) inch length 6 Hose barb − 3/8 inch barb 1 4A488 end / 1/4 inch male NPTF 7 Hose clamp − worm drive, 1 stainless steel, 3/8 inch (nominal size) Drain tube − low pressure, A/R None specified 8 low density polyethylene (or similar), 3/8 inch I.D., 5 foot (1.5 m) length SOURCE OF SUPPLY (see note) Grainger (a subsidiary of W. W. Grainger, Inc.) www.grainger.com None specified Subtask 32−21−30−944−002 C. Consumable Materials REFERENCE None specified 02−002 02−003 04−005 05−002 05−004 05−005 05−037 05−054 06−002 DESIGNATION Soap, hand dishwashing, liquid Hydraulic fluid, petroleum base Landing gear shock strut fluid, anti−wear Grease, arcraft and instrument, gear and actuator screw Nitrogen, technical Lockwire Lockwire Compound, leak detection, oxygen systems Cloth, crocus (polishing) Petrolatum, (petroleum jelly) technical, soft Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 422 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REFERENCE 06−028 09−009 09−023 11−007 16−003 (or equivalent) DESIGNATION Compound, corrosion−preventative, solvent cutback, cold application Compound, sealing and coating, corrosion inhibitive Compound, sealing and coating, corrosion inhibitive Methyl Ethel Ketone (MEK) Red paint Subtask 32−21−30−945−001 Refer to Figure 401. D. Parts REF 4 6 7 8 NAME OF PART Preformed packing Preformed packing Preformed packing, MS28778−4 Union, AN815−4D QTY 1 1 1 1 IPC SEQUENCE NO. IPC 32−21−00−02−092 IPC 32−21−00−03−013 None specified None specified **ON A/C 7003−7067, 7069−7273 Pre VSBM−DT−16040−32−12 Subtask 32−21−30−945−002 Refer to Figure 403. E. Parts REF 6 7 8 9 10 12 13 14 15 18 19 20 21 22 23 NAME OF PART QTY Bolt 1 Washer 2 Spacer washer 2 Nut 1 Cotter pin 1 Tee seal assembly (with two backup rings) 1 Preformed packing 1 Tee seal assembly (with two backup rings) 1 Wear ring 2 Cotter pin 1 Nut 1 Washer 1 Washer 2 Bolt 1 Countersunk washer 1 Master EFFECTIVITY: See Pageblock 32−21−30 page 401 IPC SEQUENCE NO. IPC 32−21−00−02−180 IPC 32−21−00−02−185 IPC 32−21−00−02−190 IPC 32−21−00−02−195 IPC 32−21−00−02−200 IPC 32−21−00−04−005 IPC 32−21−00−04−004 IPC 32−21−00−04−040 IPC 32−21−00−04−037 IPC 32−21−00−02−085 IPC 32−21−00−02−080 IPC 32−21−00−02−075 IPC 32−21−00−02−070 IPC 32−21−00−02−060 IPC 32−21−00−02−065 32−21−30 Page 423 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REF 26 28 29 30 31 NAME OF PART Cotter pin Nut Washer Bolt Washer QTY 1 1 1 2 2 IPC SEQUENCE NO. IPC 32−21−00−02−165 IPC 32−21−00−02−160 IPC 32−21−00−02−155 IPC 32−21−00−02−170 IPC 32−21−00−02−155 **ON A/C 7274−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7273 Post VSBM−DT−16040−32−12 Subtask 32−21−30−945−003 Refer to Figure 404. F. Parts REF 6 7 8 9 10 12 13 14 15 18 19 20 21 23 24 28 30 31 32 33 NAME OF PART QTY Bolt 1 Washer 2 Spacer washer 2 Nut 1 Cotter pin 1 Tee seal assembly (with two backup rings) 1 Preformed packing 1 Tee seal assembly (with two backup rings) 1 Wear ring 2 Cotter pin 1 Nut 1 Washer 1 Washer 1 Bolt 1 Countersunk washer 1 Cotter pin 1 Nut 1 Washer 1 Bolt 2 Washer 2 IPC SEQUENCE NO. IPC 32−21−00−02−180 IPC 32−21−00−02−185 IPC 32−21−00−02−190 IPC 32−21−00−02−195 IPC 32−21−00−02−200 IPC 32−21−00−04−005 IPC 32−21−00−04−004 IPC 32−21−00−04−040 IPC 32−21−00−04−037 IPC 32−21−00−02−085 IPC 32−21−00−02−080 IPC 32−21−00−02−077 IPC 32−21−00−02−072 IPC 32−21−00−02−062 IPC 32−21−00−02−065 IPC 32−21−00−02−165 IPC 32−21−00−02−160 IPC 32−21−00−02−155 IPC 32−21−00−02−170 IPC 32−21−00−02−155 **ON A/C ALL Subtask 32−21−30−945−004 Refer to Figure 405. Master EFFECTIVITY: See Pageblock 32−21−30 page 401 424 32−21−30 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL G. Parts REF 40 41 44 45 59 60 61 62 64 65 66 67 NAME OF PART QTY Bolt 2 Washer 2 Excluder 1 Pin 2 Pin 2 Rebound ring 1 Tee seal 1 Headed pin 3 Tee seal assembly (with two backup rings) 1 Spare tee seal 1 Preformed packing 1 Retainer 2 IPC SEQUENCE NO. IPC 32−21−00−04−055 IPC 32−21−00−04−060 IPC 32−21−00−04−008 IPC 32−21−00−04−TBD IPC 32−21−00−04−TBD IPC 32−21−00−04−TBD IPC 32−21−00−04−TBD IPC 32−21−00−04−021 IPC 32−21−00−04−025 IPC 32−21−00−04−030 IPC 32−21−00−04−010 IPC 32−21−00−04−015 Subtask 32−21−30−946−002 H. Reference Information **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED REFERENCE TASK 07−11−01−582−804 TASK 12−12−32−220−802 TASK 12−20−32−640−801 TASK 32−21−10−710−801 TASK 32−21−15−400−801 TASK 32−30−00−720−801 TASK 32−33−05−820−801 TASK 32−42−01−400−801 TASK 51−23−00−390−804 TASK 51−23−00−390−808 TASK 51−23−00−390−815 TASK 51−26−00−110−801 DESIGNATION Removal of the Aircraft from Jacks Extension Check and Adjustment (with Nitrogen) of the NLG Shock Strut Lubrication of the Nose Landing Gear Operational Test of the Torque Link Assembly Installation of the NLG Axle Assembly Functional Test of the Landing Gear Extension/Retraction System Alignment of the NLG Uplock Pin with the NLG Uplock Assembly Installation of the Nosewheel/Tire Assembly Bead Seal Sealant Procedure Applicant of Sealant with a Brush Curing of Sealant Solvent Cleaning **ON A/C WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON INSTALLED REFERENCE TASK 07−11−01−582−804 TASK 12−12−32−220−802 DESIGNATION Removal of the Aircraft from Jacks Extension Check and Adjustment (with Nitrogen) of the NLG Shock Strut Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 425 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REFERENCE TASK 12−20−32−640−801 TASK 32−30−00−720−801 TASK 32−33−05−820−801 TASK 32−42−01−400−801 TASK 51−23−00−390−804 TASK 51−23−00−390−808 TASK 51−23−00−390−815 TASK 51−26−00−110−801 DESIGNATION Lubrication of the Nose Landing Gear Functional Test of the Landing Gear Extension/Retraction System Alignment of the NLG Uplock Pin with the NLG Uplock Assembly Installation of the Nosewheel/Tire Assembly Bead Seal Sealant Procedure Applicant of Sealant with a Brush Curing of Sealant Solvent Cleaning **ON A/C ALL 2. Job Set−Up Subtask 32−21−30−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Subtask 32−21−30−110−001 B. C. Clean the NLG main fitting, the shock strut piston, and all of the internal components (that will be installed again) of any unwanted contaminants (Ref. TASK 51−26−00−110−801). Apply a light coating of clean 02−002 hydraulic fluid with a brush to the internal surfaces of the shock strut piston and the NLG main fitting. Subtask 32−21−30−430−001 **ON A/C 7003−7067, 7069−7273 Pre VSBM−DT−16040−32−12 Refer to Figure 403. **ON A/C 7274−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7273 Post VSBM−DT−16040−32−12 Refer to Figure 404. **ON A/C ALL D. Install the floating piston in the bore of the shock strut piston as follows: NOTE: When you do the procedure that follows, lubricate all preformed packings, retainers, tee seals, wear rings, excluders and internal surfaces with 06−002 technical petrolatum or clean 02−002 hydraulic fluid before you install them. (1) Install the tee seal (14) and related inner and outer back−up rings in the middle groove of the floating piston. NOTE: The tee seal (14) is an assembly of the tee seal (14) and two sets of inner back−up rings (white color) and outer back−up rings (black color). When you install the tee seal (14), make sure that the radius of each of the two inner back−up rings fits against the radius of the tee seal (14). Master EFFECTIVITY: See Pageblock 32−21−30 page 401 426 32−21−30 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (2) Install the two wear rings (15) in the top and bottom grooves of the floating piston. (3) Install the threaded rod−end of the CAT5643−4B floating piston installation tool (or equivalent) fully into the bottom of the floating piston. NOTE: The CAT5643−5B floating piston removal tool or a bolt or shaft that is approximately 6 inches (15 cm) long and has a 1/4−28 NF thread can be used if the CAT5643−4B floating piston installation tool is not available. (4) Install the floating piston in the bore of the shock strut piston with the floating piston installation tool. Subtask 32−21−30−430−002 Refer to Figure 405. E. If they were removed in the removal procedure, install the components that follow on the shock strut piston: NOTE: When you do the procedure that follows, lubricate all preformed packings, retainers, tee seals, wear rings, excluders and internal surfaces with 06−002 technical petrolatum or clean 02−002 hydraulic fluid before you install them. (1) If it was removed in the removal procedure, install the excluder (44) in the groove in the retaining collar (42). (2) Install the retaining collar (42) on the shock strut piston. (3) Install the components that follow on the lower bearing (57): (a) If they were removed in the removal procedure, install the back−up rings (71) in the lower external groove in the lower bearing (57). (b) Install the preformed packing (70) in the lower external groove in the lower bearing (57) between the two back−up rings (71). When you install the preformed packing (70), do not damage the two back−up rings (71). (c) Install the tee seal (66), and (if they were removed) the related back−up rings (67) and (68) in the top of the lower bearing (57). NOTE: The tee seal (66) is an assembly of the tee seal (66) and two sets of inner back−up rings (67) (white color) and outer back−up rings (68) (black color). When you install the tee seal (66), make sure that the radius of each of the two inner back−up rings (67) fit against the radius of the tee seal (66). (d) If it is not installed, install a new spare tee seal (69) in the upper external groove on the lower bearing (57). NOTE: Install only the tee seal in the groove. Do not install the two sets of the inner and outer back−up rings that are supplied with the new spare tee seal (69). (e) Install the spacer ring (65) in the top of the lower bearing (57). (f) Install the three headed pins (64) that secure the spacer ring (65) in the lower bearing (57). NOTE: Apply a heavy layer of 06−002 technical petrolatum to the three headed pins (64) to keep them in position as the shock strut piston is installed in the NLG main fitting. Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 427 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (4) Install the lower bearing (57), the lower cam (46), and the upper cam (48) as follows: (a) Install the lower bearing (57) on the shock strut piston. (b) Install the lower cam (46) on the shock strut piston. Make sure that the alignment protrusions on the lower bearing (57) are aligned with the related detente in the lower cam (46) and move the lower cam (46) against the lower bearing (57). (c) If they were removed, install the inner and outer back−up rings (62) and (63) in the internal groove in the upper cam (48). (d) Install the tee seal (61) in the internal groove in the upper cam (48). NOTE: The tee seal (61) is an assembly of the tee seal (61) and two sets of inner back−up rings (62) (white color) and outer back−up rings (63) (black color). When you install the tee seal (61), make sure that the radius of each of the two inner back−up rings (62) fit against the radius of the tee seal (61). (e) If it was removed, install the rebound ring (60) in the external groove in the upper cam (48). (f) Apply a layer of 06−002 technical petrolatum to the groove around the shock strut piston and to the two vertical grooves near the top of the shock strut piston (g) Install the upper cam (48) on the top of the shock strut piston until the groove around the shock strut piston can be seen through the holes in the upper cam (48). Install the eight retaining ring segments (58) in the groove near the top of the shock strut piston. (h) Move the upper cam (48) up until the two vertical grooves in the shock strut piston can be seen through the holes in the upper cam (48). (i) Install the two pins (59) in the vertical grooves near the top of the shock strut piston. Make sure that the pins (59) are aligned with the vertical grooves in the upper cam (48). (j) Move the upper cam (48) down on the shock strut piston until it touches the retaining ring segments (58). Subtask 32−21−30−430−003 Refer to Figure 405. F. If it was removed in the removal procedure, do the steps that follow to install the taxi valve body (52) in the top of the shock strut piston: NOTE: The steps that follow must be done on a bench with a vise that is large enough to securely hold the DST100−32 holding blocks. Other special tools are required. (1) Put the shock strut piston between the two DST100−32 holding blocks and securely clamp the two holding blocks in the bench vise. (2) Insert the taxi valve body (52) in the top of the shock strut piston. Make sure that the top of the taxi valve body (52) is below the groove in the top of the piston inner bore. Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 428 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL G. (3) Install the retaining ring (56) in the groove in the top of the piston inner bore. (4) Move the taxi valve body (52) up until it touches the retaining ring (56). (5) Install the cup washer (54) on the taxi valve body (52) and then install the locknut (55) on taxi valve body (52). (6) Use the CAT5643−12C and CAT5643−13C torque wrench adapters to torque the locknut (55) from 2000 to 2100 pound−inches (226 to 237 N·m). NOTE: Make sure that the shock strut piston does not rotate in the two DST100−32 holding blocks. (7) Use a spherical ended punch and deform the edges of the cup washer (54) into the slots in the locknut (55). Do the steps that follow to install the spring (51), the taxi valve (50), and the taxi valve seat (49) in the taxi valve body (52): NOTE: The taxi valve (50) and the taxi valve seat (49) are matched parts and must be kept together. (1) Install the spring (51) and the taxi valve (50) in taxi valve body (52). (2) Install the cup washer (53) on the taxi valve seat (49) and then install the taxi valve seat (49) in taxi valve body (52). (3) Use the CAT5643−7B and CAT5643−12C torque wrench adapters to torque the taxi valve seat (49) from 800 to 850 pound−inches (90.4 to 96.0 N·m). (4) Use a spherical ended punch and deform the edges of the cup washer (53) into the slots in the taxi valve seat (49). 3. Procedure Refer to Figure 405. Subtask 32−21−30−420−001 A. Do the steps that follow to install the shock strut piston in the NLG main fitting: (1) Apply a thin layer of 06−002 technical petrolatum to the wide groove around the upper cam (48) to hold the upper bearing (47) in position when the upper cam (48) is inserted in the NLG main fitting. NOTE: Do not use too much technical petrolatum. This can make the installation of the upper cam (48) in the NLG main fitting more difficult. (2) Put the two halves of the upper bearing (47) in position in the groove. If the two halves of the upper bearing (47) have alignment protrusions, make sure that they are aligned with the related detente in the upper cam (48). (3) Lubricate the CAT5643−6B split guide with 06−002 technical petrolatum and install it in the inner bore of the shock strut piston. (4) Carefully install the shock strut piston into the split guide. Only insert the shock strut piston into the NLG main fitting until the upper cam (48) is not seen. (5) Apply a layer of 06−002 technical petrolatum to the vertical grooves in the lower cam (46) and install the two pins (45). Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 429 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL CAUTION: (6) (7) (8) (9) (10) (11) (12) (13) (14) (15) MAKE SURE THAT THE PINS ARE CORRECTLY ALIGNED WITH THEIR RELATED VERTICAL GROOVES WHEN THE SHOCK STRUT PISTON IS INSTALLED. IF YOU DO NOT DO THIS, DAMAGE TO THE INNER BORE OF THE NLG MAIN FITTING WILL OCCUR. Align the two pins (45) with the related grooves in the NLG main fitting and then continue to install the shock strut piston and lower cam (46). Make sure that the two pins (45) are engaged correctly with the related grooves in the NLG main fitting. NOTE: If necessary, use the CAT5643−14D alignment tool to install the lower cam (46). Make sure that the three headed pins (64) that secure the spacer ring (65) are still correctly installed and then continue to install the lower bearing (57) fully into the NLG main fitting. NOTE: If necessary, use the CAT5643−15D alignment tool to install the lower bearing (57). The alignment tool will make sure that the alignment protrusions on the lower bearing (57) are still engaged with the related detente in the lower cam (46) when the lower bearing (57) is installed in the NLG main fitting. Apply a layer of 09−009 or 09−023 sealant to the faying surfaces between the bottom of the shock strut piston, the two locking segments (43), and the retaining collar (42). Lift the shock strut piston approximately 1 inch (2.5 cm) from its fully extended position. Hold the shock strut piston in position and install the two locking segments (43) in the groove in the bottom of the NLG main fitting. Raise the retaining collar (42) on the shock strut piston until it is correctly engaged with the two locking segments (43). Install the two bolts (40) and the two washers (41) that attach the retaining collar (42) to the two locking segments (43). Torque the two bolts (40) from 20 to 25 pound−inches (2.26 to 2.28 N·m). Let the shock strut piston move to its fully extended position. Safety the two bolts (40) with 05−004 lockwire. **ON A/C 7003−7067, 7069−7501 WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON NOT INSTALLED 4. Close Out Subtask 32−21−30−410−001 A. Install the axle assembly (Ref. TASK 32−21−15−400−801). Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 430 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON INSTALLED 5. Close Out Subtask 32−21−30−150−001 Refer to Figure 403. A. Remove any unwanted sealant (Ref. TASK 51−23−00−100−801) that remains on the components that follow: ± The bolt (6) ± The washers (7) and (8) ± The nut (9). At the same time, also remove any unwanted sealant that remains from the area where the washers (7) touch the axle of the shock strut piston and also on the bottom of the shock strut at the joint between the axle of the shock strut piston and the diaphragm assembly. B. Use a clean low−lint cloth that is moist with 11−007 Methyl Ethel Ketone (MEK) to remove any remaining sealant and unwanted contamination. **ON A/C 7003−7067, 7069−7273 Pre VSBM−DT−16040−32−12 Subtask 32−21−30−430−004 Refer to Figure 403. C. If the shock strut piston that was installed is not the same one that was removed in the removal procedure, do the steps that follow to install the uplock bracket (32), the jacking pad (24), and the lower torque link (16) (if they were removed in the removal procedure): (1) Put the uplock spacer (33) between the uplock bracket (32) and the axle of the shock strut piston. Make sure that the serrated surface of the uplock spacer (33) faces forward. (2) Install the uplock bracket (32) with the bolts (30) and the washers (31). Make sure that the serrated surfaces of the uplock spacer (33) and the uplock bracket (32) are correctly engaged. NOTE: For the initial alignment with the uplock assembly, install the uplock bracket (32) so that it is centered on the uplock spacer (33). Make sure that there are an equal number of serrations visible at the top and the bottom of the uplock bracket (32). (3) Temporarily tighten the bolts (30). NOTE: Do not torque or safety the bolts (30) with lockwire at this time. This will be done in the NLG uplock pin alignment procedure. (4) Temporarily install the uplock pin (27), the washer (29), and the nut (28). Temporarily tighten the nut (28) by hand. NOTE: Do not safety the nut (28) with the cotter pin (26) at this time. This will be done in the NLG uplock pin alignment procedure. (5) Put the lower torque link (16) and the jacking pad (24) in position between the attachment lugs on bottom of the shock strut piston. NOTE: Make sure that the anti−rotation pads of the jacking pad (24) are located to the left side of the NLG. Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 431 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (6) Install the torque pin (25) to connect the lower torque link (16) and the jacking pad (24) to the attachment lugs on bottom of the shock strut piston. (7) Install the washer (21) and the countersunk washer (23) on the bolt (22). (8) Align the cross−holes of the torque pin (25) and the jacking pad (24). Install the bolt (22) (facing forward) that attaches the jacking pad (24) to the torque pin (25). (9) Install the washers (20) and/or (21) and the nut (19) on the bolt (22). NOTE: Use a maximum of two washers (20) or (21) on the side of the nut (19) if necessary to align the hole in the bolt (22) with the slot in the nut (19). Put a minimum of one washer (20) or (21) on the side of the nut (19). (10) Torque the nut (19) from 25 to 30 pound−inches (2.86 to 3.3 N·m). (11) Safety the nut (19) with the cotter pin (18). (12) Pull the quick−disconnect pins on the upper torque link (17) and then connect the lower torque link (16) to the upper torque link (17). D. Do the steps that follow to install the diaphragm assembly in the shock strut piston: (1) Lightly lubricate the tee seal (12) and the preformed packing (13) with 02−002 hydraulic fluid or 06−002 technical petrolatum. (2) Install the tee seal (12) and related backing rings in the groove near the top of the diaphragm assembly. Make sure that the radius of the backing rings fit the radius of the tee seal (24). NOTE: The tee seal (12) is an assembly of a tee seal and two backing rings. (3) Apply a layer of 04−005 grease to the faying surface of the diaphragm assembly between the tee seal (12) and the bottom of the diaphragm assembly. (4) Install the preformed packing (13) in the groove near the bottom of the diaphragm assembly. (5) Carefully put the diaphragm assembly into the shock strut piston and align the holes in the diaphragm assembly with their related holes in the axle of the shock strut piston. NOTE: Make sure that the tee seal (12) does not get damaged as it moves past the hole for the bolt (6). (6) Install the washers (8) and (7) (as required), on the bolt (6). (7) Install the bolt (6) with the washers (7) and (8), through the diaphragm and the shock strut piston. (8) Install the washers (8) and (7) (as required), and the nut (9) on the bolt (6). NOTE: To align the slots of the nut (9) with the cotter pin hole in the bolt (6), use: ± a maximum of two washers (7) ± a minimum of one washer (8). (9) Torque the nut (9) from 140 to 160 pound−inches (15.8 to 18.0 N·m). (10) Safety the nut (9) with the cotter pin (10). Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 432 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7274−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7273 Post VSBM−DT−16040−32−12 Subtask 32−21−30−430−005 Refer to Figure 404. E. If the shock strut piston that was installed is not the same one that was removed in the removal procedure, do the steps that follow to install the uplock bracket (34), the jacking pad (25), and the lower torque link (16): (1) Put the uplock spacer (35) between the uplock bracket (34) and the axle of the shock strut piston. Make sure that the serrated surface of the uplock spacer (35) faces forward. (2) Install the uplock bracket (34) with the bolts (32) and the washers (33). Make sure that the serrated surfaces of the uplock spacer (35) and the uplock bracket (34) are correctly engaged. NOTE: For the initial alignment with the uplock assembly, install the uplock bracket (34) so that it is centered on the uplock spacer (35). Make sure that there are an equal number of serrations visible at the top and the bottom of the uplock bracket (34). (3) Temporarily tighten the bolts (32). NOTE: Do not torque or safety the bolts (32) with lockwire at this time. This will be done in the NLG uplock pin alignment procedure. (4) Temporarily install the uplock pin (29), the washer (31), and the nut (30). Temporarily tighten the nut (30) by hand. NOTE: Do not safety the nut (30) with the cotter pin (28) at this time. This will be done in the NLG uplock pin alignment procedure. (5) If it was removed for other maintenance in the removal procedure, install the torsion spring (27) on the jacking pad (25). (6) Put the lower torque link (16) and the jacking pad (25) in position between the attachment lugs on bottom of the shock strut piston. NOTE: Make sure that the anti−rotation pads of the jacking pad (25) are located to the left side of the NLG and that the lower torque link (16) is in a position that causes the least amount of torsion in the torsion spring (27) that is installed on the jacking pad (25). (7) Install the torque pin (26) to connect the lower torque link (16) and the jacking pad (25) to the attachment lugs on bottom of the shock strut piston. (8) Install the countersunk washer (24) on the bolt (23). (9) Align the cross−holes of the torque pin (26) and the jacking pad (25). Install the bolt (23) (facing forward) that attaches the jacking pad (25) to the torque pin (26). (10) Install the bracket (22) on the bolt (23). Make sure that: ± The horizontal flange of the bracket (22) points aft ± The vertical flange points forward ± The horizontal flange of the bracket (22) is on top of the horizontal arm of the torsion spring (27). Master EFFECTIVITY: See Pageblock 32−21−30 page 401 433 32−21−30 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (11) Install the washers (20) and/or (21) and the nut (19) on the bolt (23). NOTE: Use a maximum of two washers (20) or (21) on the side of the nut (19) if necessary to align the hole in the bolt (23) with the slot in the nut (19) when you torque the nut (19). Put a minimum of one washer (20) or (21) on the side of the nut. (12) Torque the nut (19) from 25 to 30 pound−inches (2.86 to 3.3 N·m). (13) Safety the nut (19) with the cotter pin (18). (14) Pull the quick−disconnect pins on the upper torque link (17) and then connect the lower torque link (16) to the upper torque link (17). F. Do the steps that follow to install the diaphragm assembly in the shock strut piston: (1) Lightly lubricate the tee seal (12) and the preformed packing (13) with 02−002 hydraulic fluid or 06−002 petrolatum. (2) Install the tee seal (12) and related backing rings in the groove near the top of the diaphragm assembly. Make sure that the radius of the backing rings fit the radius of the tee seal (12). NOTE: The tee seal (12) is an assembly of a tee seal and two backing rings. (3) Apply a layer of 04−005 grease to the faying surface of the diaphragm assembly between the tee seal (12) and the bottom of the diaphragm assembly. (4) Install the preformed packing (13) in the groove near the bottom of the diaphragm assembly. (5) Carefully put the diaphragm assembly into the shock strut piston and align the holes in the diaphragm assembly with their related holes in the axle of the shock strut piston. NOTE: Make sure that the tee seal (12) does not get damaged as it moves past the hole for the bolt (6). (6) Install the washers (8) and (7) (as required), on the bolt (6). (7) Install the bolt (6) with the washers (7) and (8), through the diaphragm and the shock strut piston. (8) Install the washers (8) and (7) (as required), and the nut (9) on the bolt (6). NOTE: To align the slots of the nut (9) with the cotter pin hole in the bolt (6), use: ± a maximum of two washers (7) ± a minimum of one washer (8). (9) Torque the nut (9) from 140 to 160 pound−inches (15.8 to 18.0 N·m). (10) Safety the nut (9) with the cotter pin (10). **ON A/C WITH THE INTEGRAL AXLE/SHOCK STRUT PISTON INSTALLED Subtask 32−21−30−390−001 Refer to Figure 402. G. Apply a brush coat of 09−023 sealant on the head of the bolt (6), the washers (7) and (8), and the nut (9). Include the area where the washers touch the axle of the shock strut piston (Ref. TASK 51−23−00−390−808). Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 434 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL H. Apply a bead of 09−009 sealant at the bottom of the shock strut at the joint between the shock strut piston and the diaphragm assembly (Ref. TASK 51−23−00−390−804) NOTE: 09−009 sealant is preferred. If a faster cure time is required, refer to TASK 51−23−00−390−815 for alternate sealants. **ON A/C ALL 6. Close Out Subtask 32−21−30−910−001 A. If it is not available, assemble the NLG air purge tool (refer to the table at the start of this procedure and to Figure 406). Subtask 32−21−30−610−001 Refer to Figure 401 and Figure 406. B. Service the NLG shock strut with oil and nitrogen, while the aircraft is on the main jacks, as follows: NOTE: The chrome extension/compression limits (dimension ‘X’) for the NLG shock strut are: ± extended fully: 14.50 inches (368.3 mm) ± compressed fully: 0.00 inches (0.00 mm). NOTE: Servicing oil 02−002 or 02−003 can be used in the procedure that follows. They can be mixed in any proportion. (1) Measure and make a record of the ambient air temperature and the ambient hydraulic fluid temperature. The ambient air temperature must be 59 to 95 °F (15 to 35 °C) and the ambient hydraulic fluid temperature must be 59 to 131 °F (15 to 55 °C). (2) Install a MS28778−4 preformed packing (7) on an AN815−4D union (8). (3) Install the AN815−4D union (8) with the MS28778−4 preformed packing (7) in the oil filler port (as an adapter for the output hydraulic line from the NLG air purge tool). (4) Connect the output hydraulic line from the from the NLG air purge tool to the AN815−4D union (8) in the oil filler port. (5) Connect the line from the hydraulic servicing unit to the inlet fitting on the NLG air purge tool. (6) Put the drain line from the NLG air purge tool in a suitable waste hydraulic fluid container. NOTE: The NLG shock strut contains approximately 0.75 gallons (2.8 L) of hydraulic fluid. Make sure that the container is large enough to contain this volume. (7) Make sure that the thin nut (3) on the nitrogen charging valve (2) is fully open. (8) Put the axle jack in position below the NLG jacking point. (9) Do the steps that follow to fill the NLG shock strut with 02−002 or 02−003 hydraulic fluid: Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 435 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (a) Make sure that the NLG air purge tool is in position 2. NOTE: Hydraulic fluid flows from the hydraulic servicing unit to the NLG when the NLG air purge tool is in position 2. (b) Slowly pump 02−002 or 02−003 oil from the hydraulic servicing unit until the shock strut piston is fully extended and the gauge on the servicing unit shows a pressure of 250 PSIG (1724 kPa). (c) Make sure that there is no hydraulic fluid leakage at the bottom of the NLG main fitting adjacent to the shock strut piston or from the nitrogen charging valve (2). (d) Move the NLG air purge tool to position 1. Make sure that the hydraulic pressure is released. NOTE: Hydraulic fluid flows from the NLG (through the drain tube) to the waste fluid container when the NLG air purge tool is in position 1. WARNING: STOP THE JACKING PROCEDURE WHEN THE SHOCK STRUT IS FULLY COMPRESSED OR YOU WILL LIFT THE AIRCRAFT OFF THE MAIN JACKS. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (e) Operate the NLG axle jack until the shock strut is fully compressed. Make sure that you stop the jacking procedure when the strut is fully compressed. As the NLG axle jack is operated, examine the return fluid for air. (10) If air was seen in the hydraulic fluid, do all of the previous step again until the hydraulic fluid is free of air. (11) If no air was seen in the hydraulic fluid before the strut is fully compressed by the NLG axle jack, do the steps that follow: (a) Disconnect the output hydraulic line (from the NLG air purge tool) from the AN815−4D union (8) in the oil filler port on the NLG shock strut. (b) Close the valve on the servicing unit. (c) Remove the AN815−4D union (8) with the MS28778−4 preformed packing (7) from the oil filler port. (d) If necessary, manually fill the shock strut with 02−002 or 02−003 oil until it is full. (12) Install a new preformed packing (6) on the oil filler plug (5). (13) Install the oil filler plug (5) and torque it from 55 to 65 inch−pounds (6.2 to 7.3 N·m). Safety oil filler plug (5) with 05−004 lockwire. CAUTION: REMOVE THE NLG AXLE JACK BEFORE YOU PRESSURIZE THE SHOCK STRUT. (14) Remove the axle jack. (15) Connect the charging and gauging kit to the nitrogen charging valve (2). (16) Connect the hose from the nitrogen bottle/service regulator to the charging and gauging kit. Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 436 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL WARNING: OBEY THE SAFETY PRECAUTIONS THAT FOLLOW WHEN YOU DO WORK WITH HIGH−PRESSURE GAS NITROGEN: ± USE A FACE SHIELD ± USE SAFETY GOGGLES ± CLOSE THE VALVES ON THE PIPING AND THE TANKS WHEN THEY ARE NOT USED OR WHEN EMPTY ± GO TO AN AREA THAT HAS A GOOD FLOW OF CLEAN AIR AND GET MEDICAL AID IF YOU BREATHE IN GAS NITROGEN NITROGEN CAN CAUSE SUFFOCATION AND DEATH WHEN IT IS BREATHED IN. CAUTION: REMOVE THE NLG AXLE JACK BEFORE YOU PRESSURIZE THE SHOCK STRUT. (17) Slowly pressurize the shock strut with 05−002 technical nitrogen until the shock strut is fully extended. Measure and make a record of the shock strut piston travel. The travel must be between 14.435 and 14.565 inches (366.65 and 369.95 mm). (18) Continue to slowly pressurize the shock strut with 05−002 technical nitrogen to 180±10 PSI (1241±69 kPa). NOTE: Read the pressure on the charging and gauging kit with its handle at the closed position for an accurate reading. (19) Close the thin nut (3) on the nitrogen charging valve (2). WARNING: CLOSE ALL VALVES ON SERVICING EQUIPMENT AND ON THE EQUIPMENT THAT IS SERVICED WHEN THE DISCONNECTION OF HOSES AND EQUIPMENT IS MADE. DISCONNECT HOSES SLOWLY TO RELEASE THE RESIDUAL PRESSURE FROM THE EQUIPMENT. FAILURE TO DO THIS CAN CAUSE INJURIES. (20) Close all service equipment valves and carefully disconnect the charging and gauging kit from the nitrogen charging valve (2). Subtask 32−21−30−750−001 MAKE SURE THE AIRCRAFT STAYS ON THE NOSE JACK. USE NECESSARY PRECAUTION (THE TAIL STEADY OR THE NOSE GEAR JACKING PAD TIE DOWN) TO PREVENT THE NOSE GEAR TO FALL OF THE NOSE JACK. IF YOU DO NOT DO THIS IT CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO THE AIRCRAFT. Do the steps that follow to do a cycle test of the NLG: (1) Put the axle jack in position below the NLG jacking point. (2) Operate the NLG axle jack until dimension ‘X’ on the shock strut piston is 4.5 inches (114.3 mm). (3) Release the pressure in the NLG axle jack and allow the shock strut to fully extend. When the shock strut piston extends: ± the operation must be smooth ± no external hydraulic fluid leakage is allowed ± hydraulic fluid leakage at the piston seal must be less than 1 drop. WARNING: C. Master EFFECTIVITY: See Pageblock 32−21−30 page 401 437 32−21−30 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL D. E. Do all of the previous steps in this subtask again 10 times. If the operation of the NLG and the hydraulic fluid leakage is acceptable, do the steps that follow to finish the cycle test: CAUTION: REMOVE THE NLG AXLE JACK BEFORE YOU PRESSURIZE THE SHOCK STRUT. (1) Remove the axle jack. (2) Connect the charging and gauging kit to the nitrogen charging valve (2) again. (3) With the shock strut piston fully extended, open the thin nut (3) on the nitrogen charging valve (2). (4) Slowly pressurize the shock strut with 05−002 technical nitrogen until the pressure is between 767 and 857 PSIG (5285 and 5909 kPa). (5) Close the thin nut (3) on the nitrogen charging valve (2). WARNING: CLOSE ALL VALVES ON SERVICING EQUIPMENT AND ON THE EQUIPMENT THAT IS SERVICED WHEN THE DISCONNECTION OF HOSES AND EQUIPMENT IS MADE. DISCONNECT HOSES SLOWLY TO RELEASE THE RESIDUAL PRESSURE FROM THE EQUIPMENT. FAILURE TO DO THIS CAN CAUSE INJURIES. (6) Close all service equipment valves and carefully disconnect the charging and gauging kit from the nitrogen charging valve (2). (7) Apply leak 05−037 detection solution (or a solution of soap and water) to the nitrogen charging valve (2). No leakage is permitted. (8) Slowly open the thin nut (3) on the nitrogen charging valve (2) and release all of the nitrogen pressure. (9) Connect the charging and gauging kit to the nitrogen charging valve (2) again. (10) Slowly pressurize the shock strut with 05−002 technical nitrogen to 180±10 PSI (1241±69 kPa). (11) Close the thin nut (3) on the nitrogen charging valve (2). WARNING: CLOSE ALL VALVES ON SERVICING EQUIPMENT AND ON THE EQUIPMENT THAT IS SERVICED WHEN THE DISCONNECTION OF HOSES AND EQUIPMENT IS MADE. DISCONNECT HOSES SLOWLY TO RELEASE THE RESIDUAL PRESSURE FROM THE EQUIPMENT. FAILURE TO DO THIS CAN CAUSE INJURIES. (12) Close all service equipment valves and carefully disconnect the charging and gauging kit from the nitrogen charging valve (2). F. Install the dust cap (1) on the nitrogen charging valve (2). Subtask 32−21−30−640−001 G. Apply a small quantity of 02−002 hydraulic fluid with a brush to the exposed chrome surfaces of the shock strut piston. Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 438 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−30−410−002 H. Install the nosewheel/tire assembly (Ref. TASK 32−42−01−400−801). Subtask 32−21−30−586−001 I. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−21−30−640−002 J. Lubricate the torque link assembly (Ref. TASK 12−20−32−640−801). Subtask 32−21−30−220−001 K. When the aircraft is removed from the main jacks and is fully supported by its landing gear, do an extension check and, if necessary, adjustment of the NLG shock strut (Ref. TASK 12−12−32−220−802). Subtask 32−21−30−280−001 Do the 6 hour pressure check. If necessary, the check can be deferred until the subsequent Service Check (72 hours or 3 calendar days). Do the 6 hour pressure check as follows: (1) Pressurize the shock strut to 170−190 psig (1172−1310 kPa). (2) Install the wheels. (3) Lower the aircraft to the ground. Remove the jack. (4) Measure dimension "X". (5) Record the nitrogen pressure. (6) After 6 hours, calculate the difference between the initial pressure and the final pressure. The pressure must be within 40 psig (275 kPa) of the pressure recorded in Para 5 above. (7) Measure dimension "X". This must be within the limits shown on the service plate (3−250A). NOTE: L. Subtask 32−21−30−710−001 M. Do an operational test of the torque link assembly (Ref. TASK 32−21−10−710−801). Subtask 32−21−30−865−002 N. Close the circuit breakers that follow: CB PANEL CBP−1 CBP−2 CB NO. F8 F8 NAME NOSE STEER NOSE STEER Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 ZONE 221 222 Page 439 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−21−30−720−001 O. P. Do an alignment of the NLG uplock pin (Ref. TASK 32−33−05−820−801). Do a test of the extension/retraction system of the landing gear (Ref. TASK 32−30−00−720−801). Subtask 32−21−30−941−002 Q. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 440 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 8 7 HANDPUMP HYDRAULIC FLUID MIL−H−5606 4 6 3 3 1 400 G1 600 200 800 0 1000 VALVE V 1 2 1 0 − 1000 psig (0 − 6895 kPa) 2 TO UNION AN815−4 3 HYDRAULIC SCHEMATIC − TYPICAL (VALVE SHOWN IN POSITION 1 −FLUID RETURN) 4 NOTES 5 Typical four port valve shown. Three port valve assemblies may require additional tee fitting and union for the connection of items 2 and 5 to the inlet port. Apply a layer of 05−038 anti seize tape to all NPT fittings before assembly. 3 LEGEND 1. Selector valve. 2. Pressure gauge. 3. Reducer bushing. 4. Hose adapter. 5. Hose assembly. 6. Hose barb. 7. Hose clamp. 8. Drain tube. ram3221304_005.dg, gv/rm, 2709/02 2 NLG Hydraulic Fluid Fill and Air Purge Tool − Assembly Figure 406 Master EFFECTIVITY: See Pageblock 32−21−30 page 401 32−21−30 Page 441 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL NOSE GEAR DOOR SYSTEM − DESCRIPTION AND OPERATION 1. 2. General A. The nose−gear door system makes a smooth fuselage surface when the nose landing gear (NLG) is retracted. B. The nose−gear door system has the components that follow: ± Two forward doors ± One rear door ± One door actuator ± One door link assembly ± One door selector valve ± Three check valves ± One maintenance access switch. Component Details Refer to Figure 1. A. Forward Doors (1) The forward doors are attached and hinged to the left and right sidewalls of the nosewheel well. The doors are hydraulically operated to open or close the forward area of the nosewheel well. B. Rear Door (1) The rear door is attached to the NLG and hinged to the left and right sidewalls of the nosewheel well. The door is mechanically operated to open or close the aft area of the nosewheel well. C. Door Actuator (1) The door actuator is installed on the right side in the nosewheel well. The door actuator is hydraulically operated by hydraulic system No. 3 (29−00−00). The actuator transmits a mechanical force to the door link assembly. The door actuator has an inlet and an outlet hydraulic port. The inlet port is connected to the hydraulic lines of the door selector valve and of the NLG−door bypass valve (32−34−40). The outlet port is connected to the return line of hydraulic system No. 3 (29−00−00). D. Door Link Assembly (1) The door link assembly is installed on the left and right sidewalls of the nosewheel well. The door link assembly has push/pull rods, levers, bellcrank assemblies, and provisions for proximity switches. The door link assembly mechanically opens and closes the forward doors. The right side door link assembly has provision for a rig pin. E. Door Selector Valve (1) The door selector valve is installed in the nosewheel well. The door selector valve is a four−way, three−position, solenoid−operated valve. It is equipped with one electrical connector and four hydraulic ports identified R, P, C1, and C2. The door selector valve supplies hydraulic pressure to the door actuator. Master EFFECTIVITY: See Pageblock 32−22−00 page 1 32−22−00 Page 1 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL F. 3. 4. Check Valve Refer to Figure 2. (1) There is one check valve installed on the door selector valve, the NLG−door bypass valve (32−34−40), and the NLG bypass valve (32−34−35). The check valves let hydraulic fluid flow in one direction only. G. Maintenance Access Switch Refer to Figure 3. (1) The maintenance access switch is installed on the external service panel. The external service panel is installed on the right side of the aircraft nose, between the ac−ground−power receptacle door and the oxygen refill door. The maintenance access switch is a double−pole, double−throw toggle switch. Its function is to open and close the forward doors when the aircraft is on the ground. Operation A. When the landing gear handle is put in the DOWN position, the proximity sensor electronic unit (PSEU) sends a command signal to the door selector valve (32−31−01) (32−61−01). The door selector valve opens the forward doors before the NLG is released from the uplock assembly (32−33−05). The door selector valve lets pressurized hydraulic fluid flow to the door actuator. The door actuator pushes on the control levers which make the bellcrank assemblies push the control rods. The control rods then open the forward doors. B. When the NLG is released from the uplock assembly, the rear door opens mechanically by the extension movement of the NLG. When the NLG is downlocked, the PSEU gives a command signal to the door selector valve to close the forward doors C. When the landing gear handle is put in the UP position, the PSEU sends a command signal to the door selector valve (32−31−01) (32−61−00). The door selector valve opens the forward doors before the NLG starts to retract. When the NLG is up and locked, the proximity sensor installed on the uplock assembly sends a gear uplocked signal to the PSEU. The PSEU sends a command signal to the door selector valve to close the forward doors. D. When the aircraft is parked, the maintenance technician uses the maintenance access switch to open the forward doors. Component Location Index Refer to Figure 1, Figure 2, and Figure 3. COMPONENT NAME Check valve Door actuator Door link assembly Door selector valve Forward doors Maintenance access switch Rear door QTY 3 1 1 1 2 1 1 Master EFFECTIVITY: See Pageblock 32−22−00 page 1 ACCESS/ZONE 711/712 711/712 711/712 711/712 711/712 122CR 713 REFERENCE 32−22−25 32−22−10 32−22−15 32−22−20 32−22−01 32−22−30 32−22−05 32−22−00 Page 2 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL DOOR ACTUATOR DOOR MECHANISIM DOOR SELECTOR VALVE DOOR CONTROL ROD FORWARD DOORS DOOR CONTROL ROD DOOR SPRING ram3222000_001(1).dc, dm/pm, 10/11/95 REAR DOOR Nose Gear Door System − Component Location/Recognition Figure 1 Master EFFECTIVITY: See Pageblock 32−22−00 page 1 32−22−00 Page 3 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A A A REF. NLG DOOR BYPASS VALVE A REF. NOSE LANDING GEAR DOOR SELECTOR VALVE ram3222000_002.dg, mb, 24/08/92 A REF. NLG BYPASS VALVE A CHECK VALVE Nose Gear Door System/Check Valve − Component Location/Recognition Figure 2 Master EFFECTIVITY: See Pageblock 32−22−00 page 1 32−22−00 Page 4 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL MAINTENANCE ACCESS SWITCH OPEN EXT AC PUSH AVAIL IN USE FLT/ NORM CKPT CALL PUSH HDPH CALL APU BATT PKG BRK LAMP TEST SHUT−OFF ON ON MIC ram3222000_003(2).dg, sb/pb, 11/10/94 NOSE DOOR EXTERNAL SERVICES PANEL Nose Gear Door System/Maintenance Access Switch − Component Location/Recognition Figure 3 Master EFFECTIVITY: See Pageblock 32−22−00 page 1 32−22−00 Page 5 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL FORWARD DOORS, NOSE LANDING GEAR (NLG) − MAINTENANCE PRACTICES 1. General A. The maintenance procedures that follow give the instructions to open and isolate the NLG forward doors and to close them after maintenance is completed. When the NLG forward doors are open it is usually for maintenance purposes. Hydraulic pressure from system No. 3 is used to open and close the NLG forward doors in these procedures. B. The TASK that follows isolates the door actuator of the NLG forward doors from hydraulic system No. 3 while the doors are open. Always obey the procedures that follow when the NLG forward doors are opened for maintenance. TASK 32−22−01−980−801 Open and Isolate the Nose−Landing−Gear Forward Doors 1. Job Set−Up Information Subtask 32−22−01−946−001 A. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−803 TASK 12−00−06−863−804 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 2. Job Set−Up Subtask 32−22−01−941−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. Subtask 32−22−01−010−001 B. Open the access panel that follows: ACCESS 122CR DESIGNATION Door, external service panel Master EFFECTIVITY: See Pageblock 32−22−01 page 201 32−22−01 Page 201 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. Procedure Subtask 32−22−01−860−024 Refer to Figure 201. WARNING: MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF FLIGHT CONTROLS AND HYDRAULIC COMPONENTS WHEN YOU PRESSURIZE THE HYDRAULIC SYSTEMS. IF YOU DO NOT DO THIS, INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT CAN OCCUR. WARNING: IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. A. Open and isolate the NLG forward doors as follows: (1) Pressurize hydraulic system No. 3 (Ref. TASK 12−00−06−863−803). (2) At the external services panel, put the NOSE DOOR maintenance switch to the OPEN position. (3) When the doors open, release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). (4) On the overhead HYDRAULIC panel, install a DO NOT OPERATE HYDRAULICS warning placard. (5) Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 (6) At the external services panel, install a DO NOT OPERATE THE NOSE DOOR SWITCH warning placard. (7) At access panel 196BL (hydraulic system No. 3 − external power unit connection point), install a DO NOT CONNECT HYDRAULIC POWER UNIT warning placard. Master EFFECTIVITY: See Pageblock 32−22−01 page 201 32−22−01 Page 202 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL MAINTENANCE ACCESS SWITCH OPEN FLT/ NORM EXT AC PUSH AVAIL IN USE CKPT CALL PUSH HDPH CALL APU BATT PKG BRK LAMP TEST SHUT−OFF ON ON MIC EXTERNAL SERVICES PANEL ram3222000_003(2).dg, sb/pb, 11/10/94 NOSE DOOR Maintenance Access Switch Used to Open and Close the Nose Doors − Maintenance Practices Figure 201 Master EFFECTIVITY: See Pageblock 32−22−01 page 201 32−22−01 Page 203 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−22−01−980−802 Close the Nose−Landing−Gear Forward Doors 1. Job Set−Up Information Subtask 32−22−01−946−002 A. Reference Information REFERENCE TASK 12−00−06−863−803 TASK 12−00−06−863−804 DESIGNATION Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 2. Job Set−Up Subtask 32−22−01−869−013 A. Make sure that the aircraft is in the same configuration as in the open/isolate TASK. 3. Procedure Subtask 32−22−01−860−025 Refer to Figure 201. A. Close the NLG forward doors as follows: (1) Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 (2) On the overhead HYDRAULIC panel, remove the DO NOT OPERATE HYDRAULICS warning placard. WARNING: MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF FLIGHT CONTROLS AND HYDRAULIC COMPONENTS WHEN YOU PRESSURIZE THE HYDRAULIC SYSTEMS. IF YOU DO NOT DO THIS, INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT CAN OCCUR. (3) Pressurize hydraulic system No. 3 (Ref. TASK 12−00−06−863−803). (4) At the external services panel, remove the DO NOT OPERATE THE NOSE DOOR SWITCH warning placard. (5) Put the NOSE DOOR maintenance switch to the FLT/NORM position. (6) When the doors close, release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). (7) At access panel 196BL, remove the DO NOT CONNECT HYDRAULIC POWER UNIT warning placard. Master EFFECTIVITY: See Pageblock 32−22−01 page 201 32−22−01 Page 204 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 4. Close Out Subtask 32−22−01−410−002 A. Close the access panel that follows: ACCESS 122CR DESIGNATION Door, external service panel Master EFFECTIVITY: See Pageblock 32−22−01 page 201 32−22−01 Page 205 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL FORWARD DOORS, NOSE LANDING GEAR − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the forward doors of the nose landing gear. The forward doors are installed on the left and the right sides of the nosewheel well. TASK 32−22−01−000−801 Removal of the Forward Doors of the Nose Landing Gear 1. Job Set−Up Information Subtask 32−22−01−946−010 A. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−22−01−980−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Open and Isolate the Nose−Landing−Gear Forward Doors 2. Job Set−Up Subtask 32−22−01−490−002 WARNING: A. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Master EFFECTIVITY: See Pageblock 32−22−01 page 401 32−22−01 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−01−010−010 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the nose landing gear forward doors (Ref. TASK 32−22−01−980−801). WARNING: B. 3. Procedure Subtask 32−22−01−020−010 Refer to Figure 401. A. Remove the right forward door (1) of the nose landing gear as follows: NOTE: The procedure that follows is for the right forward door (1). The procedure for the left forward door (2) is the same. (1) Remove the nut (3), the lockwasher (4), and the bonding jumper (6) with the washers (5), from the screw (7). (2) Remove and discard the cotter pin (8). (3) Remove the nut (9), the washer (10), and the bolt (11). (4) Disconnect the door operating rod (12) from the fitting (13). (5) From the aft hinge (19) and the aft door fitting (20) remove the components that follow: (a) Remove and discard the cotter pin (14). (b) Remove the nut (15), the washer (16), and the bolt (18). (6) From the forward hinge (21) and the forward door fitting (22) remove the components that follow: (a) Remove and discard the cotter pin (14). (b) Remove the nut (15), the washer (16), and the bolt (18). (7) Remove the door (1) and the laminated shims (17). Master EFFECTIVITY: See Pageblock 32−22−01 page 401 32−22−01 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND. 1. Right forward door of the nose landing gear. 2. Left forward door of the nose landing gear. 3. Nut. 4. Lockwasher. 5. Washer. 6. Bonding jumper. 7. Screw. 8. Cotter pin. 9. Nut. 10. Washer. 11. Bolt. 12. Door operating rod. 13. Fitting. 14. Cotter pin. 15. Nut. 16. Washer. 17. Laminated shim. 18. Bolt. 19. Aft hinge. 20. Aft door fitting. 21. Forward hinge. 22. Forward door fitting. 12 1 20 21 22 A 1 2 NOSE LANDING GEAR (REF) 1 19 17 NOTE 1 16 15 14 Components of the aft hinge (19) and the aft door fitting (20) are shown. Components of the forward hinge (21) and the forward door fitting (22) are the same. 1 3 18 4 6 11 7 13 10 9 8 5 A ram3222014_001(2).dc, cr/rm, 21/04/97 5 Forward Doors of the Nose Landing Gear − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−22−01 page 401 32−22−01 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−22−01−400−801 Installation of the Forward Doors of the Nose Landing Gear 1. Job Set−Up Information Subtask 32−22−01−943−010 A. Tools and Equipment REFERENCE None specified DESIGNATION Torque wrench, torque range 25−30 pound−inches (2.83−3.39 N·m). Subtask 32−22−01−945−010 B. Parts REF 3 4 5 8 9 10 11 14 15 16 17 18 NAME OF PART Nut Lockwasher Washer Cotter pin Nut Washer Bolt Cotter pin Nut Washer Laminated shim Bolt QTY 2 2 4 2 2 AR 2 4 4 AR 8 4 IPC SEQUENCE NO. IPC 32−22−01−01−135 IPC 32−22−01−01−125 IPC 32−22−01−01−120 IPC 32−22−01−01−470 IPC 32−22−01−01−465 IPC 32−22−01−01−460 IPC 32−22−01−01−455 IPC 32−22−01−01−035 IPC 32−22−01−01−030 IPC 32−22−01−01−025 IPC 32−22−01−01−155 IPC 32−22−01−01−015 Subtask 32−22−01−946−011 C. Reference Information REFERENCE TASK 32−22−01−720−801 TASK 32−22−01−830−802 DESIGNATION Functional Test of the Forward Doors of the Nose Landing Gear Rigging of the Forward Doors of the Nose Landing Gear 2. Procedure Subtask 32−22−01−869−010 A. Make sure that the aircraft is in the same configuration as in the removal task. Subtask 32−22−01−420−010 Refer to Figure 401. Master EFFECTIVITY: See Pageblock 32−22−01 page 401 32−22−01 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL B. Install the right forward door (1) of the nose landing gear as follows: NOTE: The procedure that follows is for the right forward door (1). The procedure for the left forward door (2) is the same. (1) Align the forward and aft hinges (19) and (21) with their related fittings (20) and (22). (2) At the forward hinge (19) and the door fitting (20) install the components that follow: (a) Install a laminated shim (17) on each side of the door fitting (20) between the door fitting and the fork of the forward hinge (19) (two shims per hinge and fitting assembly). (b) At the forward hinge (19) and related door fitting (20), install the bolt (18), the washer (16), and the nut (15). NOTE: Use a minimum of one washer (16) and a maximum of three washers (16) to align the cotter pin holes of the bolt (18) and the nut (15). (3) At the aft hinge (20) and the door fitting (22) install the components that follow: (a) Install a laminated shim (17) on each side of the door fitting (22) between the door fitting and the fork of the aft hinge (20) (two shims per hinge and fitting assembly). (b) At the aft hinge (19) and related door fitting (20), install the bolt (18), the washer (16), and the nut (15). NOTE: Use a minimum of one washer (16) and a maximum of three washers (16) to align the cotter pin holes of the bolt (18) and the nut (15). (4) Torque the nuts (15) to 25−30 pound−inches (2.82−3.39 N·m). (5) Safety each nut (15) with a cotter pin (14). (6) Install the bonding jumper (6), the washers (5), (install one washer (5) on each side of the bonding jumper), the lockwasher (4), and the nut (3) on the screw (7). (7) With the door operating rod (12) moved away from the door, manually operate the door to the closed and open position to make sure that it operates smoothly. (8) Align the end of the door operating rod (12) with the fitting (13). (9) Temporarily install the bolt (11) to connect the end of the door operating rod (12) to the fitting (13). Subtask 32−22−01−820−001 C. Do a check of the NLG forward door rigging (Ref. TASK 32−22−01−830−802). If necessary, adjust the NLG forward doors. Subtask 32−22−01−410−013 D. If the NLG forward door rigging, the forward door−to−skin clearances and the forward door−to−skin mismatches are satisfactory do the steps that follow: (1) Install the bolt (11), the washer (10), and the nut (9). NOTE: Use a minimum of one washer (10) and a maximum of three washers (10) to align the cotter pin holes of the bolt (11) and the nut (9). Master EFFECTIVITY: See Pageblock 32−22−01 page 401 32−22−01 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (2) Torque the nut (9) to 25−30 pound−inches (2.82−3.39 N·m). (3) Safety the nut (9) with the cotter pin (8). 3. Close Out Subtask 32−22−01−941−010 A. Remove all tools, equipment, and unwanted materials from the work area. Subtask 32−22−01−220−010 B. Do a functional test of the NLG forward doors (Ref. TASK 32−22−01−720−801). Master EFFECTIVITY: See Pageblock 32−22−01 page 401 32−22−01 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL FORWARD DOORS, NOSE LANDING GEAR − ADJUSTMENT/TEST 1. General A. The maintenance procedures that follow are for the functional test and rigging of the nose−landing−gear (NLG) forward doors. TASK 32−22−01−720−801 Functional Test of the Nose−Landing−Gear Forward Doors 1. Job Set−Up Information Subtask 32−22−01−946−022 A. Reference Information REFERENCE TASK 12−00−07−861−801 TASK 12−00−07−861−802 TASK 32−22−01−980−801 TASK 32−22−01−980−802 DESIGNATION Connect External AC Power Remove External AC Power Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors 2. Job Set−Up Subtask 32−22−01−861−028 A. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801). 3. Procedure Subtask 32−22−01−720−001 A. Do a functional test of the forward doors as follows: (1) Open and isolate the NLG forward doors (Ref. TASK 32−22−01−980−801). (2) Close the NLG forward doors (Ref. TASK 32−22−01−980−802). 4. Close Out Subtask 32−22−01−861−029 A. Disconnect the external AC power from the aircraft (Ref. TASK 12−00−07−861−802). Master EFFECTIVITY: See Pageblock 32−22−01 page 501 32−22−01 Page 501 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−22−01−830−802 Rigging of the Forward Doors of the Nose Landing Gear 1. Job Set−Up Information Subtask 32−22−01−943−012 A. Tools and Equipment REFERENCE None specified DESIGNATION Torque wrench, range 0−50 pound−inches (0−5.7 N·m) Subtask 32−22−01−944−001 B. Consumable Materials REFERENCE 05−031 DESIGNATION Lockwire Subtask 32−22−01−945−012 C. Parts REF 3 4 5 6 NAME OF PART Cotter pin Nut Washer Bolt QTY 2 2 2 2 IPC SEQUENCE NO. IPC 32−22−00−01−475 IPC 32−22−00−01−470 IPC 32−22−00−01−465 IPC 32−22−00−01−460 Subtask 32−22−01−946−021 D. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 10−11−00−000−801 TASK 10−11−00−000−802 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−803 TASK 12−00−06−863−804 TASK 12−00−07−861−801 TASK 12−00−07−861−802 TASK 27−54−00−866−802 TASK 32−22−01−220−801 TASK 32−22−05−220−801 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Removal of the Nose Landing Gear Lockpin Removal of the Main Landing Gear Lockpins Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 Connect External AC Power Remove External AC Power Electrical Retraction of the Flaps Clearance Check of the NLG Forward Doors Clearance Check of the Rear Door of the Nose Landing Gear Master EFFECTIVITY: See Pageblock 32−22−01 page 501 32−22−01 Page 502 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REFERENCE TASK 32−22−01−980−801 TASK 32−22−01−980−802 DESIGNATION Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors 2. Job Set−Up Subtask 32−22−01−861−002 A. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801). Subtask 32−22−01−582−022 B. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). Make sure that there is at least 4 inches (10 cm) of clearance between the tires and the ground. Subtask 32−22−01−860−022 C. Make sure that the LDG GEAR control handle is in the DN position and that the green−color DN indications are shown in the three GEAR boxes on the engine indication and crew alerting system (EICAS) primary page. Subtask 32−22−01−866−002 D. Make sure that the flaps are fully retracted to zero degrees (Ref. TASK 27−54−00−866−802). Subtask 32−22−01−220−001 E. To find the initial amount that a nose landing gear (NLG) door must be adjusted, do an inspection of the door clearances between the two forward NLG doors and also between each forward NLG door and its adjacent aircraft structure (Ref. TASK 32−22−01−220−801. Subtask 32−22−01−010−023 F. When you know the initial amount that a NLG door (or doors) must be adjusted, open and isolate the forward doors of the NLG (Ref. TASK 32−22−01−980−801). 3. Procedure Subtask 32−22−01−830−002 Refer to Figure 501. A. Do the basic rigging of the forward doors of the NLG as follows: (1) Disconnect the applicable control rod (1) from the applicable door (2) as follows: (a) Remove and discard the cotter pin (3) from the nut (4). (b) Remove the nut (4), the washer (5), and the bolt (6). Disconnect the control rod (1) from the door (2). Master EFFECTIVITY: See Pageblock 32−22−01 page 501 32−22−01 Page 503 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (2) Adjust the length of the left and right control rods as follows: NOTE: This procedure is for the adjustment of the right control rod. The adjustment of the left control is the same. (a) Remove and discard the lockwire from the lock nuts (7) and the control rods (1). Loosen the lock nuts (7). (b) Turn the rod ends (8) as necessary to adjust the length of the control rod (1). (c) Tighten the lock nuts (7). Do not safety the lock nuts at this time. (d) Align the end of the control rod (1) with the door fitting (9). (e) Install the bolt (6), the washer (5), and the nut (4). Install the bolt (6) with a minimum of one washer (5) and a maximum of three washers. Do not torque the nut (4) at this time. (3) Close the forward doors of the NLG (Ref. TASK 32−22−01−980−802) and do a check of the NLG forward door clearances again. If necessary, do these steps again until the clearances are satisfactory. Subtask 32−22−01−090−001 B. If the basic rigging of the NLG forward doors was satisfactory, remove the safety lockpins from the nose landing gear and from the main landing gear (Ref. TASK 10−11−00−000−801 and TASK 10−11−00−000−802). Subtask 32−22−01−863−002 C. Pressurize hydraulic systems No. 3A and No. 3B (Ref. TASK 12−00−06−863−803). **ON A/C 7033, 7041, 7052, 7138, 7149, 7180, 7189, 7193 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Pre SB601R−31−022 Subtask 32−22−01−867−001 NOTE: D. E. Unless it is specified in this procedure, ignore the three white−color UP indications in the GEAR boxes on the EICAS primary page. In this procedure, the three white−color UP indications will not go off after 30 seconds and is normal. When the aircraft is in the correct flight configuration, the three white−color UP indications go out of view after a maximum of 30 seconds after first being seen. This will only happen if: ± There is no message related to brakes, gear, flaps, antiskid, steering, WOW, or the proximity sensor system shown on the EICAS primary and status pages ± The flaps are at zero degrees ± There is no flap overspeed condition. To keep the landing gear horn from being heard during this procedure, move the throttle levers forward out of the IDLE position. Do the steps that follow to retract the NLG and the main landing gear (MLG): Master EFFECTIVITY: See Pageblock 32−22−01 page 501 504 32−22−01 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL WARNING: BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. CAUTION: IF THE FORWARD DOORS OF THE NOSE LANDING GEAR DO NOT OPEN BEFORE THE NOSE LANDING GEAR RETRACTS, PUT THE LANDING−GEAR SELECTOR HANDLE IN THE "DN" POSITION. THE RETRACTION OF THE NOSE LANDING GEAR WILL CAUSE DAMAGE TO THE CLOSED DOORS. (1) Put the LDG GEAR control handle in the UP position. Make sure that the steps that follow occur: ± The forward doors of the NLG open ± The three amber−color gear hash marks are shown on the EICAS primary page ± In approximately 9 to 15 seconds, the NLG and the MLG are retracted and locked and the three white−color UP indications come into view in the three GEAR boxes on the EICAS primary page. **ON A/C 7032, 7059, 7061, 7063, 7094, 7103, 7110, 7115, 7125, 7133, 7142, 7148, 7154, 7166−7167, 7170, 7205, 7272, 7365, 7371, 7384, 7390−7990, 8000−8064, 8066−8068 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Post SB601R−31−022 Subtask 32−22−01−867−002 NOTE: F. Unless it is specified in this procedure, ignore the three white−color UP indications in the GEAR boxes on the EICAS primary page. In this procedure, the three white−color UP indications will not go off after 30 seconds and is normal. When the aircraft is in the correct flight configuration, the three white−color UP indications go out of view after a maximum of 30 seconds after first being seen. This will only happen if: ± There is no message related to brakes, gear, flaps, antiskid, steering, WOW, or the proximity sensor system shown on the EICAS primary and status pages ± The flaps are at zero degrees ± There is no flap overspeed condition. To keep the landing gear horn from being heard during this procedure, and to make sure that the correct indication will be seen on the EICAS primary page, move the throttle levers forward out of the IDLE position. NOTE: If the throttle levers are in the IDLE position, the landing gear is not down and locked, and the logic state is satisfied for the landing gear horn to be heard for 10 seconds or more, one or more of the indications in the three GEAR boxes on the EICAS primary page will become amber and flash with a one second interval. This is a visual indication for additional landing safety and occurs even if the landing gear horn has been muted or disabled. Master EFFECTIVITY: See Pageblock 32−22−01 page 501 505 32−22−01 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL G. Do the steps that follow to retract the NLG and the main landing gear (MLG): WARNING: BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. CAUTION: IF THE FORWARD DOORS OF THE NOSE LANDING GEAR DO NOT OPEN BEFORE THE NOSE LANDING GEAR RETRACTS, PUT THE LANDING−GEAR SELECTOR HANDLE IN THE "DN" POSITION. THE RETRACTION OF THE NOSE LANDING GEAR WILL CAUSE DAMAGE TO THE CLOSED DOORS. (1) Put the LDG GEAR control handle in the UP position. Make sure that the steps that follow occur: ± The forward doors of the NLG open ± The three amber−color gear hash marks are shown on the primary page of the engine indication and crew alerting system (EICAS) ± In approximately 9 to 15 seconds, the NLG and the MLG are retracted and locked and the three white−color UP indications come into view in the three GEAR boxes on the EICAS primary page. **ON A/C ALL Subtask 32−22−01−220−002 H. With the NLG retracted, do the inspection of the door clearances between the forward doors and the rear door (Ref. TASK 32−22−01−220−801). If the clearances are incorrect (but this procedure will correct them), do this procedure again. NOTE: If the clearances between the forward doors and the rear door are not satisfactory and this procedure will not correct them, you will need to do the clearance check of the NLG rear door (Ref. TASK 32−22−05−220−801). Subtask 32−22−01−867−003 I. If the clearances between the forward doors and the rear door are satisfactory, put the LDG GEAR control handle in the DN position. Make sure that the NLG and the MLG extend and lock in the down position, and that the green−color DN indications come into view in the three GEAR boxes on the EICAS primary page. Subtask 32−22−01−980−001 J. Move the throttle levers aft to the IDLE position again. Subtask 32−22−01−867−004 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: K. Master EFFECTIVITY: See Pageblock 32−22−01 page 501 506 32−22−01 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−01−430−001 L. Do the steps that follow to complete the rigging of the forward doors of the nose landing gear: (1) Open and isolate the forward doors of the NLG (Ref. TASK 32−22−01−980−801). (2) Safety the lock nuts (7) with lockwire. (3) Torque the nuts (4) to 25−30 pound−inches (2.82−3.39 N·m). Safety the nuts with the cotter pins (3). (4) Close the forward doors of the NLG (Ref. TASK 32−22−01−980−802). 4. Close Out Subtask 32−22−01−863−001 A. Make sure that the pressure from hydraulic system No. 3 is released (Ref. TASK 12−00−06−863−804). Subtask 32−22−01−861−003 B. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802). Subtask 32−22−01−582−023 C. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−22−01−941−021 D. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−22−01 page 501 507 32−22−01 SepPage 10/2004 C AIRCRAFT MAINTENANCE MANUAL A FORWARD DOOR LEGEND. 1. Control rod. 2. Door. 3. Cotter pin. 4. Nut. 5. Washer. 6. Bolt. 7. Lock nut. 8. Rod end. 9. Door fitting. 1 7 8 4 3 2 6 9 A ram3222015_001.dc, cr/jp, 14/12/92 5 Rigging of the Forward Doors − Adjustment/Test Figure 501 Master EFFECTIVITY: See Pageblock 32−22−01 page 501 32−22−01 Page 508 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL FORWARD DOORS, NOSE LANDING GEAR − INSPECTION/CHECK 1. General A. This section gives the data and procedure necessary to do the mismatch and clearance check of the forward doors of the nose landing gear. The forward doors are installed on the left and the right sides of the nose wheel well. TASK 32−22−01−220−801 Clearance Check of the NLG Forward Doors 1. Job Set−Up Information Subtask 32−22−01−946−020 A. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 10−11−00−000−801 TASK 10−11−00−000−802 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−803 TASK 12−00−06−863−804 TASK 12−00−07−861−801 TASK 12−00−07−861−802 TASK 27−54−00−866−802 TASK 32−22−01−980−801 TASK 32−22−01−980−802 TASK 32−22−01−830−802 TASK 32−22−05−220−801 TASK 32−61−05−220−801 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Removal of the Nose Landing Gear Lockpin Removal of the Main Landing Gear Lockpins Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 Connect the External AC Power Remove the External AC Power Electrical Retraction of the Flaps Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors Rigging of the Forward Doors of the Nose Landing Gear Clearance Check of the NLG Rear Door Gap Inspection of the Proximity Sensor 2. Job Set−Up Subtask 32−22−01−861−001 A. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801). Master EFFECTIVITY: See Pageblock 32−22−01 page 601 32−22−01 Page 601 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−01−582−001 B. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). Make sure that there is at least 4 inches (10 cm) of clearance between the tires and the ground. Subtask 32−22−01−860−020 C. Make sure that the LDG GEAR control handle is in the DN position and that the green−color DN indications are shown in the three GEAR boxes on the engine indication and crew alerting system (EICAS) primary page. Subtask 32−22−01−866−001 D. Make sure that the flaps are fully retracted to zero degrees (Ref. TASK 27−54−00−866−802). Subtask 32−22−01−010−002 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. If they are open, close the forward doors of the nose landing gear (NLG) (Ref. TASK 32−22−01−980−802). WARNING: E. Subtask 32−22−01−090−002 F. Remove the safety lockpins from the nose landing gear and from the main landing gear (Ref. TASK 10−11−00−000−801 and TASK 10−11−00−000−802). Subtask 32−22−01−863−003 G. Pressurize hydraulic system No. 3A and No. 3B (Ref. TASK 12−00−06−863−803). Master EFFECTIVITY: See Pageblock 32−22−01 page 601 32−22−01 Page 602 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7033, 7041, 7052, 7138, 7149, 7180, 7189, 7193 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Pre SB601R−31−022 Subtask 32−22−01−867−020 NOTE: H. I. Unless it is specified in this procedure, ignore the three white−color UP indications in the GEAR boxes on the EICAS primary page. In this procedure, the three white−color UP indications will not go off after 30 seconds and is normal. When the aircraft is in the correct flight configuration, the three white−color UP indications go out of view after a maximum of 30 seconds after first being seen. This will only happen if: ± There is no message related to brakes, gear, flaps, antiskid, steering, WOW, or the proximity sensor system shown on the EICAS primary and status pages ± The flaps are at zero degrees ± There is no flap overspeed condition. To keep the landing gear horn from being heard during this procedure, move the throttle levers forward out of the IDLE position. Do the steps that follow to retract the NLG and the main landing gear (MLG): WARNING: BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. CAUTION: IF THE FORWARD DOORS OF THE NOSE LANDING GEAR DO NOT OPEN BEFORE THE NOSE LANDING GEAR RETRACTS, PUT THE LANDING−GEAR SELECTOR HANDLE IN THE "DN" POSITION. THE RETRACTION OF THE NOSE LANDING GEAR WILL CAUSE DAMAGE TO THE CLOSED DOORS. (1) Put the LDG GEAR control handle in the UP position. Make sure that the steps that follow occur: ± The NLG forward doors open ± The three amber−color gear hash marks are shown on the EICAS primary page ± In approximately 9 to 15 seconds, the NLG and the MLG are retracted and locked and the three white−color UP indications come into view in the three GEAR boxes on the EICAS primary page ± The NLG forward doors close. Master EFFECTIVITY: See Pageblock 32−22−01 page 601 603 32−22−01 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7032, 7059, 7061, 7063, 7094, 7103, 7110, 7115, 7125, 7133, 7142, 7148, 7154, 7166−7167, 7170, 7205, 7272, 7365, 7371, 7384, 7390−7990, 8000−8064, 8066−8068 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Post SB601R−31−022 Subtask 32−22−01−867−005 NOTE: J. K. Unless it is specified in this procedure, ignore the three white−color UP indications in the GEAR boxes on the EICAS primary page. In this procedure, the three white−color UP indications will not go off after 30 seconds and is normal. When the aircraft is in the correct flight configuration, the three white−color UP indications go out of view after a maximum of 30 seconds after first being seen. This will only happen if: ± There is no message related to brakes, gear, flaps, antiskid, steering, WOW, or the proximity sensor system shown on the EICAS primary and status pages ± The flaps are at zero degrees ± There is no flap overspeed condition. To keep the landing gear horn from being heard during this procedure, and to make sure that the correct indication will be seen on the EICAS primary page, move the throttle levers forward out of the IDLE position. NOTE: If the throttle levers are in the IDLE position, the landing gear is not down and locked, and the logic state is satisfied for the landing gear horn to be heard for 10 seconds or more, one or more of the indications in the three GEAR boxes on the EICAS primary page will become amber and flash with a one second interval. This is a visual indication for additional landing safety and occurs even if the landing gear horn has been muted or disabled. Do the steps that follow to retract the NLG and the main landing gear (MLG): WARNING: BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. IF THE FORWARD DOORS OF THE NOSE LANDING GEAR DO NOT CAUTION: OPEN BEFORE THE NOSE LANDING GEAR RETRACTS, PUT THE LANDING−GEAR SELECTOR HANDLE IN THE "DN" POSITION. THE RETRACTION OF THE NOSE LANDING GEAR WILL CAUSE DAMAGE TO THE CLOSED DOORS. (1) Put the LDG GEAR control handle in the UP position. Make sure that the steps that follow occur: ± The NLG forward doors open ± The three amber−color gear hash marks are shown on the EICAS primary page ± In approximately 9 to 15 seconds, the NLG and the MLG are retracted and locked and the three white−color UP indications come into view in the three GEAR boxes on the EICAS primary page Master EFFECTIVITY: See Pageblock 32−22−01 page 601 604 32−22−01 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL ± The NLG forward doors close. **ON A/C ALL Subtask 32−22−01−863−021 L. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−22−01−861−021 M. De−energize the aircraft AC buses (Ref. TASK 12−00−07−861−802). 3. Procedure Subtask 32−22−01−220−024 Refer to Figure 601. A. Measure the mismatches between the left and right forward doors (1) and (2) and the fuselage skin (4) (refer to Figure 601 section B−B). Make sure there is a maximum mismatch of ±0.040 inch (±1.02 mm) at the areas that follow: ± Between the outboard edge of the right forward door (1) and the fuselage skin (4) (at RBL 12.280 and RBL 5.88) ± Between the outboard edge of the left forward door (2) and the fuselage skin (4) (at LBL 12.280 and LBL 5.88) ± Between the right forward door (1) and the left forward door (2) (at BL 0.0). B. Measure the mismatches at the fwd and aft edges of the left and right forward doors (1) and (2) and the fuselage skin (4). Make sure there is a maximum mismatch of ±0.020 inch (±0.51 mm). (1) If you do not get the specified mismatch, then do the rigging of the forward doors of the nose landing gear (Ref. TASK 32−22−01−830−802). C. Measure the clearance between the right and left forward doors (1) and (2) and the fuselage skin (4) (at BL 12.280) at 45 degrees to the skin surface(refer to Figure 601 view D−D). (1) Make sure there is a maximum clearance of 0.080 inch (2.03 mm). (2) Make sure there is a minimum clearance of 0.040 inch (1.02 mm). D. Measure the clearances at the edges of the right and left forward doors (1) and (2) and the fuselage skin (4) in the locations that follow: ± Between the right and left forward doors (1) and (2) at BL 0.0 ± Between the forward edges of the right and left forward doors (1) and (2) and the fuselage skin (4) at FS 170.65 ± Between the edges of the right and left forward doors (1) and (2) and the fuselage skin (4) at FS 202.75. (1) Make sure there is a maximum clearance of 0.080 inch (2.03 mm). (2) Make sure there is a minimum clearance of 0.020 inch (0.51 mm). (3) If you do not get the specified clearance, then remove the unwanted material where Master EFFECTIVITY: See Pageblock 32−22−01 page 601 605 32−22−01 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL E. F. G. applicable from the forward doors (1) and (2). NOTE: To get access to trim the material from the doors, open and isolate the nose landing gear doors (Ref. TASK 32−22−01−980−801). (a) Close the nose landing gear doors (Ref. TASK 32−22−01−980−802) and open and isolate the nose landing gear doors (Ref. TASK 32−22−01−980−801) as required until the doors are correctly trimmed. When the forward doors (1) and (2) are correctly trimmed, close the nose landing gear doors (Ref. TASK 32−22−01−980−802). If the mismatches and clearances between the the right and left forward doors (1) and (2) and at the fuselage skin (4) are correct, do a mismatch and clearance check at the rear door (3) as follows: (1) Measure the mismatch between the forward doors (1) and (2) and the rear door (3) at FS 212.7. Make sure there is a maximum mismatch of ±0.020 inch (0.51 mm). (2) Measure the clearance between the right and left forward doors (1) and (2) and the rear door (3) at FS 212.7. (a) Make sure there is a maximum clearance of 0.080 inch (2.03 mm). (b) Make sure there is a minimum clearance of 0.020 inch (0.51 mm). If the mismatches and clearances of the right and left forward doors (1) and (2) are not correct at the rear door (3), do the clearance check of the rear door (3) (Ref. TASK 32−22−05−220−801). 4. Close Out Subtask 32−22−01−861−022 A. Energize the aircraft AC buses again (Ref. TASK 12−00−07−861−801). Subtask 32−22−01−863−022 B. Pressurize hydraulic system No. 3 (Ref. TASK 12−00−06−863−803). Subtask 32−22−01−867−021 C. If the clearances are satisfactory, put the LDG GEAR control handle in the DN position. Make sure that the NLG and the MLG extend and lock in the down position, and that the green−color DN indications come into view in the three GEAR boxes on the EICAS primary page. Subtask 32−22−01−980−002 D. Move the throttle levers aft to the IDLE position again. Master EFFECTIVITY: See Pageblock 32−22−01 page 601 606 32−22−01 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−01−490−003 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: E. Subtask 32−22−01−863−023 F. Make sure that the pressure from hydraulic system No. 3 is released (Ref. TASK 12−00−06−863−804). Subtask 32−22−01−861−023 G. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802). Subtask 32−22−01−582−021 H. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−22−01−220−020 I. Do a gap check of the closed position proximity sensors (PS18GA and PS19GA) at each NLG forward door (Ref. TASK 32−61−05−220−801). Subtask 32−22−01−941−020 J. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−22−01 page 601 607 32−22−01 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Right forward door. 2. Left forward door. 3. Rear door. 4. Aircraft structure. A FS 170.65 FS 202.75 B FS 212.70 4 2 C 3 D D C BL 0.0 FWD RBL 5.88 MINIMUM CLEARANCE 0.020 in.(0.51 mm) MAXIMUM CLEARANCE 2 0.080 in.(2.03 mm) RBL 12.28 1 2 A B VIEW LOOKING UP SEALANT (REF) 4 4 LBL 12.28 RBL 12.28 4 BL 0.00 45 MINIMUM CLEARANCE 0.020 in.(0.51 mm) MAXIMUM CLEARANCE 1 0.080 in.(2.03 mm) 0 2 1 C − C MAXIMUM MISMATCH + − 0.040 in.(1.02 mm) B − B 4 1 or 2 3 NOTES 1 MAXIMUM MISMATCH + 0.020 in. (0.51 mm) − D − D VIEW LOOKING OUTBOARD ON RIGHT SIDE VIEW LOOKING FORWARD Typical at all solid−shaded edges. Solid−shaded edges 2 Typical at all hatched edges. Hatched edges ram3222016_001(1).dg, rs/rm, 06/03/97 VIEW LOOKING FORWARD NLG Forward Doors − Clearance Check Figure 601 Master EFFECTIVITY: See Pageblock 32−22−01 page 601 32−22−01 Page 608 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL REAR DOOR, NOSE LANDING GEAR − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the nose−landing−gear (NLG) rear door. TASK 32−22−05−000−801 Removal of the Nose−Landing−Gear Rear Door 1. Job Set−Up Information Subtask 32−22−05−946−001 A. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 29−00−00−910−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Hydraulic Safety Precautions 2. Job Set−Up Subtask 32−22−05−910−002 WARNING: A. OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). Subtask 32−22−05−490−002 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: B. 3. Procedure Subtask 32−22−05−020−001 Refer to Figure 401. A. Remove the NLG rear door (1) as follows: (1) Remove the nut (2), the lockwasher (3), the washers (4), and the bonding jumper (5) from the screw (6). Master EFFECTIVITY: See Pageblock 32−22−05 page 401 32−22−05 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (2) Disconnect each control rod (12) and (14) from its related door lower fitting (13) and (15) on the NLG rear door (1) as follows: (a) Remove and discard the cotter pin (7). (b) Remove the nut (8), the washer (9), the spacer (11), the washer (23) and the bolt (10). Disconnect the control rods (12) and (14). (3) Disconnect the NLG rear door (1) from each upper fitting (19) and (20) at the fuselage as follows: (a) At each upper fitting (19) and (20), remove the nuts (16), the washers (17), and the screws (18). (4) Remove the NLG rear door (1) from the aircraft. Master EFFECTIVITY: See Pageblock 32−22−05 page 401 32−22−05 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL FS 235.00 LEGEND 1. Rear door of the nose landing gear. 2. Nut. 3. Lockwasher. 4. Washer. 5. Bonding jumper. 6. Screw. 7. Cotter pin. 8. Nut. 9. Washer. 10. Bolt. 11. Spacer. 12. Left control rod. 13. Lower left fitting. 14. Right control rod. 15. Lower right fitting. 16. Nut. 17. Washer. 18. Screw. 19. Upper left fitting. 20. Upper right fitting. 21. Locknut. 22. Rod end. 23. Washer. A FS 231.50 20 18 5 6 19 FS 235.00 17 3 16 4 2 1 14 21 22 23 11 21 15 8 7 A 8 9 13 11 23 22 10 ram3222054_001(2).dc, pb/rm, 21/04/97 12 Rear Door of the Nose Landing Gear − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−22−05 page 401 32−22−05 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−22−05−400−801 Installation of the Rear Door of the Nose Landing Gear 1. Job Set−Up Information Subtask 32−22−05−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Torque wrench, torque range 0−50 pound−inches (0−5.7 N·m) Subtask 32−22−05−944−002 B. Consumable Materials REFERENCE 05−004 DESIGNATION Lockwire Subtask 32−22−05−945−001 C. Parts REF 2 3 4 7 8 9 10 11 16 17 18 23 NAME OF PART Nut Lockwasher Washer Cotter pin Nut Washer Bolt Spacer Nut Washer Screw Washer QTY 1 1 2 2 2 2 2 2 4 4 4 2 IPC SEQUENCE NO. IPC 32−22−00−01−360 IPC 32−22−00−01−350 IPC 32−22−00−01−345 IPC 32−22−00−01−425 IPC 32−22−00−01−420 IPC 32−22−00−01−445 IPC 32−22−00−01−400 IPC 32−22−00−01−410 IPC 32−22−00−01−290 IPC 32−22−00−01−285 IPC 32−22−00−01−280 IPC 32−22−00−01−445 Subtask 32−22−05−946−002 D. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 32−22−01−980−801 TASK 32−22−01−980−802 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors Master EFFECTIVITY: See Pageblock 32−22−05 page 401 32−22−05 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REFERENCE TASK 32−30−00−710−802 DESIGNATION Landing Gear Extension and Retraction − Maintenance Practices 2. Job Set−Up Subtask 32−22−05−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Subtask 32−22−05−582−024 B. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). Subtask 32−22−05−867−022 STAY AWAY FROM HYDRAULICALLY ACTUATED COMPONENTS RELATED TO THE LANDING GEAR AND THE NLG FORWARD DOORS WHEN PRESSURE IS APPLIED TO THE HYDRAULIC SYSTEMS. THESE HYDRAULICALLY ACTUATED COMPONENTS CAN CAUSE INJURIES WHEN THE HYDRAULIC SYSTEMS ARE PRESSURIZED. CAUTION: MAKE SURE THAT THE CONTROL RODS WILL NOT CATCH THE GEAR OR SURROUNDING AREA WHEN THE LANDING GEAR IS OPERATED. DAMAGE TO THE AIRCRAFT CAN OCCUR. C. Retract the landing gear (Ref. TASK 32−30−00−710−802). Make sure that the nose landing gear and the main landing gear are up and locked. WARNING: Subtask 32−22−05−910−001 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the NLG forward doors (Ref. TASK 32−22−01−980−801). WARNING: D. Master EFFECTIVITY: See Pageblock 32−22−05 page 401 32−22−05 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. Procedure Subtask 32−22−05−420−001 Refer to Figure 401. A. Install the NLG rear door (1) as follows: (1) Align the NLG rear door (1) with the upper left and the upper right fittings (19) and (20). (2) Install the screws (18), the washers (17), and the nuts (16) at four places to attach the upper left and the upper right fittings (19) and (20) to the NLG rear door (1). (3) Tighten the nuts (16). (4) Move the door (1) to the closed position by hand. (5) Make sure that the clearance between the left and right edges of the NLG rear door (1) and the fuselage skin is 0.030−0.080 inch (0.76−2.03 mm). (6) Make sure that the clearance between the aft edge of the NLG rear door (1) and the fuselage skin is 0.030−0.283 inch (0.76−7.20 mm). (7) Torque the nuts (16) to 20−25 pound−inches (2.26−2.82 Nm) and do a final check of the gaps. (8) Hold the NLG rear door (1) firmly at the closed position, and align the control rods (12) and (14) with their related door lower fittings (13) and (15). NOTE: Make sure that the NLG rear door (1) is flush with the surrounding fuselage skin. There must be a maximum door−to−skin mismatch of ±0.040 inch (1.02 mm) at the left, right, and aft edges of the NLG rear door (1). NOTE: Make sure that you can install the bolt (10) freely through each rod end (22) and its related door lower fitting (13) or (15). (9) If necessary, adjust the length of the control rods (12) and (14) as follows: NOTE: Make sure that the door is held firmly and flush to the aircraft when you insert the bolt (10) through the rod end (22) and the door lower fitting (13) or (15). (a) Remove and discard the lockwire from the locknut (21) on the rod end (22). (b) Loosen the locknut (21). (c) Adjust the length of the control rods (12) and (14) until the bolt (10) can be inserted freely through the rod end (22) and its applicable door lower fitting (13) or (15). (10) When the control rods (12) and (14) are correctly adjusted, temporarily install the bolt (10), the washer (23), the spacer (11), the washer (9), and the nut (8). NOTE: Make sure that the washer (23) is installed between the rod end (22) and the spacer (11). (11) Temporarily tighten the locknut (21). Master EFFECTIVITY: See Pageblock 32−22−05 page 401 32−22−05 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL WARNING: STAY AWAY FROM HYDRAULICALLY ACTUATED COMPONENTS RELATED TO THE LANDING GEAR AND THE NLG FORWARD DOORS WHEN PRESSURE IS APPLIED TO THE HYDRAULIC SYSTEMS. THESE HYDRAULICALLY ACTUATED COMPONENTS CAN CAUSE INJURIES WHEN THE HYDRAULIC SYSTEMS ARE PRESSURIZED. (12) Extend the landing gear (Ref. TASK 32−30−00−710−802). Make sure that the nose landing gear and the main landing gear are down and locked. (13) Install the bonding jumper (5) with one washer (4) on each side, the lockwasher (3), and the nut (2) on the screw (6). (14) Make sure that there is a minimum clearance of 0.030 inch (0.76 mm) between the lower surface NLG rear door (1) and the fuselage skin when the NLG is fully extended and locked. Adjust the left and right control rods (12) and (14) again as required to get the correct clearance. NOTE: It is possible that the left and right control rods (12) and (14) will have to be adjusted again to get the correct door−to−skin mismatch when the NLG rear door (1) is closed. WARNING: STAY AWAY FROM HYDRAULICALLY ACTUATED COMPONENTS RELATED TO THE LANDING GEAR AND THE NLG FORWARD DOORS WHEN PRESSURE IS APPLIED TO THE HYDRAULIC SYSTEMS. THESE HYDRAULICALLY ACTUATED COMPONENTS CAN CAUSE INJURIES WHEN THE HYDRAULIC SYSTEMS ARE PRESSURIZED. (15) Retract the landing gear (Ref. TASK 32−30−00−710−802). Make sure that the nose landing gear and the main landing gear are up and locked. (16) Close the NLG forward doors (Ref. TASK 32−22−01−980−802). (17) Make sure that the NLG rear door (1) is flush with the forward doors. There must be a maximum door−to−door mismatch of ±0.030 inch (0.76 mm) at the forward edge of the NLG rear door (1). (18) Make sure that the clearance between the NLG rear door (1) and the forward doors is satisfactory. There must be a minimum clearance of 0.020 inch (0.51) and a maximum clearance of 0.080 inch (2.03 mm) at the forward edge of the NLG rear door (1). (19) If the clearance between the lower surface NLG rear door (1) and the fuselage skin was adjusted when the NLG was fully extended and locked, do the step that follows: (a) Make sure that the clearance between the left and right edges NLG rear door (1) and the fuselage skin is still correct. If it is not correct, it is possible that the left and right control rods (12) and (14) will have to be adjusted again to get the correct door−to−skin mismatch. (20) If the NLG rear door (1) clearances and mismatches are satisfactory, do the steps that follow: Master EFFECTIVITY: See Pageblock 32−22−05 page 401 32−22−05 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL WARNING: (a) (b) (c) (d) (e) (f) STAY AWAY FROM HYDRAULICALLY ACTUATED COMPONENTS RELATED TO THE LANDING GEAR AND THE NLG FORWARD DOORS WHEN PRESSURE IS APPLIED TO THE HYDRAULIC SYSTEMS. THESE HYDRAULICALLY ACTUATED COMPONENTS CAN CAUSE INJURIES WHEN THE HYDRAULIC SYSTEMS ARE PRESSURIZED. Extend the landing gear (Ref. TASK 32−30−00−710−802). Make sure that the nose landing gear and the main landing gear are down and locked. Install the bolt (10), the washer (23), the spacer (11), the washer (9), and the nut (8). NOTE: Make sure that the washer (23) is installed between the rod end (22) and the spacer (11). If the control rods (12) and (14) were adjusted, make sure that the locknuts (21) on the rod ends (22) are tightened. Safety the locknuts (21) on the rod ends (22) with 05−004 lockwire. Torque the nuts (8) to 25−30 pound−inches (2.82−3.39 N·m). Safety the nuts (8) with the cotter pins (7). 4. Close Out Subtask 32−22−05−941−001 A. Remove all tools, equipment, and unwanted materials from the work area. Subtask 32−22−05−710−001 STAY AWAY FROM HYDRAULICALLY ACTUATED COMPONENTS RELATED TO THE LANDING GEAR AND THE NLG FORWARD DOORS WHEN PRESSURE IS APPLIED TO THE HYDRAULIC SYSTEMS. THESE HYDRAULICALLY ACTUATED COMPONENTS CAN CAUSE INJURIES WHEN THE HYDRAULIC SYSTEMS ARE PRESSURIZED. Do one more complete retraction and extension of the NLG and make sure that the rear door operates correctly (Ref. TASK 32−30−00−710−802). WARNING: B. Subtask 32−22−05−582−025 C. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Master EFFECTIVITY: See Pageblock 32−22−05 page 401 32−22−05 Page 408 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL REAR DOOR, NOSE LANDING GEAR (NLG) − ADJUSTMENT/TEST 1. General A. The maintenance procedure that follows is for the adjustment of the nose landing gear (NLG) rear door. The NLG rear door is installed on the forward fuselage and attached to the NLG. TASK 32−22−05−820−801 Adjustment of the NLG Rear Door 1. Job Set−Up Information Subtask 32−22−05−944−001 A. Consumable Materials REFERENCE 05−006 DESIGNATION Lockwire Subtask 32−22−05−945−003 B. Parts REF 2 3 4 5 6 7 10 NAME OF PART Cotter pin Bolt Nut Washer Spacer Door fitting Nut QTY 2 2 2 2 2 4 8 IPC SEQUENCE NO. IPC 32−22−00−01−425 IPC 32−22−00−01−400 IPC 32−22−00−01−420 IPC 32−22−00−01−415 IPC 32−22−00−01−410 IPC 32−22−00−01−315 IPC 32−22−00−01−330 Subtask 32−22−05−946−021 C. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 12−00−06−863−803 TASK 12−00−06−863−804 TASK 12−00−07−861−801 TASK 12−00−07−861−802 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 Connect External AC Power Remove External AC Power Master EFFECTIVITY: See Pageblock 32−22−05 page 501 32−22−05 Page 501 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 2. Job Set−Up Subtask 32−22−05−582−022 A. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). 3. Procedure Subtask 32−22−05−820−001 Refer to Figure 501. A. Do the adjustment of the rear door as follows: NOTE: This procedure is applicable for the adjustment of the left control rod. The adjustment for the right control rod is the same. (1) Remove and discard the lockwire from the control rod (1). (2) Remove and discard the cotter pin (2) from the bolt (3). (3) Remove the nut (4), the washer (5), the spacer (6), and the bolt (3). Disconnect the control rod (1) from the rear door fitting (7). (4) Loosen the locknut (8). Turn and adjust the rod end (9). NOTE: The rod end is adjusted to the necessary length until the clearances between the door and the fuselage are correct, when the door is closed. (5) Attach the control rod (1) to the rear door fitting (7) with the bolt (3), the spacer (6), the washer (5), and the nut (4). NOTE: Do not safety the nut with the cotter pin at this time. (6) Tighten the locknut (8) against the control rod (1). NOTE: Do not safety the locknut with lockwire at this time. (7) Connect external ac power to the aircraft (Ref. TASK 12−00−07−861−801). (8) Pressurize hydraulic system No. 3 (Ref. TASK 12−00−06−863−803). (9) Move the landing gear lever in the flight compartment to the UP position and retract the landing gear. Install a DO NOT OPERATE THE LANDING GEAR tag on the lever. (10) Make sure that the clearances between the doors and between the doors and fuselage skin are as follows: (a) For the left and right edges (BL12.280) of the forward doors: 0.040 inches to 0.080 inches (1.02 mm to 2.03 mm) at 45 degrees of skin surface. (b) For all the other edges of the forward doors: 0.020 inches to 0.080 inches (0.51 mm to 2.03 mm). (c) For the left and right edges of the aft door 0.050 inches (1.27 mm) maximum. (11) The mismatch between doors and between doors and fuselage contour must be as follows: (a) For all longitudinal edges (right, left center) of all doors: ±0.040 inches (±1.02 mm). (b) For the forward and aft edges of the forward doors: ±0.020 inches (±0.51 mm). (c) For the aft edge of the aft door: 0.050 inches (1.27 mm) maximum. Master EFFECTIVITY: See Pageblock 32−22−05 page 501 32−22−05 Page 502 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (12) (13) (14) (15) Move the landing gear lever to the DN position and extend the landing gear. If necessary, do this procedure until the clearances are correct. Safety the locknut (8) with 05−006 lockwire. Safety the nut (4) with the cotter pin (2). 4. Close Out Subtask 32−22−05−863−024 A. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−22−05−861−024 B. Remove the external ac power from the aircraft (Ref. TASK 12−00−07−861−802). Subtask 32−22−05−582−023 C. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−22−05−941−021 D. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−22−05 page 501 32−22−05 Page 503 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL C A MINIMUM CLEARANCE 0.030 in. (0.76 mm) MAXIMUM CLEARANCE 0.080 in. (2.03 mm) MAXIMUM MISMATCH ±0.02 in. (0.51 mm) B B MAXIMUM MISMATCH ±0.03 in. (0.76 mm) MAXIMUM CLEARANCE 0.283 in. (7.20 mm) B FWD A 1 8 3 10 2 4 7 5 6 C 9 ram3222055_001.dg, pb/lr, 3/07/03 LEGEND 1. Control rod. 2. Cotter pin. 3. Bolt. 4. Nut. 5. Washer. 6. Spacer. 7. Door fitting. 8. Locking nut. 9. Rod end. 10. Nut. NLG Rear Door − Adjustment/ Test Figure 501 Master EFFECTIVITY: See Pageblock 32−22−05 page 501 32−22−05 Page 504 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL REAR DOOR, NOSE LANDING GEAR − INSPECTION/CHECK 1. General A. This section gives the data and procedure necessary to do an inspection of the rear door of the nose landing gear (NLG). The NLG rear door is installed on the forward fuselage at the aft edge of the NLG wheel well and is attached to the NLG by two connecting rods. TASK 32−22−05−220−801 Clearance Check of the NLG Rear Door 1. Job Set−Up Information Subtask 32−22−05−946−020 A. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 10−11−00−000−801 TASK 10−11−00−000−802 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−803 TASK 12−00−06−863−804 TASK 12−00−07−861−801 TASK 12−00−07−861−802 TASK 27−54−00−866−802 TASK 32−22−01−830−802 TASK 32−22−01−980−801 TASK 32−22−01−980−802 TASK 32−22−05−820−801 TASK 32−30−00−710−802 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Removal of the Nose Landing Gear Lockpin Removal of the Main Landing Gear Lockpins Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 Connect the External AC Power Remove the External AC Power Electrical Retraction of the Flaps Rigging of the Forward Doors of the Nose Landing Gear Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors Adjustment of the NLG Rear Door Landing Gear Extension and Retraction − Maintenance Practices 2. Job Set−Up Subtask 32−22−05−861−005 A. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801). Master EFFECTIVITY: See Pageblock 32−22−05 page 601 32−22−05 Page 601 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−05−582−002 B. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). Make sure that there is at least 4 inches (10 cm) of clearance between the tires and the ground. Subtask 32−22−05−860−003 C. Make sure that the LDG GEAR control handle is in the DN position and that the green−color DN indications are shown in the three GEAR boxes on the engine indication and crew alerting system (EICAS) primary page. Subtask 32−22−05−866−001 D. Make sure that the flaps are fully retracted to zero degrees (Ref. TASK 27−54−00−866−802). Subtask 32−22−05−010−020 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. If they are open, close the forward doors of the nose landing gear (NLG) (Ref. TASK 32−22−01−980−802). WARNING: E. Subtask 32−22−05−090−001 F. Remove the safety lockpins from the nose landing gear and from the main landing gear (Ref. TASK 10−11−00−000−801 and TASK 10−11−00−000−802). Subtask 32−22−05−863−020 G. Pressurize hydraulic system No. 3A and No. 3B (Ref. TASK 12−00−06−863−803). Master EFFECTIVITY: See Pageblock 32−22−05 page 601 32−22−05 Page 602 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7033, 7041, 7052, 7138, 7149, 7180, 7189, 7193 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Pre SB601R−31−022 Subtask 32−22−05−867−020 NOTE: H. I. Unless it is specified in this procedure, ignore the three white−color UP indications in the GEAR boxes on the EICAS primary page. In this procedure, the three white−color UP indications will not go off after 30 seconds and is normal. When the aircraft is in the correct flight configuration, the three white−color UP indications go out of view after a maximum of 30 seconds after first being seen. This will only happen if: ± There is no message related to brakes, gear, flaps, antiskid, steering, WOW, or the proximity sensor system shown on the EICAS primary and status pages ± The flaps are at zero degrees ± There is no flap overspeed condition. To keep the landing gear horn from being heard during this procedure, move the throttle levers forward out of the IDLE position. Do the steps that follow to retract the NLG and the main landing gear (MLG): WARNING: BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. CAUTION: IF THE FORWARD DOORS OF THE NOSE LANDING GEAR DO NOT OPEN BEFORE THE NOSE LANDING GEAR RETRACTS, PUT THE LANDING−GEAR SELECTOR HANDLE IN THE "DN" POSITION. THE RETRACTION OF THE NOSE LANDING GEAR WILL CAUSE DAMAGE TO THE CLOSED DOORS. (1) Put the LDG GEAR control handle in the UP position. Make sure that the steps that follow occur: ± The NLG forward doors open ± The three amber−color gear hash marks are shown on the EICAS primary page ± In approximately 9 to 15 seconds, the NLG and the MLG are retracted and locked and the three white−color UP indications come into view in the three GEAR boxes on the EICAS primary page ± The NLG doors close. Master EFFECTIVITY: See Pageblock 32−22−05 page 601 603 32−22−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7032, 7059, 7061, 7063, 7094, 7103, 7110, 7115, 7125, 7133, 7142, 7148, 7154, 7166−7167, 7170, 7205, 7272, 7365, 7371, 7384, 7390−7990, 8000−8064, 8066−8068 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Post SB601R−31−022 Subtask 32−22−05−867−001 NOTE: J. K. Unless it is specified in this procedure, ignore the three white−color UP indications in the GEAR boxes on the EICAS primary page. In this procedure, the three white−color UP indications will not go off after 30 seconds and is normal. When the aircraft is in the correct flight configuration, the three white−color UP indications go out of view after a maximum of 30 seconds after first being seen. This will only happen if: ± There is no message related to brakes, gear, flaps, antiskid, steering, WOW, or the proximity sensor system shown on the EICAS primary and status pages ± The flaps are at zero degrees ± There is no flap overspeed condition. To keep the landing gear horn from being heard during this procedure, and to make sure that the correct indication will be seen on the EICAS primary page, move the throttle levers forward out of the IDLE position. NOTE: If the throttle levers are in the IDLE position, the landing gear is not down and locked, and the logic state is satisfied for the landing gear horn to be heard for 10 seconds or more, one or more of the indications in the three GEAR boxes on the EICAS primary page will become amber and flash with a one second interval. This is a visual indication for additional landing safety and occurs even if the landing gear horn has been muted or disabled. Do the steps that follow to retract the NLG and the main landing gear (MLG): WARNING: BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. IF THE FORWARD DOORS OF THE NOSE LANDING GEAR DO NOT CAUTION: OPEN BEFORE THE NOSE LANDING GEAR RETRACTS, PUT THE LANDING−GEAR SELECTOR HANDLE IN THE "DN" POSITION. THE RETRACTION OF THE NOSE LANDING GEAR WILL CAUSE DAMAGE TO THE CLOSED DOORS. (1) Put the LDG GEAR control handle in the UP position. Make sure that the steps that follow occur: ± The NLG forward doors open ± The three amber−color gear hash marks are shown on the EICAS primary page ± In approximately 9 to 15 seconds, the NLG and the MLG are retracted and locked and the three white−color UP indications come into view in the three GEAR boxes on the EICAS primary page Master EFFECTIVITY: See Pageblock 32−22−05 page 601 604 32−22−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL ± The NLG doors close. **ON A/C ALL Subtask 32−22−05−863−021 L. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−22−05−861−021 M. De−energize the aircraft AC buses (Ref. TASK 12−00−07−861−802). 3. Procedure Subtask 32−22−05−220−024 Refer to Figure 601. A. Measure the rear door (3) to fuselage skin (4) mismatch as follows: NOTE: Hold a straightedge across the clearance between the edge of the rear door (3) and the fuselage skin (4) to check the mismatch (Refer to Figure 601, section B−B and section C−C). (1) Measure the mismatch between the rear door (3) and the fuselage skin (4) at the outboard edges of the rear door (3). Make sure there is a maximum mismatch of ±0.040 inch (±1.02 mm). (2) Measure the mismatch between the aft edge of the rear door (3) and the fuselage skin (4). Make sure there is a maximum mismatch of ±0.030 inch (±0.76 mm). (3) If you do not get the specified mismatch, then do an adjustment of the NLG rear door (Ref. TASK 32−22−05−820−801). B. Measure the rear door (3) to fuselage skin (4) clearance as follows: (1) Measure the clearance between the rear door (3) and the fuselage skin (4) at the outboard edges of the rear door (3) (Refer to Figure 601, view A). (a) Make sure there is a maximum clearance of 0.080 inch (2.03 mm). (b) Make sure there is a minimum clearance of 0.030 inch (0.76 mm). (2) Measure the clearance between the rear door (3) and the fuselage skin (4) at the aft edge of the rear door (3) (Refer to Figure 601, view A). (a) Make sure there is a maximum clearance of 0.283 inch (7.20 mm). (b) Make sure there is a minimum clearance of 0.030 inch (0.76 mm). C. If you do not get the specified clearance, then do an adjustment of the NLG rear door (Ref. TASK 32−22−05−820−801). D. To get access to trim the material from the doors, do the steps that follow: (1) Extend the landing gear (Ref. TASK 32−22−01−980−801) and trim the doors as required. NOTE: Make sure there is a minimum clearance of 0.030 inch (0.76 mm) between the rear door (3) and the fuselage (4) at FS 233.8 when the NLG is fully extended and locked (Refer to Figure 601, view D). Master EFFECTIVITY: See Pageblock 32−22−05 page 601 605 32−22−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (2) When the doors are correctly trimmed, retract the landing gear (Ref. TASK 32−22−01−980−801). Subtask 32−22−05−220−021 E. If the mismatch and clearance of the rear door (3) is correct at the fuselage skin (4), do a mismatch and clearance check between the aft edges of the right and left forward doors (1) and (2) and the rear door (3) as follows: (1) Make sure that the forward doors (1) and (2) are rigged correctly (Ref. TASK 32−22−01−830−802). (2) Measure the mismatches between the forward doors (1) and (2) and the rear door (3). Make sure there is a maximum mismatch of ±0.020 inch (±0.51 mm) (Refer to Figure 601, section B−B). (3) Measure the clearance between the right and left forward doors (1) and (2) and the rear door (3) (Refer to Figure 601, view A). (a) Make sure there is a maximum clearance of 0.080 inch (2.03 mm). (b) Make sure there is a minimum clearance of 0.020 inch (0.51 mm). (4) If you do not get the correct measurement, then do an adjustment of the rear door of the nose landing gear (Ref. TASK 32−22−05−820−801) or trim the material (as necessary) from the forward or rear doors (where applicable). 4. Close Out Subtask 32−22−05−861−022 A. Energize the aircraft AC buses again (Ref. TASK 12−00−07−861−801). Subtask 32−22−05−863−022 B. Pressurize hydraulic system No. 3 (Ref. TASK 12−00−06−863−803). Subtask 32−22−05−867−021 C. If the clearances are satisfactory, put the LDG GEAR control handle in the DN position. Make sure that the NLG and the MLG extend and lock in the down position, and that the green−color DN indications come into view in the three GEAR boxes on the EICAS primary page. Subtask 32−22−05−980−001 D. Move the throttle levers aft to the IDLE position again. Subtask 32−22−05−490−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: E. Master EFFECTIVITY: See Pageblock 32−22−05 page 601 606 32−22−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−05−863−005 F. Make sure that the pressure from hydraulic system No. 3 is released (Ref. TASK 12−00−06−863−804). Subtask 32−22−05−861−023 G. Remove the external AC power (Ref. TASK 12−00−07−861−802). Subtask 32−22−05−582−021 H. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−22−05−941−020 I. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−22−05 page 601 32−22−05 Page 607 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL MINIMUM CLEARANCE 0.030 in. (0.76 mm) MAXIMUM CLEARANCE 0.080 in. (2.03 mm) A 2 D C B B FWD MAXIMUM CLEARANCE 0.283 in. (7.20 mm) C BL0.0 MINIMUM CLEARANCE 0.020 in. (0.51 mm) MAXIMUM CLEARANCE 0.080 in. (2.03 mm) LEGEND 1. Right forward door. 2. Left forward door. 3. Rear door. 4. Aircraft structure. RBL5.88 4 1 FS212.70 3 FS233.75 A VIEW LOOKING UP MAXIMUM MISMATCH ±0.020 in. (0.51 mm) 4 3 4 MAXIMUM MISMATCH ±0.040 in. (1.02 mm) 3 2 MAXIMUM MISMATCH ±0.030 in. (0.76 mm) B − B C − C VIEW LOOKING OUTBOARD ON RIGHT SIDE VIEW LOOKING FORWARD 3 4 UP MINIMUM CLEARANCE ±0.030 in. (0.76 mm) D VIEW LOOKING INBOARD WITH DOOR OPEN ram3222056_001.dg, rm/lr, 3/07/03 FS233.80 NLG Rear Door − Clearance Check Figure 601 Master EFFECTIVITY: See Pageblock 32−22−05 page 601 32−22−05 Page 608 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL DOOR ACTUATOR, NOSE LANDING GEAR − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the actuator for the nose landing gear (NLG) forward doors. The NLG door actuator is installed in the right door−operating mechanism that is located on the right side of the NLG bay. TASK 32−22−10−000−801 Removal of the NLG Door Actuator 1. Job Set−Up Information Subtask 32−22−10−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Container, hydraulic fluid resistant Subtask 32−22−10−946−001 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 29−00−00−910−801 TASK 32−22−01−980−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions Open and Isolate the Nose−Landing−Gear Forward Doors 2. Job Set−Up Subtask 32−22−10−490−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. A. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: MAKE SURE THAT THE WHEEL CHOCKS ARE PUT AT THE MAIN WHEELS. IF YOU DO NOT DO THIS, THE AIRCRAFT CAN MOVE. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. B. Install wheel chocks at the main wheels. WARNING: Master EFFECTIVITY: See Pageblock 32−22−10 page 401 32−22−10 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−10−910−001 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: C. Subtask 32−22−10−010−001 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the NLG forward doors (Ref. TASK 32−22−01−980−801). WARNING: D. Subtask 32−22−10−863−001 E. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−22−10−865−001 F. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. G11 A2 G15 A2 NAME HYD SYST AC PUMP CONT 3B HYD PUMP 3B HYD SYST AC PUMP CONT 3A HYD PUMP 3A ZONE 221 221 222 222 3. Procedure **ON A/C 7003−7067, 7069−7500, 7522, 7524 Subtask 32−22−10−020−001 Refer to Figure 401. A. Remove the NLG door actuator (1) as follows: (1) Put a container that is resistant to hydraulic fluid below the work area. (2) Disconnect the hydraulic lines from the fittings in the extension and retraction ports of the NLG door actuator (1). Master EFFECTIVITY: See Pageblock 32−22−10 page 401 32−22−10 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (3) Install protective caps/plugs on the hydraulic lines and on the fittings in the extension and retraction ports of the NLG door actuator (1). (4) At the bottom end of the NLG door actuator (1), remove and discard the cotter pin (2). (5) Remove the nut (3), the bolt (4), and the bushings (5). NOTE: The holes in the bushings are used to help with their removal. (6) At the top end of the NLG door actuator (1), remove and discard the cotter pin (6). (7) Remove the nut (7), the washer (8), and the bolt (10). (8) Remove the NLG door actuator (1) and the two washers (9). NOTE: The two washers (9) are installed on each side of the bearing in the upper lever assembly; between the upper lever assembly and the fork−end of the NLG door actuator (1). **ON A/C 7501−7521, 7523, 7525−7990, 8000−8064, 8066−8068 Subtask 32−22−10−020−002 Refer to Figure 402. B. Remove the NLG door actuator (1) as follows: (1) Put a container that is resistant to hydraulic fluid below the work area. (2) Disconnect the hydraulic lines from the fittings in the extension and retraction ports of the NLG door actuator (1). (3) Install protective caps/plugs on the hydraulic lines and on the fittings in the extension and retraction ports of the NLG door actuator (1). (4) At the bottom end of the NLG door actuator (1), remove and discard the cotter pin (2). (5) Remove the nut (3), the bolt (4), and the bushings (5). NOTE: The holes in the bushings are used to help with their removal. (6) Remove the Teflon washers (11), that are installed between the bearing in the bottom of the NLG door actuator (1) and the related attachment lugs of the rocking lever. (7) At the top end of the NLG door actuator (1), remove and discard the cotter pin (6). (8) Remove the nut (7), the washer (8), and the bolt (10). (9) Remove the NLG door actuator (1) and the two washers (9). NOTE: The two washers (9) are installed on each side of the bearing in the upper lever assembly; between the upper lever assembly and the fork−end of the NLG door actuator (1). Master EFFECTIVITY: See Pageblock 32−22−10 page 401 403 32−22−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL FS202.75 10 RIGGING RIGGING PIN P1 PIN P2 (REF) (REF) A CL FS235.00 9 8 6 7 RIGHT DOOR− OPERATING MECHANISM (REF) JAM NUTS (REF) 1 4 HYDRAULIC HOSES (REF) 5 HOLE (REF) ROCKING LEVER (REF) NOTE LEGEND 1. NLG door actuator. 6. Cotter pin. 7. Nut. 2. Cotter pin. 8. Washer. 3. Nut. 9. Washer. 4. Bolt. 10. Bolt. 5. Bushing. 5 HOLE (REF) The door−operating mechanism is shown in the closed and locked postion. 3 2 A ram3222104_001.dg, rs/rm, 23/01/02 CL OF THE NLG DOOR ACTUATOR NLG Door Actuator − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−22−10 page 401 32−22−10 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL RIGGING PIN P2 (REF) FS202.75 A RIGGING PIN P1 (REF) 10 CL 9 FS235.00 8 6 7 JAM NUTS (REF) 1. NLG door actuator. 1 2. Cotter pin. 3. Nut. 4. Bolt. 5. Bushing. 6. Cotter pin. 7. Nut. 8. Washer. 9. Washer. 10. Bolt. 11. Teflon washer. CL OF THE NLG DOOR ACTUATOR 5 HYDRAULIC HOSE (REF) 11 4 11 HOLE (REF) NOTE The door−operating mechanism is shown in the closed and locked postion. HYDRAULIC HOSE (REF) 5 3 ROCKING LEVER (REF) HOLE (REF) 2 A ram3222104_004.dg, rs/yf, 23/07/04 LEGEND RIGHT DOOR− OPERATING MECHANISM (REF) NLG Door Actuator − Removal/Installation Figure 402 Master EFFECTIVITY: See Pageblock 32−22−10 page 401 405 32−22−10 SepPage 10/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL TASK 32−22−10−400−801 Installation of the NLG Door Actuator 1. Job Set−Up Information Subtask 32−22−10−943−003 A. Tools and Equipment REFERENCE G601R270001−1 None specified DESIGNATION Kit, rigging pins Container, hydraulic fluid resistant Subtask 32−22−10−944−002 B. Consumable Materials REFERENCE 05−004 DESIGNATION Lockwire **ON A/C 7003−7067, 7069−7500, 7522, 7524 Subtask 32−22−10−945−001 C. Parts REF 2 3 4 5 6 7 8 9 10 12 13 14 15 16 17 18 19 NAME OF PART Cotter pin Nut Bolt Bushing Cotter pin Nut Washer Washer Bolt Cotter pin Nut Washer Bolt Jam nut Stop bolt Jam nut Stop bolt Master EFFECTIVITY: See Pageblock 32−22−10 page 401 QTY 1 1 1 2 1 1 1 2 1 1 1 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−22−00−03−195 IPC 32−22−00−03−190 IPC 32−22−00−03−180 IPC 32−22−00−03−185 IPC 32−22−00−03−175 IPC 32−22−00−03−170 IPC 32−22−00−03−160 IPC 32−22−00−03−165 IPC 32−22−00−03−155 IPC 32−22−00−02−035 IPC 32−22−00−02−030 IPC 32−22−00−02−020 IPC 32−22−00−02−015 IPC 32−22−00−03−430 IPC 32−22−00−03−423 IPC 32−22−00−03−430 IPC 32−22−00−03−425 32−22−10 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7501−7521, 7523, 7525−7990, 8000−8064, 8066−8068 Subtask 32−22−10−945−003 D. Parts REF 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 NAME OF PART Cotter pin Nut Bolt Bushing Cotter pin Nut Washer Washer Bolt Washer (Teflon) Cotter pin Nut Washer Bolt Jam nut Stop bolt Jam nut Stop bolt QTY 1 1 1 2 1 1 1 2 1 2 1 1 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−22−00−03−195 IPC 32−22−00−03−190 IPC 32−22−00−03−180 IPC 32−22−00−03−185 IPC 32−22−00−03−175 IPC 32−22−00−03−170 IPC 32−22−00−03−160 IPC 32−22−00−03−165 IPC 32−22−00−03−155 IPC 32−22−00−03−187 IPC 32−22−00−02−035 IPC 32−22−00−02−030 IPC 32−22−00−02−020 IPC 32−22−00−02−015 IPC 32−22−00−03−430 IPC 32−22−00−03−423 IPC 32−22−00−03−430 IPC 32−22−00−03−425 **ON A/C ALL Subtask 32−22−10−946−002 E. Reference Information REFERENCE TASK 29−00−00−910−801 TASK 29−10−00−870−803 TASK 32−00−00−790−801 TASK 32−22−01−980−801 TASK 32−22−01−980−802 TASK 32−22−10−830−801 DESIGNATION Hydraulic Safety Precautions Bleed Hydraulic System No. 3 External Leak Check of the Landing Gear Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors Adjustment of the NLG Door Actuator and Mechanism Master EFFECTIVITY: See Pageblock 32−22−10 page 401 407 32−22−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 2. Job Set−Up Subtask 32−22−10−869−002 A. Make sure that the aircraft is in the same configuration as in the removal task. Subtask 32−22−10−910−003 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: B. Subtask 32−22−10−680−001 **ON A/C 7003−7067, 7069−7500, 7522, 7524 Refer to Figure 401. **ON A/C 7501−7521, 7523, 7525−7990, 8000−8064, 8066−8068 Refer to Figure 402. **ON A/C ALL C. Put the NLG door actuator (1) in position over a suitable hydraulic fluid resistant container and remove the protective caps from the fittings in its extension and retraction ports. D. Slowly extend and retract the actuator rod to allow any hydraulic fluid that remains in the NLG door actuator (1) to drain from the fittings in its extension and retraction ports. 3. Procedure − Part 1 **ON A/C 7003−7067, 7069−7500, 7522, 7524 Subtask 32−22−10−420−001 Refer to Figure 401. A. Install the NLG door actuator (1) as follows: (1) Put the bottom of the NLG door actuator (1) in position between the lugs of the rocking lever at the bottom of the right door−operating mechanism. (2) Insert the bushings (5) through the lugs of the rocking lever and in to the NLG door actuator (1). NOTE: To make the future removal of the bushings easier, insert the bushings so that the small holes in the bushings will be visible when the bushings are installed (away from the center line of the NLG door actuator (1)). (3) At the bottom end of the NLG door actuator (1), align the related attachment holes in the NLG door actuator (1) and the rocking lever. (4) Install the bolt (4) that attaches the door NLG actuator (1) to the rocking lever. (5) Install the nut (3) on the bolt (4). (6) Safety the nut (3) with the cotter pin (2). Master EFFECTIVITY: See Pageblock 32−22−10 page 401 408 32−22−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (7) Retract or extend the fork−end of the actuator rod manually to align it with the upper lever assembly of the right door−operating mechanism. (8) Temporarily secure the fork−end of the NLG door actuator (1) to the upper lever assembly with the bolt (10). Do not install the two washers (9), the washer (8), the nut (7), or the cotter pin (6) at this time. They will be installed at a later step. **ON A/C 7501−7521, 7523, 7525−7990, 8000−8064, 8066−8068 Subtask 32−22−10−420−002 Refer to Figure 402. B. Install the NLG door actuator (1) as follows: (1) Hold a Teflon washer (11) in position on each side of the bearing on the bottom of the NLG door actuator (1). (2) Put the bottom of the NLG door actuator (1) and the Teflon washers (11) in position between the lugs of the rocking lever at the bottom of the right door−operating mechanism. (3) Insert the bushings (5) through the lugs of the rocking lever and in to the NLG door actuator (1). NOTE: To make the future removal of the bushings easier, insert the bushings so that the small holes in the bushings will be visible when the bushings are installed (away from the center line of the NLG door actuator (1)). (4) At the bottom end of the NLG door actuator (1), align the related attachment holes in the NLG door actuator (1), the Teflon washers (11), and the rocking lever. (5) Install the bolt (4) that attaches the NLG door actuator (1) to the rocking lever. (6) Install the nut (3) on the bolt (4). (7) Safety the nut (3) with the cotter pin (2). (8) Retract or extend the fork−end of the actuator rod manually to align it with the upper lever assembly of the right door−operating mechanism. (9) Temporarily secure the fork−end of the NLG door actuator (1) to the upper lever assembly with the bolt (10). Do not install the two washers (9), the washer (8), the nut (7), or the cotter pin (6) at this time. They will be installed at a later step. **ON A/C ALL Subtask 32−22−10−820−004 C. If any other component was removed from the right door−operating mechanism, do the adjustment procedure for the door actuator and mechanism only (Ref. TASK 32−22−10−830−801). NOTE: The adjustment procedure contains the steps needed to complete the installation procedure. If only the NLG door actuator was removed, do the Part 2. Master EFFECTIVITY: See Pageblock 32−22−10 page 401 409 32−22−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 4. Procedure − Part 2 Subtask 32−22−10−010−003 Refer to Figure 403. A. To get access to the work area, disconnect the fork−end of the right door−operating rod from the upper lever assembly of the right door−operating mechanism as follows: (1) At the top end of the right door−operating rod, remove and discard the cotter pin (12). (2) Remove the nut (13), the washer (14), and the bolt (15) from the right door−operating rod and the upper lever assembly. (3) Disconnect the right door−operating rod from the upper lever assembly. (4) Rotate the right door−operating rod down to make sure that it is away from any components that will move when the door mechanism operates. Subtask 32−22−10−840−001 **ON A/C 7003−7067, 7069−7500, 7522, 7524 Refer to Figure 401. **ON A/C 7501−7521, 7523, 7525−7990, 8000−8064, 8066−8068 Refer to Figure 402. **ON A/C ALL B. Do the steps that follow to prepare the NLG door actuator (1) for adjustment: (1) If installed, remove and discard the lockwire from the jam nuts at the actuator rod end. (2) Loosen the jam nuts at the actuator rod end. (3) Remove the bolt (10) that was temporarily installed in Part 1 of the procedure. (4) Manually move the upper lever assembly and the locking lever so that the roller engages the cam in the door closed and locked position. NOTE: The left door−operating mechanism will also operate and the left NLG door will close. (5) With the door operating mechanism closed and locked, install the rig pin P1. C. Do the steps that follow to adjust the travel of the NLG door actuator (1) in the closed position: (1) Fully extend the NLG door actuator (1) manually until the actuator rod is completely extended. (2) Make sure that the rocking lever at the bottom of the NLG door actuator (1) is fully against its stop surface on the right door−operating mechanism. (3) Adjust the fork−end of the actuator rod until it is aligned with the upper lever assembly and you can install and remove the bolt (10) easily. (4) Extend the fork−end of the actuator rod an additional half turn to increase the length of the actuator rod. NOTE: This adjustment prevents the actuator rod from bottoming by approximately 0.020 inch (0.51 mm) when the NLG forward doors are operated. Master EFFECTIVITY: See Pageblock 32−22−10 page 401 410 32−22−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (5) Temporarily install the bolt (10) again at the fork−end of the actuator rod. (6) Tighten the jam nuts at the fork−end of the actuator rod. (7) Remove the rig pin P1. Subtask 32−22−10−820−005 Refer to Figure 404. D. Do an adjustment of the NLG door actuator (1) in the open position as follows: (1) Remove and discard the lockwire from the jam nut (16) on the stop bolt (17). (2) Loosen the jam nut (16) and adjust the stop bolt (17) to make sure that there will be clearance between the stop bolt (17) and the rocking lever at the bottom of the NLG door actuator (1) when the rig pin P2 is installed. (3) Remove the bolt (10) that was temporarily installed at the fork−end of the actuator rod. (4) Manually retract the NLG door actuator (1) until the actuator rod is completely retracted. (5) Manually operate the manual release lever and check that the roller freely disengages from the cam. At the same time, rotate the upper lever assembly down so that the door operating mechanism is in the open position. (6) Make sure that you can install the rig pin P2 easily when the stop bolt (19) touches the upper lever assembly. If the rig pin P2 cannot be inserted easily, (or the stop bolt (19) does not touch the upper lever assembly when the rig pin P2 is inserted), do the steps that follow: NOTE: If the rig pin P2 can be installed easily when the stop bolt (19) touches the upper lever assembly, go to the next step. (a) Temporarily remove the rig pin P2. (b) Remove and discard the lockwire from the jam nut (18) on the stop bolt (19). (c) Loosen the jam nut (18) and adjust the stop bolt (19) to make sure that the rig pin P2 can be installed easily when the stop bolt (19) touches the upper lever assembly. (d) Tighten the jam nut (18). (e) Safety the jam nut (18) with 05−004 lockwire. (f) Install the rig pin P2 again. Make sure that it can be inserted easily. (7) With the actuator rod completely retracted, make sure that: ± the bolt (10) can be installed at the upper lever assembly easily ± the stop bolt (17) does not touch the rocking lever at the bottom of the NLG door actuator (1) with the bolt (10) installed. (8) Adjust the stop bolt (17) until it just touches the rocking lever at the bottom of the NLG door actuator (1), with the actuator rod completely retracted. (9) Extend the stop bolt (17) an additional 0.020−0.040 inch (0.51−1.02 mm). NOTE: This adjustment prevents the actuator piston from bottoming when the NLG forward doors are operated. (10) Tighten the jam nut (16). Master EFFECTIVITY: See Pageblock 32−22−10 page 401 411 32−22−10 SepPage 10/2004 C AIRCRAFT MAINTENANCE MANUAL (11) Safety the jam nut (16) with 05−004 lockwire. Subtask 32−22−10−430−001 **ON A/C 7003−7067, 7069−7500, 7522, 7524 Refer to Figure 401. **ON A/C 7501−7521, 7523, 7525−7990, 8000−8064, 8066−8068 Refer to Figure 402. **ON A/C ALL E. Do the steps that follow to complete the installation of the NLG door actuator (1): (1) Remove the temporarily installed bolt (10) from the fork−end of the NLG door actuator (1) and the upper lever assembly. (2) Insert the two washers (9) between the fork−end of the actuator rod and the upper lever assembly. NOTE: The two washers (9) are installed on each side of the bearing in the upper lever assembly; between the upper lever assembly and the fork−end of the NLG door actuator (1). (3) Connect the fork−end of the NLG door actuator (1), the washers (9), and the upper lever assembly together again with the bolt (10). (4) Install the washer (8), and the nut (7) on the bolt (10). (5) Safety the nut (10) with the cotter pin (6). (6) Remove the protective plugs from the hydraulic lines. (7) Connect the hydraulic lines to the fittings in the extension and the retraction ports on the NLG door actuator (1). (8) Remove the rig pin P2. Subtask 32−22−10−410−001 Refer to Figure 403. F. Connect the right door−operating rod to the upper lever assembly of the right door−operating mechanism as follows: (1) Rotate the right door−operating rod up (that is attached to the NLG door) and attach it to the upper lever assembly with the bolt (15). Make sure that the head of the bolt (15) is adjacent to the aft side of the fork−end on the right door−operating rod. (2) Install the washer (14) and the nut (13) on the bolt (10). (3) Safety the nut (13) with the cotter pin (12). 5. Close Out Subtask 32−22−10−160−001 A. Clean all signs of hydraulic fluid from the actuator assembly and surrounding area. Master EFFECTIVITY: See Pageblock 32−22−10 page 401 412 32−22−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−10−941−001 B. Remove all tools, equipment, and unwanted materials from the work area. Subtask 32−22−10−865−002 C. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G10 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−22−10−870−001 WARNING: D. STAY AWAY FROM THE NOSE LANDING GEAR DOORS. IF THE DOORS ARE OPEN WHEN HYDRAULIC PRESSURE IS APPLIED TO HYDRAULIC SYSTEM NO. 3, THE DOORS WILL CLOSE. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Close the NLG forward doors (Ref. TASK 32−22−01−980−802). Subtask 32−22−10−870−003 E. Bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−22−10−790−001 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the NLG forward doors (Ref. TASK 32−22−01−980−801). Do an inspection of the door actuator assembly and hydraulic connections for leaks (Ref. TASK 32−00−00−790−801). Close the NLG forward doors (Ref. TASK 32−22−01−980−802). WARNING: F. G. H. Master EFFECTIVITY: See Pageblock 32−22−10 page 401 32−22−10 Page 413 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL FS202.75 FS235.00 RIGHT DOOR− OPERATING MECHANISM (REF) A UPPER LEVER ASSEMBLY (REF) NLG FORWARD DOOR (REF) NOTE 1 12 Make sure that the head of the bolt (15) is adjacent to the aft side of the operating rod fork−end. 14 13 RIGHT DOOR− OPERATING ROD (REF) LEGEND 12. Cotter pin. 13. Nut. 14. Washer. 15. Bolt. A MECHANISM IN THE OPEN POSITION ram3222104_002 .dg, cr/rm, 29/03/01 15 1 NLG Door Actuator − Access Details Figure 403 Master EFFECTIVITY: See Pageblock 32−22−10 page 401 32−22−10 Page 414 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND FS202.75 16. Jam nut. 17. Stop bolt. 18. Jam nut. 19. Stop bolt. A FS235.00 MANUAL RELEASE LEVER (REF) UPPER LEVER ASSEMBLY (REF) ROLLER (REF) CAM (REF) MANUAL RELEASE LEVER (REF) A VIEW LOOKING OUTBOARD UPPER LEVER ASSEMBLY 18 19 (REF) 17 ROCKING LEVER (REF) WITH RIG PIN P2 INSTALLED WITH RIG PIN P2 INSTALLED ram3222104_003.dg, rm, 29/03/01 16 NLG Door Actuator − Basic Adjustment Figure 404 Master EFFECTIVITY: See Pageblock 32−22−10 page 401 32−22−10 Page 415 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL DOOR ACTUATOR, NOSE LANDING GEAR − ADJUSTMENT/TEST 1. General A. The maintenance procedures that follow are for the adjustment of the nose−landing−gear (NLG) forward−door actuator and its related door mechanism assembly. The NLG door actuator and the operating mechanism for the right−forward NLG door is installed on the right side of the nosewheel well. TASK 32−22−10−830−801 Adjustment of the NLG Door Actuator and Mechanism 1. Job Set−Up Information Subtask 32−22−10−943−002 A. Tools and Equipment REFERENCE G601R270001−1 None specified None specified None specified None specified DESIGNATION Kit, rigging pin Container, fluid Force gauge − 0−50 pounds (222 N) Torque wrench, torque range 0−150 pound−inches (0−16.95 N·m) Weight, 20 pounds (9.1 kg) Subtask 32−22−10−944−001 B. Consumable Materials REFERENCE 05−004 DESIGNATION Lockwire Subtask 32−22−10−945−002 C. Parts REF 1 2 3 4 5 6 7 8 9 NAME OF PART Cotter pin Nut Washer Bolt Cotter pin Nut Washer Bolt Washer Master EFFECTIVITY: See Pageblock 32−22−10 page 501 QTY 2 2 2 2 1 1 1 1 2 IPC SEQUENCE NO. IPC 32−22−00−02−035 IPC 32−22−00−02−030 IPC 32−22−00−02−020 IPC 32−22−00−02−015 IPC 32−22−00−03−175 IPC 32−22−00−03−170 IPC 32−22−00−03−160 IPC 32−22−00−03−155 IPC 32−22−00−03−165 32−22−10 Page 501 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REF 10 11 13 14 15 16 17 19 20 21 22 23 24 25 26 27 28 NAME OF PART Stop bolt Jam nut Jam nut Cotter pin Nut Washer Bolt Nut Keywasher Jam nut Stop bolt Jam nut Stop bolt Nut Nut Keywasher Washer, internal tooth QTY 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−22−00−03−423 IPC 32−22−00−03−430 IPC 32−22−00−03−055 IPC 32−22−00−03−035 IPC 32−22−00−03−030 IPC 32−22−00−03−020 IPC 32−22−00−03−010 IPC 32−61−05−03−030 IPC 32−61−05−03−025 IPC 32−22−00−03−430 IPC 32−22−00−03−423 IPC 32−22−00−03−430 IPC 32−22−00−03−425 IPC 32−61−15−01−012 Subtask 32−22−10−946−003 D. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 29−00−00−910−801 TASK 29−10−00−870−803 TASK 32−00−00−790−801 TASK 32−22−01−720−801 TASK 32−22−01−980−801 TASK 32−22−01−980−802 TASK 32−30−00−720−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Hydraulic Safety Precautions Bleed Hydraulic System No. 3 External Leak Check of the Landing Gear Functional Test of the Forward Doors of the Nose Landing Gear Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors Functional Test of the Landing Gear Extension/Retraction System Master EFFECTIVITY: See Pageblock 32−22−10 page 501 32−22−10 Page 502 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 2. Job Set−Up Subtask 32−22−10−490−002 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. Subtask 32−22−10−910−002 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: B. Subtask 32−22−10−010−002 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the NLG forward doors (Ref. TASK 32−22−01−980−801). WARNING: C. 3. Procedure Subtask 32−22−10−030−002 Refer to Figure 501. A. Put a fluid container in position below the NLG door actuator. B. Disconnect the hydraulic lines at the extend and retract ports of the NLG door actuator. Make sure that any hydraulic fluid in the actuator is allowed to drain from the ports. (1) Install protective caps on the open hydraulic lines. Master EFFECTIVITY: See Pageblock 32−22−10 page 501 32−22−10 Page 503 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−10−030−003 C. D. To get access to the work area, disconnect the fork−end of the door operating rod from the upper lever assembly of the right−door operating mechanism as follows: (1) At the top end of the door operating rod, remove and discard the cotter pin (1). (2) Remove the nut (2), the washer (3), and the bolt (4) from the door operating rod and the upper lever assembly. (3) Disconnect the door operating rod from the upper lever assembly. (4) Rotate the door operating rod down to make sure that it is away from any components that will move when the door mechanism operates. To isolate the right−door operating mechanism from the−left door operating mechanism, do the steps that follow: (1) Manually move the upper lever assembly and the locking lever so that the roller engages the cam in the door closed and locked position. (2) At the fork−end of the connecting rod between the right−door operating mechanism and the left−door operating mechanism, remove and discard the cotter pin (1). (3) Remove the nut (2), the washer (3), and the bolt (4) to disconnect the fork−end of the connecting rod from the upper lever assembly of the right−door operating mechanism. (4) Disconnect the connecting rod from the upper lever assembly. (5) Rotate the connecting rod down to make sure that it is away from any components that will move when the right−door operating mechanism operates. (6) Manually operate the manual release lever and check that the roller freely disengages from the cam. At the same time, rotate the upper lever assembly down so that the door operating mechanism is in the open position. Subtask 32−22−10−865−003 E. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. G11 A2 G15 A2 NAME HYD SYST AC PUMP CONT 3B HYD PUMP 3B HYD SYST AC PUMP CONT 3A HYD PUMP 3A ZONE 221 221 222 222 Subtask 32−22−10−820−002 F. Do an adjustment of the NLG door actuator and the door operating mechanism in the closed position as follows: (1) Remove and discard the lockwire from the jam nuts at the actuator rod end. (2) Loosen the jam nuts at the actuator rod end. (3) Disconnect the NLG door actuator from the door operating mechanism as follows: (a) At the top end of the NLG door actuator, remove and discard the cotter pin (5). Master EFFECTIVITY: See Pageblock 32−22−10 page 501 32−22−10 Page 504 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (4) (5) (6) (7) (8) (9) (b) Remove the nut (6), the washer (7), the bolt (8), and the washers (9). NOTE: The washers (9) are installed adjacent to the bearing in the upper lever assembly on each side of the fork−end of the NLG door actuator. Manually move the upper lever assembly and the locking lever so that the roller engages the cam in the door closed and locked position. With the roller engaged on the cam, check that the clearance between the upper lever assembly and the stop bolt (10) is 0.010 to 0.020 inch (0.25 to 0.51 mm). If the clearance is not correct, do the steps that follow: (a) Remove and discard the lockwire from the jam nut (11) on the stop bolt (10). (b) Loosen the jam nut (11) and adjust the stop bolt (10) to get the specified clearance. (c) Tighten the jam nut (11). (d) Safety the jam nut (11) with 05−004 lockwire. Manually operate the release lever and check that the roller freely disengages from the cam. Release the release lever and check that the roller engages the cam and locks the door operating mechanism. With the door operating mechanism closed and locked, make sure that the rigging pin P1 can be installed and removed easily. Do the steps that follow to adjust the travel of the NLG door actuator. (a) Fully extend the NLG door actuator manually until the actuator piston rod is completely extended. (b) Make sure that the rocking lever at the bottom of the NLG door actuator is fully against its stop surface on the door operating mechanism. (c) Adjust and align the rod end of the NLG door actuator with the upper lever assembly as required until you can install and remove the bolt (8) easily. (d) Extend the rod end of the NLG door actuator an additional half turn to increase the length of the actuator piston rod. NOTE: This adjustment prevents the actuator piston rod from bottoming by approximately 0.020 inch (0.51 mm) when the NLG forward doors are operated. (e) Temporarily install the bolt (8) at the actuator rod end. (f) Tighten the jam nuts at the actuator rod end. With the roller engaged on the cam, (the door operating mechanism closed and locked) check that there is a clearance of 0.040 to 0.060 inch (1.02 to 1.53 mm) between the bottom of the slot in the slotted rod and the bushings on the bolt (12) in the locking lever. If the clearance is not correct, do the steps that follow: (a) At the bottom of the slotted rod, remove and discard the lockwire from the jam nut (13) on the rod end of the slotted rod. (b) Loosen the jam nut (13) sufficiently to disengage the lock on the rod end of the slotted rod. (c) Remove and discard the cotter pin (14) from the nut (15). Master EFFECTIVITY: See Pageblock 32−22−10 page 501 32−22−10 Page 505 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (d) (e) (f) (g) (h) (i) (j) Remove the nut (15), the washer (16), and the bolt (17). Adjust the rod end of the slotted rod to get the specified clearance. Install the bolt (17), the washer (16), and the nut (15). Engage the lock on the rod end in the slotted rod. Tighten the jam nut (13). Install the cotter pin (14). Safety the jam nut (13) with 05−004 lockwire. Subtask 32−22−10−220−001 G. Check the clearance between the PS17GA proximity sensor and its target. Make sure that the sensor−to−target clearance is 0.040− 0.050 inch (1.02−1.27 mm). If you do not get the specified clearance, do the steps that follow: (1) Remove and discard the lockwire from the nuts (18) and (19) on the PS17GA proximity sensor. (2) Adjust the nuts (18) and (19) as required on the PS17GA proximity sensor until you get the specified clearance. Make sure that the tab on the keywasher (20) engages the hole in the proximity sensor bracket correctly. NOTE: Each turn of the nuts (18) and (19) changes the sensor−to−target clearance by 0.042 inch (1.07 mm). (3) Tighten the nuts (18) and (19). (4) Torque the nuts (18) and (19) to 110−120 pound inches (12.43−13.56 N·m). Subtask 32−22−10−820−003 Refer to Figure 501. H. Do an adjustment of the NLG door actuator and the door operating mechanism in the open position as follows: (1) Remove and discard the lockwire from the jam nut (21) on the stop bolt (22). (2) Remove and discard the lockwire from the jam nut (23) on the stop bolt (24). (3) Loosen the jam nut (21) and adjust the stop bolt (22) to make sure that there will be clearance between the stop bolt (22) and the rocking lever at the bottom of the NLG door actuator when the upper lever assembly is rotated down. (4) Loosen the jam nut (23) and adjust the stop bolt (24) to make sure that there will be clearance between the stop bolt (24) and the upper lever assembly when the upper lever assembly is rotated down. (5) Remove the bolt (8) that was temporarily installed at the actuator rod end. (6) Fully retract the NLG door actuator manually until the actuator piston rod is completely retracted. (7) Manually operate the manual release lever and check that the roller freely disengages from the cam. At the same time, rotate the upper lever assembly down so that the door operating mechanism is in the open position. (8) Install the rig pin P2. (9) With the actuator piston rod completely retracted, make sure that the bolt (8) can be installed at the upper lever assembly easily. Master EFFECTIVITY: See Pageblock 32−22−10 page 501 32−22−10 Page 506 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (10) Adjust the stop bolt (22) until it just touches the rocking lever at the bottom of the NLG door actuator. (11) Extend the stop bolt (22) an additional 0.020−0.040 inch (0.51−1.02 mm). NOTE: This adjustment prevents the actuator piston rod from bottoming when the NLG forward doors are operated. (12) Tighten the jam nut (21). (13) Remove the temporarily installed bolt (8) from the fork−end of the actuator and the upper lever assembly. (14) Connect the fork−end of the actuator and the upper lever assembly again with the bolt (8) and the two washers (9). NOTE: The washers (9) are installed adjacent to the bearing in the upper lever assembly on each side of the fork−end of the NLG door actuator. (15) Install the washer (7), and the nut (6) on the bolt (8). (16) Safety the nut (6) with the cotter pin (5). (17) Adjust the stop bolt (24) until it just touches the upper lever assembly. Tighten the jam nut (23). (18) Safety the jam nuts (21) and (23) with 05−004 lockwire. Subtask 32−22−10−220−002 I. With the door operating mechanism still in the open position, adjust the S1GA microswitch as follows: (1) Remove and discard the lockwire from the nuts (25) and (26) on the S1GA microswitch. (2) Turn the nuts (25) and (26) clockwise as required on the S1GA microswitch until the S1GA microswitch does not contact the upper lever assembly. (3) Loosely tighten the nut (25). NOTE: Make sure that the tab on the keywasher (27) engages the hole in the top of the door operating mechanism correctly when the nut (25) is tightened. (4) Alternately loosen the nut (25) and tighten the nut (26) to move the S1GA microswitch until it contacts the upper lever assembly lightly. NOTE: There is an internal tooth washer (28) under the adjusting nut (26). (5) Continue to alternately loosen the nut (25) and tighten the nut (26) a total of 3.25 turns to move the S1GA microswitch towards the upper lever assembly. NOTE: It is possible that you will not be able to adjust the nuts (25) and (26) the amount specified. If this happens, adjust the nuts (25) and (26) to the maximum amount possible. NOTE: Each turn of the nuts (25) and (26) changes the microswitch−to−lever clearance by 0.031 inch (0.79 mm). NOTE: 3.25 turns of the nuts (25) and (26) is equivalent to 0.101 inch (2.56 mm). This dimension is a combination of 0.040 inch (1.01 mm) microswitch pre−travel and also 0.061 inch (1.55 mm) microswitch over−travel. Master EFFECTIVITY: See Pageblock 32−22−10 page 501 32−22−10 Page 507 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (6) Tighten the nut (26). Do not let the nut (25) turn when you do this step. NOTE: Tighten only the nut (26). Do not move the nut (25) or you will change the over travel adjustment of the microswitch. (7) Check that the over travel of the S1GA microswitch is at least 0.060 inch (1.53 mm). (8) Tighten the nuts (25) and (26). (9) Torque the nut (26) to 110−120 pound inches (12.43−13.56 N·m). (10) Safety the nuts (25) and (26) with 05−004 lockwire. (11) Remove the rig pin P2. Subtask 32−22−10−720−002 J. Do a functional test of the NLG door operating mechanism as follows: (1) Manually move the upper lever assembly and the locking lever so that the roller engages the cam in the door closed and locked position. (2) Attach a suitable weight of 20 pounds (9.1 kg) to the upper lever assembly (were the NLG door operating rod was attached). Use a force gauge to apply a load to the manual release lever (in line with the pulley on the door operating mechanism) and unlock the door operating mechanism. (3) Make sure that the force required to unlock the door operating mechanism (at the manual release lever) is not more than 50 pounds (222 N). (4) Manually move the upper lever assembly and the locking lever again so that the roller engages the cam in the door closed and locked position. Subtask 32−22−10−430−003 K. L. To connect the right−door operating mechanism to the−left door operating mechanism, do the steps that follow: (1) Rotate the connecting rod up and attach it to the upper lever assembly with the bolt (4), the washer (3), and the nut (2). Make sure that the head of the bolt (4) is adjacent to the aft side of the fork−end on the connecting rod. (2) Install the cotter pin (1). Connect the door operating rod to the upper lever assembly of the door operating mechanism as follows: (1) Manually operate the manual release lever and check that the roller freely disengages from the cam. At the same time, rotate the upper lever assembly down so that the door operating mechanism is in the open position. (2) Rotate the door operating rod up and attach it to the upper lever assembly with the bolt (4), the washer (3), and the nut (2). Make sure that the head of the bolt (4) is adjacent to the aft side of the fork−end on the door operating rod. (3) Install the cotter pin (1). Master EFFECTIVITY: See Pageblock 32−22−10 page 501 32−22−10 Page 508 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−10−430−004 M. N. Remove the protective caps from the hydraulic lines. Connect the hydraulic lines at the extend and retract ports of the NLG door actuator. 4. Close Out Subtask 32−22−10−865−004 A. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G10 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−22−10−870−002 WARNING: B. STAY AWAY FROM THE NOSE LANDING GEAR DOORS. IF THE DOORS ARE OPEN WHEN HYDRAULIC PRESSURE IS APPLIED TO HYDRAULIC SYSTEM NO. 3, THE DOORS WILL CLOSE. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Close the NLG forward doors (Ref. TASK 32−22−01−980−801) and then bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−22−10−720−003 C. D. Do a functional test of the operating mechanism of the NLG forward doors (Ref. TASK 32−22−01−720−801). Do a functional test of the landing gear extension retraction system (Ref. TASK 32−30−00−720−801). Master EFFECTIVITY: See Pageblock 32−22−10 page 501 32−22−10 Page 509 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−10−790−002 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the NLG forward doors (Ref. TASK 32−22−01−980−801). Do an inspection of the actuator assembly and the hydraulic connections for leaks (Ref. TASK 32−00−00−790−801). Close the NLG forward doors (Ref. TASK 32−22−01−980−802). WARNING: E. F. G. Subtask 32−22−10−941−002 H. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−22−10 page 501 32−22−10 Page 510 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL UPPER LEVER ASSEMBLY (REF) FS202.75 A FS235.00 1 3 4 2 1 6 7 3 2 DOOR OPERATING ROD (REF) 5 8 4 LEGEND 1. Cotter pin. 2. Nut. 3. Washer. 4. Bolt. 5. Cotter pin. 6. Nut. 7. Washer. 8. Bolt. 9. Washer. CONNECTING ROD (REF) ACTUATOR PISTON ROD (REF) 9 JAM NUTS (REF) B C PULLEY (REF) E C RIG PIN P1 L UPPER LEVER ASSEMBLY (REF) K B MANUAL RELEASE (REF) 20 POUND LOAD RIG PIN P2 LOCKING LEVER (REF) K L D H J NLG DOOR ACTUATOR (REF) ROCKING LEVER (REF) A D VIEW LOOKING AFT VIEW LOOKING OUTBOARD E ram3222105_001(1).dc, rm, 25/03/97 SLOTTED ROD (REF) Adjustment of the NLG Door Actuator and Mechanism Figure 501 (Sheet 1 of 3) Master EFFECTIVITY: See Pageblock 32−22−10 page 501 32−22−10 Page 511 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND 10. Stop bolt. 11. Jam nut. 12. Bolt. 13. Jam nut. 14. Cotter pin. 15. Nut. 16. Washer. 17. Bolt. 18. Adjusting nut. 19. Adjusting nut. 20. Keywasher. 0.040−0.060 in. (1.02−1.53 mm) 0.010−0.020 in. (0.25−0.51 mm) 11 UPPER LEVER ASSEMBLY (REF) 10 BUSHING (REF) F BOLT (12) REMOVED FOR CLARITY CAM (REF) F SLOTTED ROD (REF) MANUAL RELEASE LEVER (REF) 13 ROD END (REF) 12 16 15 14 17 LOCKING LEVER (REF) G 0.040 in−0.050 in. (1.02−1.27 mm) 18 SLOTTED ROD (REF) 20 19 G E − E H PS17GA PROXIMITY SENSOR (REF) ram3222105_002.dg, rm, 31/03/97 ROLLER (REF) Adjustment of the NLG Door Actuator and Mechanism Figure 501 (Sheet 2 of 3) Master EFFECTIVITY: See Pageblock 32−22−10 page 501 32−22−10 Page 512 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL UPPER LEVER ASSEMBLY 24 (REF) 23 21 22 J ROCKING LEVER (REF) WITH RIG PIN P2 INSTALLED K − K WITH RIG PIN P2 INSTALLED S1GA MICROSWITCH (REF) LEGEND 21. Jam nut. 22. Stop bolt. 23. Jam nut. 24. Stop bolt. 25. Adjusting nut. 26. Adjusting nut. 27. Keywasher. 28. Internal tooth washer. M 25 27 M ram3222105_003.dg, rm, 31/03/97 UPPER LEVER ASSEMBLY (REF) 32−22−10 Page 513 Apr 20/2004 28 26 L − L Adjustment of the NLG Door Actuator and Mechanism Figure 501 (Sheet 3 of 3) Master EFFECTIVITY: See Pageblock 32−22−10 page 501 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL DOOR MECHANISM ASSEMBLY − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the door mechanism assembly. The door mechanism assembly is installed in the nosewheel well. B. The door mechanism assembly is an assembly of the components that follow: ± a right door−operating mechanism ± a left door−operating mechanism ± an interconnect rod for the door operating mechanisms (written as the ‘center control rod’ in this procedure) ± right and left door operating rods (written as the ‘right and left controls rods’ in this procedure) ± one proximity sensor and two microswitches. TASK 32−22−15−000−801 Removal of the Door Mechanism Assembly 1. Job Set−Up Information Subtask 32−22−15−946−001 A. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 29−00−00−910−801 TASK 32−22−01−980−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Hydraulic Safety Precautions Open and Isolate the Nose−Landing−Gear Forward Doors 2. Job Set−Up Subtask 32−22−15−910−002 WARNING: A. OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). Master EFFECTIVITY: See Pageblock 32−22−15 page 401 32−22−15 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−15−010−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. B. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. C. Open and isolate the NLG forward doors (Ref. TASK 32−22−01−980−801). WARNING: 3. Procedure Subtask 32−22−15−020−001 Refer to Figure 401, Figure 402 and Figure 403. A. Remove the PS17GA proximity sensor (1), the S1GA microswitch (2), and the S2GA microswitch (3) as follows: (1) To remove the PS17GA proximity sensor (1) from the aft side of the right door−operating mechanism (22), do the steps that follow: (a) Remove and discard the lockwire from the nuts (4). (b) Loosen and remove the forward nut (4) (that is adjacent to the installation bracket). (c) Remove the PS17GA proximity sensor (1) (with the aft nut (4) and the keywasher (5)) from the right door−operating mechanism (22). (2) To remove the S1GA microswitch (2) from the top of the right door−operating mechanism (22), do the steps that follow: (a) Remove and discard the lockwire from the nuts (4). (b) Loosen and remove the lower nut (4) and the internal tooth washer (6) that are adjacent to the lower surface on the right door−operating mechanism (22). (c) Remove the S1GA microswitch (2) (with the upper nut (4) and the keywasher (5)) from the right door−operating mechanism (22). (3) To remove the S2GA microswitch (3) from the forward side of the left door−operating mechanism (41), do the steps that follow: Master EFFECTIVITY: See Pageblock 32−22−15 page 401 32−22−15 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (a) Remove the lockring (8) from the roller guide (7). (b) Turn the roller guide (7) clockwise (as viewed looking aft) to remove it from the S2GA microswitch. (c) Remove and discard the lockwire from the nuts (4). (d) Loosen and remove the aft nut (4) and the internal tooth washer (6) that are adjacent to the aft surface of the microswitch installation bracket that is attached to the left door−operating mechanism (41). (e) Remove the S2GA microswitch (3) (with the forward nut (4) and the keywasher (5)) from the microswitch installation bracket that is attached to the left door−operating mechanism (41). B. Prepare the right door−operating mechanism (22) and the left door−operating mechanism (41) for removal as follows: (1) From each end of the right control rod (11), remove and discard the cotter pins (12). (2) Remove the nuts (13), the washers (9), and the bolts (10). (3) Remove the right control rod (11). (4) From each end of the left control rod (33), remove and discard the cotter pins (29). (5) Remove the nuts (30), the washers (31), and the bolts (32). (6) Remove the left control rod (33). (7) From each end of the center control rod (16), remove and discard the cotter pins (12). (8) Remove the nuts (13), the washers (14), and the bolts (15). (9) Remove the center control rod (16). (10) Remove and discard the cotter pin (17) from the pin (19) that attaches the cable (21) to the manual release lever of the door operating mechanism (22). (11) Remove the washer (18) and the pin (19) to disconnect the cable (21). (12) Remove the pulley guard pins (20). C. Remove the spring pot assembly (38) from the left door−operating mechanism (41) as follows: NOTE: If you do not need to completely remove the spring pot assembly (38), remove only the components as required from the top or the bottom of the spring pot assembly (38). (1) From each end of the spring pot assembly (38), remove and discard the cotter pin (34). (2) Remove the nuts (35), the washers (36), and the bolts (37). (3) Remove the spring pot assembly (38). D. Remove the right door−operating mechanism (22) as follows: NOTE: Make a note of the location of each bolt and capscrew when you remove them. The fastener lengths are not the same. (1) Remove the capscrew (23) and the washer (27) from the door operating mechanism (22). (2) Remove the bolts (24) and (25) with the washers (27) from the door operating mechanism (22). Master EFFECTIVITY: See Pageblock 32−22−15 page 401 32−22−15 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL E. (3) Remove the bolts (26) and the washers (27) from the door operating mechanism (22) (three places). (4) Remove the door operating mechanism (22) and the washers (28). Remove the left door−operating mechanism (41) as follows: (1) Remove the bolts (39) with the washers (40) (four places) from the door operating mechanism (41). (2) Remove the door operating mechanism (41). Master EFFECTIVITY: See Pageblock 32−22−15 page 401 32−22−15 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL C A B LEGEND. 1. PS17GA harness assembly. 2. S1GA harness assembly. 3. S2GA harness assembly. 4. Nut. 5. Keywasher. 6. Internal tooth washer. 7. Roller guide. 8. Lock ring. 1 5 2 4 4 A 5 4 8 6 4 7 5 4 4 3 6 C ram3222154_001(2).dg, gg, 20/06/97 B Proximity Sensor and Microswitches − Disconnect Figure 401 Master EFFECTIVITY: See Pageblock 32−22−15 page 401 32−22−15 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND 9. Washer. 10. Bolt. 11. Right control rod. 12. Cotter pin. 13. Nut. 14. Washer. 15. Bolt. 16. Center control rod. 17. Cotter pin. 18. Washer. 20 19. Pin. 20. Pulley guard pin. 21. Cable. 22. Door operating mechanism. 23. Cap screw. 24. Bolt. 25. Bolt. 26. Bolt. 27. Washer. 28. Laminated washer. PULLEY (REF) 21 RIG PIN P1 19 18 17 MANUAL RELEASE LEVER 27 23 1 28 10 12 27 15 13 9 26 25 16 13 9 12 11 13 NOTE 12 1 10 14 The laminated washer (28) is cold bonded to the mounting base assembly (22) ( 6 locations) at initial installation. ram3222154_002(3).dc, rs/gg, 19/06/97 22 Door Operating Mechanism (Right) − Removal/Installation Figure 402 Master EFFECTIVITY: See Pageblock 32−22−15 page 401 32−22−15 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 39 13 40 14 41 15 12 16 RIG PIN P2 LEGEND. 35 36 37 38 31 32 29 33 30 37 34 36 12. Cotter pin. 13. Nut. 14. Washer. 15. Bolt. 16. Center control rod. 29. Cotter pin. 30. Nut. 31. Washer. 32. Bolt. 33. Left control rod. 34. Cotter pin. 35. Nut. 36. Washer. 37. Bolt. 38. Spring pot assembly. 39. Bolt. 40. Washer. 41. Door operating mechanism. 35 ram3222154_003(1).dc,rs/gg, 19/06/97 34 29 30 31 32 Door Operating Mechanism (Left) − Removal/Installation Figure 403 Master EFFECTIVITY: See Pageblock 32−22−15 page 401 32−22−15 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−22−15−400−801 Installation of the Door Mechanism Assembly 1. Job Set−Up Information Subtask 32−22−15−943−001 A. Tools and Equipment REFERENCE G601R None Specified None Specified DESIGNATION Kit, rigging pin Gauge, feeler Torque wrench, torque range 0−150 pound−inches (0−17 N·m) Subtask 32−22−15−944−001 B. Consumable Materials REFERENCE 05−004 DESIGNATION Lockwire Subtask 32−22−15−945−001 C. Parts REF 1 4 5 2 4 5 6 3 4 5 6 7 8 9 10 12 13 14 15 17 NAME OF PART PS17GA harness assembly Nut (for item 1) Keywasher (for item 1) S1GA harness assembly Nut Keywasher Washer, internal tooth S1GA harness assembly Nut Keywasher Washer, internal tooth Roller guide Lock ring Washer Bolt Cotter pin Nut Washer Bolt Cotter pin Master EFFECTIVITY: See Pageblock 32−22−15 page 401 QTY 1 2 1 1 2 1 1 1 2 1 1 1 1 2 2 4 4 2 2 1 IPC SEQUENCE NO. IPC 32−61−05−03−010 IPC 32−61−05−03−030 IPC 32−61−05−03−025 IPC 32−61−15−01−010 IPC 32−61−15−01−012 for item 2 IPC 32−61−15−01−040 IPC 32−61−15−01−042 for item 3 IPC 32−61−15−01−043 for item 3 IPC 32−22−00−02−020 IPC 32−22−00−02−015 IPC 32−22−00−02−035 IPC 32−22−00−02−030 IPC 32−22−00−02−025 IPC 32−22−00−02−015 IPC 32−22−00−02−165 32−22−15 Page 408 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REF 18 19 20 23 24 25 26 27 28 29 30 31 32 34 35 36 37 39 40 NAME OF PART Washer Pin Pulley guard pin Cap screw Bolt Bolt Bolt Washer Laminated washer Cotter pin Nut Washer Bolt Cotter pin Nut Washer Bolt Bolt Washer QTY 1 1 2 1 1 1 3 6 6 2 2 2 2 2 2 2 2 4 4 IPC SEQUENCE NO. IPC 32−22−00−02−160 IPC 32−22−00−02−155 IPC 32−22−00−03−105 IPC 32−22−00−02−385 IPC 32−22−00−02−379 IPC 32−22−00−02−381 IPC 32−22−00−02−380 IPC 32−22−00−02−390 IPC 32−22−00−02−400 IPC 32−22−00−02−035 IPC 32−22−00−02−030 IPC 32−22−00−02−020 IPC 32−22−00−02−015 IPC 32−22−00−02−245 IPC 32−22−00−02−240 IPC 32−22−00−02−235 IPC 32−22−00−02−225 IPC 32−22−00−02−325 IPC 32−22−00−02−330 Subtask 32−22−15−946−002 D. Reference Information REFERENCE TASK 32−22−01−980−801 TASK 32−22−01−980−802 TASK 32−22−10−830−801 TASK 32−22−01−830−802 TASK 32−61−00−740−801 TASK 51−23−00−390−803 DESIGNATION Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors Adjustment of the NLG Door Actuator and Mechanism Rigging of the Forward Doors of the Nose Landing Gear Power−Up Test of the PSS Mating Surface Sealant Procedure for Moderate Temperature Areas 2. Procedure Subtask 32−22−15−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Master EFFECTIVITY: See Pageblock 32−22−15 page 401 32−22−15 Page 409 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−15−420−001 Refer to Figure 402 and Figure 403. B. C. D. E. Prepare the right door−operating mechanism (22) for installation as follows: NOTE: If the door operating mechanism (22) to be installed is the one that was removed in the removal task, it will not be necessary to do this step. (1) Temporarily put the door operating mechanism (22) in position and measure the clearance between the door operating mechanism (22) and the aircraft structure at each attachment bolt location. (2) Remove the laminations from the laminated washers (28) (an amount equal to the measured clearance) and temporarily install the laminated washers (28) at each bolt location until the door operating mechanism (22) is flush with the fuselage structure. (3) Cold bond the laminated washers (28) to the door operating mechanism (22) (Ref. TASK 51−23−00−390−803). Install the right door−operating mechanism (22) as follows: (1) Align the right door−operating mechanism (22) with the fuselage installation holes. (2) Install the bolts (26) (three places) with the washers (27). (3) Install the bolts (25) and (24) with the washers (27). (4) Install the capscrew (23) with a washer (27). (5) Install the cable (21) on the pulley and install the pulley guard pins (20). (6) Align the fork end of the cable (21) with the manual release lever of the door operating mechanism (22) and install the pin (19), the washer (18), and the cotter pin (17). Temporarily install the PS17GA proximity sensor (1) in the right door−operating mechanism (22) as follows: NOTE: The PS17GA proximity sensor (1) will be adjusted at a later step. (1) Put the PS17GA proximity sensor (1) (with the aft nut (4) and the keywasher (5) installed) through the hole in the installation bracket and install the forward nut (4) until the threads of the lower nut (4) are completely engaged on the PS17GA proximity sensor (1). (2) Make sure that the tab on the keywasher (5) is correctly engaged in the hole in the installation bracket and then lightly tighten the aft nut (4). Temporarily install the S1GA microswitch (2) in the right door−operating mechanism (22) as follows: NOTE: The S1GA microswitch (2) will be adjusted at a later step. (1) Put the door operating mechanism (22) in the open position. (2) Put the S1GA microswitch (2) (with the upper nut (4) and the keywasher (5) installed) through the hole in the door operating mechanism (22) and install the internal tooth washer (6) and the lower nut (4) until the threads of the lower nut (4) are completely engaged on the S1GA microswitch (2). (3) Make sure that the tab on the keywasher (5) is correctly engaged in the hole in the Master EFFECTIVITY: See Pageblock 32−22−15 page 401 32−22−15 Page 410 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL F. G. H. I. top of the door operating mechanism (22) and then lightly tighten the upper nut (4). NOTE: Make sure that the S1GA microswitch (2) does not contact the upper lever assembly. Install the left door−operating mechanism (41) as follows: (1) Align the left door−operating mechanism (41) with the installation holes in the fuselage. (2) Install the bolts (39) with the washers (40). Install the spring pot assembly (38) on the left door−operating mechanism (41) as follows: NOTE: If the spring pot assembly (38) was not removed from the left door−operating mechanism (41), it will only be necessary to attach the spring pot assembly (38) at the bottom end. (1) Put the spring pot assembly (38) in position with the forked end on the bottom fitting if necessary. (2) At each end of the spring pot assembly (38), install the bolt (37), the washer (36), and the nut (35) as necessary. (3) Safety each nut (35) and bolt (37) with the cotter pin (34). Temporarily install the S2GA microswitch (3) on the left door−operating mechanism (41) as follows: NOTE: The S2GA microswitch (3) will be adjusted at a later step. (1) Put the S2GA microswitch (3) (with the forward nut (4) and the keywasher (5) installed) through the hole in the installation bracket and install the internal tooth washer (6) and the aft nut (4) until the threads of the aft nut (4) are completely engaged on the S2GA microswitch (3). (2) Loosely tighten the forward nut (4). NOTE: Make sure that the tab on the keywasher (5) engages the hole in the installation bracket correctly when the forward nut (4) is tightened. (3) Install the roller guide (7). Install the center control rod (16) as follows: (1) Manually move the right door−operating mechanism to the closed position. Make sure that the roller on the locking lever engages the cam in the ‘door closed and locked’ position. (2) Install the rig pin P1 through the upper lever assembly in the right door−operating mechanism. (3) Put the center control rod (16) in position with its forked end on the right side of the wheel well. (4) Attach the center control rod (16) to the upper lever assembly of the right door−operating mechanism with the bolt (15), the washer (14), and the nut (13). (5) Safety the nut (13) and bolt (15) with the cotter pin (12). (6) Manually move the upper lever assembly of the left door−operating mechanism to the closed position. (7) Install the rig pin P2 through the upper lever assembly in the left door−operating mechanism. Master EFFECTIVITY: See Pageblock 32−22−15 page 401 32−22−15 Page 411 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (8) At the adjustable end of the center control rod (16), install the bolt (15), the washer (14), and the nut (13). NOTE: Make sure that the rig pins P1 and P2 can be inserted and removed easily when the bolts (15) are installed. It is possible that an adjustment of the adjustable end of the center control rod (16) will be required. (9) Safety the nut (13) and bolt (15) with the cotter pin (12). (10) Remove the rig pin P1 from the right door−operating mechanism (22). (11) Remove the rig pin P2 from the left door−operating mechanism (41). (12) At the right door−operating mechanism, manually operate the manual release lever and, at the same time, rotate the upper lever assembly down so that both the right and the left door−operating mechanisms are in the open position. Subtask 32−22−15−820−002 J. Do an adjustment of the S2GA microswitch as follows: (1) Install the rig pin P2 in the left door−operating mechanism (41). (2) Alternately loosen the forward nut (4) and tighten the aft nut (4) to move the S2GA microswitch until it lightly contacts the upper lever assembly on the left door−operating mechanism (41). NOTE: As the S2GA microswitch is adjusted, make sure that the roller on the S2GA microswitch is aligned correctly to touch the upper lever assembly of the left door−operating mechanism (41) at 90 degrees. (3) Remove the rig pin P2 from the left door−operating mechanism (41). (4) Manually move the upper lever assembly of the right door−operating mechanism (22) so that the roller on the locking lever engages the cam in the ‘door closed and locked’ position. (5) Install the roller guide (7) and turn it until it is fully tightened on the S2GA microswitch. If necessary, loosen the roller guide (7) (within a half turn) to align the roller guide (7) on the S2GA microswitch such that the roller will touch the upper lever assembly of the left door−operating mechanism (41) at 90 degrees. (6) Install the lockring (8) on the roller guide (7). NOTE: You can rotate the roller guide (7) slightly, if required, to align the hole in the roller guide (7) with the slot in the S2GA microswitch to correctly install the lockring (8). (7) Manually move both of the door operating mechanisms to the open position. (8) Install the rig pin P2 in the left door−operating mechanism. (9) Continue to alternately loosen the aft nut (4) and tighten the forward nut (4) a total Master EFFECTIVITY: See Pageblock 32−22−15 page 401 32−22−15 Page 412 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (10) (11) (12) (13) (14) of 3.25 turns to move the S2GA microswitch towards the upper lever assembly. NOTE: It is possible that you will not be able to adjust the nuts (4) the amount specified. If this happens, adjust the nuts (4) to the maximum amount possible. NOTE: Each turn of the nuts (4) changes the S2GA microswitch−to−lever clearance by 0.031 inch (0.79 mm). NOTE: 3.25 turns of the nuts (4) is equivalent to 0.101 inch (2.56 mm). This dimension is a combination of 0.040 inch (1.01 mm) microswitch pre−travel and also 0.061 inch (1.55 mm) microswitch over−travel. Tighten the aft nut (4). Do not let the forward nut (4) turn when you do this step. NOTE: Tighten only the aft nut (4). Do not move the forward nut (4) or you will change the over travel adjustment of the S2GA microswitch. Remove the rig pin P2 from the left door−operating mechanism (41). Use a feeler guage to check that the over travel of the S2GA microswitch is a minimum of 0.060 inch (1.53 mm). Torque the aft nut (4) to 110−120 pound inches (12.43−13.56 N·m). Safety the nuts (4) together with 05−004 lockwire. Subtask 32−22−15−430−001 K. L. Install the right control rod (11) as follows: (1) Put the control rod (11) in position with the forked end at the top. (2) At the top end of the control rod (11), install the bolt (10), the washer (9), and the nut (8). Make sure that the head of the bolt (10) is adjacent to the aft side of the fork−end on the connecting rod (16). Safety the nut (8) and the bolt (10) with the cotter pin (7). (3) At the bottom end of the control rod (11), temporarily install the bolt (10), the washer (9), and the nut (8). NOTE: The control rod (11) wil be adjusted at a later step. Install the left control rod (33) as follows: (1) Put the control rod (33) in position with the forked end at the top. (2) At the top end of the control rod (33), install the bolt (32), the washer (31), and the nut (30). Make sure that the head of the bolt (15) is adjacent to the aft side of the fork−end on the connecting rod (16). Safety the nut (30) and the bolt (32) with the cotter pin (29). (3) At the bottom end of the control rod (33), temporarily install the bolt (32), the washer (31), and the nut (30). NOTE: The control rod (33) wil be adjusted at a later step. Master EFFECTIVITY: See Pageblock 32−22−15 page 401 32−22−15 Page 413 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. Close Out Subtask 32−22−15−830−001 A. Adjust the NLG door actuator and its related operating mechanism (22) on the right side (Ref. TASK 32−22−10−830−801). Subtask 32−22−15−820−001 B. Do the rigging of the forward doors (Ref. TASK 32−22−01−830−802). Subtask 32−22−15−865−002 C. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−22−15−941−001 D. Remove all tools, equipment, and unwanted materials from the work area. Subtask 32−22−15−410−001 E. Close the forward doors of the nose landing gear (Ref. TASK 32−22−01−980−802). Subtask 32−22−15−740−001 F. Do a power−up test of the proximity sensor system (Ref. TASK 32−61−00−740−801). Master EFFECTIVITY: See Pageblock 32−22−15 page 401 32−22−15 Page 414 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL VALVE, DOOR SELECTOR − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the door selector valve. The door selector valve is installed on the left side of the nosewheel well. TASK 32−22−20−000−801 Removal of the Door Selector Valve 1. Job Set−Up Information Subtask 32−22−20−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Container, hydraulic fluid Subtask 32−22−20−946−001 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 29−00−00−910−801 TASK 32−22−01−980−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Hydraulic Safety Precautions Open and Isolate the Nose−Landing−Gear Forward Doors 2. Job Set−Up Subtask 32−22−20−910−002 WARNING: A. OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all of the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). Subtask 32−22−20−010−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: B. Master EFFECTIVITY: See Pageblock 32−22−20 page 401 32−22−20 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−20−910−003 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the NLG forward doors (Ref. TASK 32−22−01−980−801). WARNING: C. 3. Procedure Subtask 32−22−20−020−001 Refer to Figure 401. A. Remove the door selector valve (8) as follows: (1) Put a fluid container below the work area. (2) Disconnect the electrical connector (1). Install protective caps on the electrical connector and the selector valve receptacle. (3) Disconnect the hydraulic lines (2), (3), (4), and (5). Install protective caps and plugs on all open hydraulic lines and valve ports. (4) Remove the nuts (6) and the bolts (7). (5) Remove the door selector valve (8). Subtask 32−22−20−030−002 B. If it is necessary to remove the fittings from the valve, do the steps that follow: (1) Remove the unions (9) and (10) and the preformed packings (11) and (12). Discard the preformed packings. (2) Remove the restrictor (13) and the preformed packing (14). Discard the preformed packing. (3) Remove the check valve (15) and the preformed packing (16). Discard the preformed packing. (4) Install plugs and caps on all open ports. Master EFFECTIVITY: See Pageblock 32−22−20 page 401 32−22−20 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND. 1. Electrical connector. 2. Hydraulic line. 3. Hydraulic line. 4. Hydraulic line. 5. Hydraulic line. 6. Bolt. 7. Nut. 8. Door Selector Valve. 9. Union. 10. Union. 11. Preformed packing. 12. Preformed packing. 13. Restrictor. 14. Preformed packing. 15. Check valve. 16. Preformed packing. 4 9 5 11 13 7 14 8 6 1 16 10 15 2 3 ram3222204_001.dc,AB,17/01/92 12 Door Selector Valve − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−22−20 page 401 32−22−20 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−22−20−400−801 Installation of the Door Selector Valve 1. Job Set−Up Information Subtask 32−22−20−944−001 A. Consumable Materials REFERENCE 02−001 DESIGNATION Hydraulic fluid, phosphate ester base Subtask 32−22−20−945−001 B. Parts REF 6 7 9 10 11 12 13 14 15 16 NAME OF PART Nut Bolt Union Union Preformed packing Preformed packing Restrictor Preformed packing Check valve Preformed packing QTY 4 4 1 1 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−22−00−01−015 IPC 32−22−00−01−010 IPC 32−22−00−04−085 IPC 32−22−00−04−085 IPC 32−22−00−04−090 IPC 32−22−00−04−090 IPC 32−22−00−04−100 IPC 32−22−00−04−090 IPC 32−22−00−04−110 IPC 32−22−00−04−090 Subtask 32−22−20−946−002 C. Reference Information REFERENCE TASK 29−10−00−870−803 TASK 32−00−00−790−801 TASK 32−22−01−720−801 TASK 32−22−01−980−801 TASK 32−22−01−980−802 DESIGNATION Bleed Hydraulic System No. 3 External Leak Check of the Landing Gear Functional Test of the Forward Doors of the Nose Landing Gear Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors 2. Job Set−Up Subtask 32−22−20−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Master EFFECTIVITY: See Pageblock 32−22−20 page 401 32−22−20 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. Procedure Subtask 32−22−20−430−001 Refer to Figure 401. A. If the door selector valve (8) needs fittings installed on it, do the steps that follow: (1) Remove the protective caps and plugs from all hydraulic ports. (2) Lightly lubricate the preformed packings (11), (12), (14), and (16) with clean 02−001 hydraulic fluid. (3) Install the check valve (15) with the preformed packing (16) in the RETURN port of the door selector valve (8). NOTE: Make sure that the flow indication arrow of the check valve (15) points away from the door selector valve when installed. (4) Install the restrictor (13) with the preformed packing (14) in the DOOR CLOSE port of the door selector valve (8). (5) Install the unions (9) and (10) with their preformed packings (11) and (12) in the PRESSURE and DOOR OPEN ports of the door selector valve (8). Subtask 32−22−20−420−001 B. Install the door selector valve (8) as follows: (1) Attach the door selector valve (8) to the aircraft structure with the bolts (7) and the nuts (6). (2) Remove the protective plugs and caps from the selector valve (8) and the hydraulic lines. (3) Connect the hydraulic lines (2), (3), (4), and (5) to the applicable ports on the selector valve. (4) Remove the protective caps from the electrical connector (1) and the selector valve receptacle. (5) Connect the electrical connector to the door selector valve. 4. Close Out Subtask 32−22−20−160−001 A. Clean all signs of hydraulic fluid from the selector valve and the surrounding work area. Subtask 32−22−20−941−002 B. Remove all tools, equipment, and unwanted materials from the work area. Subtask 32−22−20−910−004 C. Close the NLG forward doors (Ref. TASK 32−22−01−980−802). Master EFFECTIVITY: See Pageblock 32−22−20 page 401 32−22−20 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−20−870−001 D. Operate the NLG forward doors (Ref. TASK 32−22−01−720−801) and bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−22−20−910−005 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the NLG forward doors (Ref. TASK 32−22−01−980−801). WARNING: E. Subtask 32−22−20−790−001 F. Examine the work area for leaks (Ref. TASK 32−00−00−790−801). Subtask 32−22−20−910−006 G. Close the NLG forward doors (Ref. TASK 32−22−01−980−802). Master EFFECTIVITY: See Pageblock 32−22−20 page 401 32−22−20 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL CHECK VALVE, NOSE GEAR DOOR SYSTEM − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the check valve, which is installed on the nose−gear−door selector valve. The selector valve is installed on the left side of the nosewheel well. TASK 32−22−25−000−801 Removal of the Check Valve 1. Job Set−Up Information Subtask 32−22−25−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Container, fluid Subtask 32−22−25−946−001 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 29−00−00−910−801 TASK 32−22−01−980−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Hydraulic Safety Precautions Open and Isolate the Nose−Landing−Gear Forward Doors 2. Job Set−Up Subtask 32−22−25−910−002 WARNING: A. OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). Subtask 32−22−25−490−002 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: B. Master EFFECTIVITY: See Pageblock 32−22−25 page 401 32−22−25 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−22−25−910−003 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the NLG forward doors (Ref. TASK 32−22−01−980−801). WARNING: C. 3. Procedure Subtask 32−22−25−020−001 Refer to Figure 401. A. Remove the check valve (2) from the NLG door selector−valve as follows: (1) Put a fluid container below the work area. (2) Disconnect the hydraulic line (1). (3) Remove the check valve (2) and the preformed packing (3). Discard the preformed packing. B. Install a protective plug on the hydraulic line and on the selector valve port. Master EFFECTIVITY: See Pageblock 32−22−25 page 401 32−22−25 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL DOOR SELECTOR VALVE (REF) 3 2 LEGEND. 1. Hydraulic line. 2. Check valve. 3. Preformed packing. ram3222254_001.dc, mb, 24/08/92 1 Check Valve, NLG Door Selector Valve− Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−22−25 page 401 32−22−25 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−22−25−400−801 Installation of the Check Valve 1. Job Set−Up Information Subtask 32−22−25−944−001 A. Consumable Materials REFERENCE 02−001 DESIGNATION Hydraulic fluid, phosphate ester based Subtask 32−22−25−945−001 B. Parts REF NAME OF PART 2 Check Valve 3 Preformed packing QTY 1 1 IPC SEQUENCE NO. IPC 32−22−00−04−110 IPC 32−22−00−04−090 Subtask 32−22−25−946−002 C. Reference Information REFERENCE TASK 29−10−00−870−803 TASK 32−00−00−790−801) TASK 32−22−01−720−801 TASK 32−22−01−980−801 TASK 32−22−01−980−802 DESIGNATION Bleed Hydraulic System No. 3 External Leak Check of the Landing Gear Functional Test of the Forward Doors of the Nose Landing Gear Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors 2. Job Set−Up Subtask 32−22−25−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. 3. Procedure Subtask 32−22−25−430−001 Refer to Figure 401. A. Install the check valve (2) as follows: (1) Remove the protective plugs from the hydraulic line and selector valve port. (2) Lightly lubricate the preformed packing (3) with clean 02−001 hydraulic fluid. (3) Install the preformed packing (3) on the check valve (2). Master EFFECTIVITY: See Pageblock 32−22−25 page 401 32−22−25 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL B. (4) Install the check valve (2) on the door selector valve. NOTE: Make sure that the flow indication arrow on the check valve (2) points away from the selector valve when installed. Connect the hydraulic line (1). 4. Close Out Subtask 32−22−25−160−002 A. Clean all signs of hydraulic fluid from the selector valve and the surrounding work area. Subtask 32−22−25−941−002 B. Remove all tools, equipment, and unwanted materials from the work area. Subtask 32−22−25−910−004 C. Close the NLG forward doors (Ref. TASK 32−22−01−980−802). Subtask 32−22−25−870−001 D. Operate the NLG forward doors (Ref. TASK 32−22−01−720−801) and bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−22−25−910−005 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the NLG forward doors (Ref. TASK 32−22−01−980−801). WARNING: E. Subtask 32−22−25−790−002 F. Examine the work area for leaks (Ref. TASK 32−00−00−790−801). Subtask 32−22−25−910−006 G. Close the NLG forward doors (Ref. TASK 32−22−01−980−802). Master EFFECTIVITY: See Pageblock 32−22−25 page 401 32−22−25 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL SWITCH, MAINTENANCE ACCESS (NLG DOOR) − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the maintenance access switch for the NLG door. The maintenance access switch is installed on the external service panel. TASK 32−22−30−000−801 Removal of the Maintenance Access Switch 1. Job Set−Up Information Subtask 32−22−30−946−003 A. Reference Information REFERENCE TASK 24−00−00−910−801 DESIGNATION Electrical/Electronic Safety Precautions 2. Job Set−Up Subtask 32−22−30−910−001 WARNING: A. OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT. Obey all the electrical/electronic safety precautions (Ref. TASK 24−00−00−910−801). Subtask 32−22−30−865−001 B. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−2 CBP−2 CBP−4 CB NO. F6 P2 P3 B13 NAME PROX SENS LGC/D1 PROX SENS LGC/D1 PROX SENS LGC/D2 WOW 1+2 PROX SENS LGC/D2 ZONE 221 222 222 222 Subtask 32−22−30−010−001 C. Open the access door that follows: ACCESS 122CR DESIGNATION Access door, external service panel Master EFFECTIVITY: See Pageblock 32−22−30 page 401 32−22−30 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. Procedure Subtask 32−22−30−020−001 Refer to Figure 401. A. Remove the switch (3) as follows: (1) Remove the nut (7), the lockwasher (8), the lockring (9). (2) Loosen the captive screws (1). (3) Carefully pull the external−service−panel cover (2) away from its mounting box. NOTE: Identify the top and bottom of the switch for installation purposes. Make a note of the position of the terminal numbers on the back of the switch with reference to the mounted position of the switch in the external−service−panel cover (2). (4) Pull the switch (3) out from the external−service−panel cover (2). (5) Identify each wire (6) to its location on the switch (3). (6) Remove the screws (4), the lockwashers (5), and the wires (6). (7) Remove the switch (3). Master EFFECTIVITY: See Pageblock 32−22−30 page 401 32−22−30 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 7 B A LEGEND. 1. Captive screws. 2. Cover. 3. Maintenance access switch. 4. Screw. 5. Lockwasher. 6. Electrical wire. 7. Nut. 8. Lock washer. 9. Lock ring. 2 9 8 7 KEYHOLE (REF) 122 CR 1 3 A 5 6 B ram3222304_001(2).dc, pb, 08/11/95 4 Maintenance Access Switch − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−22−30 page 401 32−22−30 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−22−30−400−801 Installation of the Maintenance Access Switch 1. Job Set−Up Information Subtask 32−22−30−945−001 A. Parts REF 3 4 5 7 8 9 NAME OF PART Switch Screw Lockwasher Nut Lockwasher Lock ring QTY IPC SEQUENCE NO. 1 4 IPC 24−24−01−01−075 4 NOTE: All parts come with 2 the switch 1 1 Subtask 32−22−30−946−002 B. Reference Information REFERENCE TASK 24−00−00−910−801 TASK 32−22−01−720−801 DESIGNATION Electrical/Electronic Safety Precautions Functional Test of the Forward Doors of the Nose Landing Gear 2. Job Set−Up Subtask 32−22−30−910−002 OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT. Obey all the electrical/electronic safety precautions (Ref. TASK 24−00−00−910−801). WARNING: A. Subtask 32−22−30−869−001 B. Make sure that the aircraft is in the same configuration as in the removal task. 3. Procedure Subtask 32−22−30−420−001 Refer to Figure 401. A. Install the maintenance access switch (3) as follows: (1) Connect the electrical wires (6) to the switch (3) with the lockwashers (5) and the screws (4). (2) Remove all identification tags, such as tape, that were used to identify the wires to their original locations. Master EFFECTIVITY: See Pageblock 32−22−30 page 401 32−22−30 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (3) Put the maintenance access switch (3) through its mounting hole on the external−service−panel cover (2). NOTE: Before the switch is installed, make sure that: −There is a nut (7) installed on the threads of the microswitch (3) −The switch is correctly positioned to correspond to the OPEN and FLT/NORM positions on the front of the external−service−panel cover (2). (4) Install the lockring (9), the lockwasher (8), and the nut (7). NOTE: Make sure that the lockring key engages the keyhole in the cover. (5) Carefully put the external−service−panel cover (2) in position on its mounting box. (6) Tighten the captive screws (1). 4. Close Out WARNING: MAKE SURE THAT THE POSITION OF THE NOSE DOOR SWITCH AGREES WITH THE POSITION OF THE NLG FORWARD DOORS. IF THE SWITCH POSITION DOES NOT AGREE WITH THE POSITION OF THE DOORS, THE DOORS WILL OPERATE WHEN THE CIRCUIT BREAKERS ARE CLOSED AND HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. THIS CAN CAUSE INJURIES TO PERSONS NEAR THE DOORS. Subtask 32−22−30−865−002 A. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−2 CBP−2 CBP−4 CB NO. F6 P2 P3 B13 NAME PROX SENS LGC/D1 PROX SENS LGC/D1 PROX SENS LGC/D2 WOW 1+2 PROX SENS LGC/D2 ZONE 221 222 222 222 Subtask 32−22−30−710−001 B. Do a functional test of the NLG forward doors (Ref. TASK 32−22−01−720−801). Subtask 32−22−30−410−001 C. Close the access door that follows: ACCESS 122CR DESIGNATION Access door, external service panel Subtask 32−22−30−941−002 D. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−22−30 page 401 32−22−30 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL EXTENSION AND RETRACTION − DESCRIPTION AND OPERATION 1. 2. General A. The aircraft has three hydraulically−actuated landing−gear assemblies which supply directional stability and support to the aircraft while on the ground. Each gear is retracted during flight to increase the efficiency of aerodynamic flow. The gear is then extended into a locked vertical position for aircraft landings. The extension and retraction system includes the subsystems that follow: ± Landing gear control (32−31−00) ± Main landing gear (MLG) extension/retraction (32−32−00) ± Nose landing gear (NLG) extension/retraction (32−33−00) ± Landing gear manual release (32−34−00). Description Refer to Figure 1. A. Landing Gear Control (1) Pilot inputs to the aircraft landing gear are by the operation of the control lever on the landing gear control handle. The landing gear control handle includes a two−position control lever, a downlock release button (DN LCK REL), and a mute switch/light for the landing gear aural warning−horn (MUTE HORN). The landing gear control handle is installed in the LDG GEAR control panel on the center pedestal in the flight compartment. B. MLG Extension/Retraction (1) The MLG extension/retraction system is electrically controlled and hydraulically actuated. The MLG are extended in the outboard direction and hydro/mechanically locked in place for landing. They are retracted by the MLG side stay actuator in the inboard direction and locked in the MLG wheel wells during flight by the MLG uplock. The MLG extension and retraction system includes the components that follow: ± MLG side stay actuator ± MLG uplock assembly ± MLG selector valve ± Priority valve ± Runaround and bypass valve. C. NLG Extension/Retraction (1) The NLG is hydraulically extended in the aft direction and mechanically locked in place for landing. It is retracted in the forward direction and locked into the NLG wheel well during flight. The NLG extension and retraction system includes the components that follow: ± Extension/retraction actuator ± NLG uplock assembly ± NLG selector valve ± Priority valve. Master EFFECTIVITY: See Pageblock 32−30−00 page 1 32−30−00 Page 1 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL D. 3. Landing−Gear Manual Release System (1) The manual release system is used to extend the gear manually during an electrical or hydraulic failure. If a malfunction occurs in the landing gear extension system, the gear can be manually released from the flight compartment. The manual release system includes the components that follow: ± Manual release handle ± Downlock assist actuator ± Operating lever ± NLG release mechanism ± MLG release mechanism ± Downlock assist valve ± MLG manual−release relief−valve ± NLG bypass valve ± NLG door bypass−valve. Operation A. Landing Gear Extension (1) When the pilot sets the landing gear control handle to the DN position, the extend signal is sent to the proximity sensor electronic unit (PSEU). The PSEU will then collect and calculate the input signals from the landing gear and other aircraft systems to control the actuation of the landing gear. (2) The PSEU will then supply an electrical signal to energize the MLG selector valve, and to the NLG door selector valve to the doors open position. When the forward doors are open, the PSEU sends a signal to energize the NLG selector valves to the gear down position. (3) Hydraulic fluid from system No. 3 is used to extend the actuators for the NLG forward doors and release the MLG and NLG uplocks. (4) Hydraulic fluid is then sent to the extend side of the MLG side stay actuators and the NLG extension/retraction actuator. (5) When the uplock actuators have released the gear, the main gear and the nose gear will extend to the down and locked position. (6) When the down and locked signal is complete the PSEU will send a signal to close the NLG forward doors. It also keeps the NLG and MLG selector valves energized in the gear down position with the hydraulic lines pressurized. B. Landing Gear Retraction (1) When the pilot sets the landing gear control handle to the UP position, the retract signal is sent to the PSEU. The PSEU will then collect and calculate the input signals from the landing gear and other aircraft systems to control the retraction of the landing gear. (2) The PSEU will then supply an electrical signal to energize the MLG selector valve and the NLG door selector valve to the doors open position. When the forward doors are open, the PSEU sends a signal to energize the NLG selector valves to the gear up position. Master EFFECTIVITY: See Pageblock 32−30−00 page 1 Page 2 32−30−00 Dec 10/2005 C AIRCRAFT MAINTENANCE MANUAL C. (3) Hydraulic fluid from system No. 3 is sent to extend the actuators for the NLG forward doors. When the nose doors are fully open, the hydraulic fluid is sent to retract the MLG side stay actuators and the NLG extension/retraction actuator. (4) When the gear has been fully retracted, the uplocks will mechanically lock the gear into place. When the uplock signal is complete, the NLG forward doors will be closed and locked for flight. Manual Release System (1) The manual release system is controlled by the vertical movement of the manual release handle. The movement of the handle is transmitted by a cable circuit to the MLG and the NLG release mechanisms. (2) Cable movement moves the lever assembly on the NLG release mechanism. The movement of this lever releases the NLG forward doors, the NLG uplock, the NLG bypass valve, and the NLG door bypass−valve. The NLG and NLG doors are helped to the down and locked position by spring pressure and aerodynamic flow. (3) The movement of the operating lever on the runaround and bypass valve is transmitted by two cables to the MLG uplocks. This releases the MLG uplocks and permits the landing gear to extend by the weight of the gear. (4) The movement of the operating lever is also transmitted by a control rod to the downlock assist valve. This sends pressurized hydraulic fluid from system No. 2 to extend the downlock assist actuators and help the main gear to extend to the down and locked position. Master EFFECTIVITY: See Pageblock 32−30−00 page 1 32−30−00 Page 3 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL NOSE LANDING GEAR EXTENSION RETRACTION LANDING GEAR CONTROL SYSTEM LANDING GEAR ALTERNATE EXTENSION MAIN LANDING GEAR EXTENSION RETRACTION ram3230000_001.dg, sb, 29/09/92 LEGEND. Alternate extension Landing gear extension/retraction Extension/Retraction − Block Diagram Figure 1 Master EFFECTIVITY: See Pageblock 32−30−00 page 1 32−30−00 Page 4 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL EXTENSION AND RETRACTION, LANDING GEAR − MAINTENANCE PRACTICES 1. General A. The procedure that follows gives the maintenance practice for the extension and retraction of the landing gear. This procedure is used when it is necessary to do a basic extension and retraction of the the landing gear. TASK 32−30−00−710−802 Landing Gear Extension and Retraction − Maintenance Practices 1. Job Set−Up Information Subtask 32−30−00−946−011 A. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 10−11−00−000−801 TASK 10−11−00−000−802 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−803 TASK 12−00−06−863−804 TASK 12−00−07−861−801 TASK 12−00−07−861−802 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Removal of the Nose Landing Gear Lockpin Removal of the Main Landing Gear Lockpins Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 Connect External AC Power Remove External AC Power 2. Job Set−Up Subtask 32−30−00−490−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. Subtask 32−30−00−840−001 B. At the LDG GEAR control panel, make sure that the landing gear control handle is in the DN position. Master EFFECTIVITY: See Pageblock 32−30−00 page 201 32−30−00 Page 201 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−30−00−582−011 C. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). Subtask 32−30−00−090−001 D. Remove the safety lockpins from the nose landing gear and the main landing gear (Ref. TASK 10−11−00−000−801 and TASK 10−11−00−000−802). Subtask 32−30−00−861−012 E. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801). Subtask 32−30−00−863−012 STAY AWAY FROM THE NOSE LANDING GEAR DOORS. IF THE DOORS ARE OPEN WHEN HYDRAULIC PRESSURE IS APPLIED TO HYDRAULIC SYSTEM NO. 3, THE DOORS WILL CLOSE. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Pressurize hydraulic system No. 3 (Ref. TASK 12−00−06−863−803). WARNING: F. Subtask 32−30−00−866−002 G. Make sure that the flaps are fully retracted to zero degrees (Ref. TASK 27−54−00−866−802). Subtask 32−30−00−980−004 H. To keep the landing gear horn from being heard during this procedure, move the throttle levers forward out of the IDLE position. 3. Procedure Subtask 32−30−00−710−001 WARNING: BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. A. Do the retraction and extension of the landing gear as follows: **ON A/C 7032, 7059, 7061, 7063, 7094, 7103, 7110, 7115, 7125, 7133, 7142, 7148, 7154, 7166−7167, 7170, 7205, 7272, 7365, 7371, 7384, 7390−7990, 8000−8064, 8066−8068 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Post SB601R−31−022 NOTE: If the throttle levers are in the IDLE position, the landing gear is not down and locked, and the logic state is satisfied for the landing gear horn to be heard for 10 seconds or more, one or more of the indications in the three GEAR boxes on the EICAS primary page will become amber and flash with a one second interval. This is a visual indication for additional landing safety and occurs even if the landing gear horn has been muted or disabled. Master EFFECTIVITY: See Pageblock 32−30−00 page 201 202 32−30−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL (1) At the LDG GEAR control panel, put the landing gear control handle to the UP position. (2) Let the landing gear retract and lock in the UP position. (3) Put the landing gear control handle to the DN position. (4) Let the landing gear extend and lock in the DN position. B. If required, do the retraction and extension of the landing gear until the applicable maintenance checks are completed. C. When the extension and retraction checks for the landing gear are complete, make sure that: (1) The landing gear control handle is put to the DN position. (2) The landing gear is down and locked. 4. Close Out Subtask 32−30−00−863−013 A. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−30−00−861−013 B. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802). Subtask 32−30−00−490−002 C. Install the safety lockpins at the nose landing gear and at the main landing gear again (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Subtask 32−30−00−582−012 D. Lower the aircraft and remove the aircraft from the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−30−00−941−005 E. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−30−00 page 201 32−30−00 Page 203 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL EXTENSION AND RETRACTION − ADJUSTMENT/TEST 1. General A. The maintenance procedures that follow give the instructions for: ± The functional test of the landing gear extension/retraction system ± The gear disagree test of the landing gear extension/retraction system ± The system test of the landing gear priority valves. There are two priority valves − one for the nose landing gear (NLG) and one for the main landing gear (MLG). Both priority valves are tested at the same time when the system test is done. TASK 32−30−00−720−801 Functional Test of the Landing Gear Extension/Retraction System 1. Reason for the Job Refer to MRB 32−00−00−07. 2. Job Set−Up Information Subtask 32−30−00−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Stopwatch Subtask 32−30−00−946−001 B. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 10−11−00−000−801 TASK 10−11−00−000−802 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−803 TASK 12−00−06−863−804 TASK 12−00−07−861−801 TASK 12−00−07−861−802 TASK 27−54−00−866−802 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Removal of the Nose Landing Gear Lockpin Removal of the Main Landing Gear Lockpins Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 Connect External AC Power Remove External AC Power Electrical Retraction of the Flaps Master EFFECTIVITY: See Pageblock 32−30−00 page 501 32−30−00 Page 501 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. Job Set−Up Subtask 32−30−00−861−001 A. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801). Subtask 32−30−00−582−001 B. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). Make sure that there is at least 4 inches (10 cm) of clearance between the tires and the ground. Subtask 32−30−00−861−002 C. Make sure that the LDG GEAR control handle is in the DN position and that the green−color DN indications are shown in the three GEAR boxes on the EICAS primary page. Subtask 32−30−00−090−002 D. Remove the safety lockpins from the nose landing gear and from the main landing gear (Ref. TASK 10−11−00−000−801 and TASK 10−11−00−000−802). Subtask 32−30−00−863−003 E. Pressurize hydraulic system No. 3A (Ref. TASK 12−00−06−863−803). Subtask 32−30−00−866−001 F. Make sure that the flaps are fully retracted to zero degrees (Ref. TASK 27−54−00−866−802). **ON A/C 7033, 7041, 7052, 7138, 7149, 7180, 7189, 7193 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Pre SB601R−31−022 Subtask 32−30−00−980−001 G. To keep the landing gear horn from being heard during this procedure, move the throttle levers forward out of the IDLE position. Master EFFECTIVITY: See Pageblock 32−30−00 page 501 502 32−30−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7032, 7059, 7061, 7063, 7094, 7103, 7110, 7115, 7125, 7133, 7142, 7148, 7154, 7166−7167, 7170, 7205, 7272, 7365, 7371, 7384, 7390−7990, 8000−8064, 8066−8068 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Post SB601R−31−022 Subtask 32−30−00−980−002 H. To keep the landing gear horn from being heard during this procedure, and to make sure that the correct indication will be seen on the EICAS primary page, move the throttle levers forward out of the IDLE position. NOTE: If the throttle levers are in the IDLE position, the landing gear is not down and locked, and the logic state is satisfied for the landing gear horn to be heard for 10 seconds or more, one or more of the indications in the three GEAR boxes on the EICAS primary page will become amber and flash with a one second interval. This is a visual indication for additional landing safety and occurs even if the landing gear horn has been muted or disabled. **ON A/C ALL 4. Procedure NOTE: Unless it is specified in this procedure, ignore the three white−color UP indications in the GEAR boxes on the EICAS primary page. In this procedure, the three white−color UP indications will not go off after 30 seconds and is normal. When the aircraft is in the correct flight configuration, the three white−color UP indications go out of view after a maximum of 30 seconds after first being seen. This will only happen if: ± There is no message related to brakes, gear, flaps, antiskid, steering, WOW, or the proximity sensor system shown on the EICAS primary and status pages ± The flaps are at zero degrees ± There is no flap overspeed condition. Subtask 32−30−00−867−010 WARNING: A. BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. Do a functional test of the landing gear extension/retraction system as follows: CAUTION: IF THE FORWARD DOORS OF THE NOSE LANDING GEAR DO NOT OPEN BEFORE THE NOSE LANDING GEAR RETRACTS, PUT THE LANDING−GEAR SELECTOR HANDLE IN THE "DN" POSITION. THE RETRACTION OF THE NOSE LANDING GEAR WILL CAUSE DAMAGE TO THE CLOSED DOORS. (1) Put the LDG GEAR control handle to the UP position and make sure that the Master EFFECTIVITY: See Pageblock 32−30−00 page 501 503 32−30−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL conditions that follow are observed: NOTE: A second technician must visually monitor the landing gear and the NLG doors to verify the landing gear extension and retraction times. (a) The NLG doors open. (b) The three amber−color gear−hash−marks come into view on the EICAS primary page. (c) The NLG and MLG are retracted and locked in the up position in 20 seconds maximum, and that the white−color UP indications come into view in the three GEAR boxes on the EICAS primary page. (d) The NLG doors close. CAUTION: IF THE FORWARD DOORS OF THE NOSE LANDING GEAR DO NOT OPEN BEFORE THE NOSE LANDING GEAR EXTENDS, PUT THE LANDING−GEAR SELECTOR HANDLE IN THE "UP" POSITION. THE EXTENSION OF THE NOSE LANDING GEAR WILL CAUSE DAMAGE TO THE CLOSED DOORS. (2) Monitor the hydraulic PSI indication on the EICAS display until the hydraulic pressure has become stable at 3000 ±200 psi (20954 ±1378 kpa) and then put the LDG GEAR control handle in the DN position. NOTE: A second technician must visually monitor the landing gear and the NLG doors to verify the landing gear extension and retraction times. (a) Make sure that the conditions that follow are observed: 1 The NLG doors open. 2 The three amber−color gear−hash−marks come into view on the EICAS primary page. 3 The NLG and the MLG are extended and locked in the down position in a maximum of 20 seconds, and that the green−color DN indications come into view in the three GEAR boxes on the EICAS primary page. 4 The NLG doors close. (3) Set the hydraulic pump No. 3A switch to the OFF position. (4) Monitor the hydraulic PSI indication on the EICAS display until the hydraulic pressure is released from hydraulic system No. 3A. (5) Set the hydraulic pump No. 3B switch to the ON position to pressurize hydraulic system No. 3B. (6) Monitor the hydraulic PSI indication on the EICAS display until the hydraulic pressure of hydraulic system No. 3B has become stable at 3000 ±200 psi (20954 ±1378 kpa). (7) Put the LDG GEAR control handle to the UP position and make sure that: (a) The NLG doors open. (b) The three amber−color gear−hash−marks come into view on the EICAS primary page. (c) The NLG and the MLG are retracted and locked in the up position in 20 seconds maximum, and that the white−color UP indications come into view in the three GEAR boxes on the EICAS primary page. Master EFFECTIVITY: See Pageblock 32−30−00 page 501 504 32−30−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (8) (9) (10) (11) (12) (d) The NLG doors close. Monitor the hydraulic PSI indication on the EICAS display until the hydraulic pressure has become stable at 3000 ±200 psi (20954 ±1378 kpa) and then put the LDG GEAR control handle in the DN position. (a) Make sure that the conditions that follow are observed: 1 The NLG doors open. 2 The three amber−color gear−hash−marks come into view on the EICAS primary page. 3 The NLG and the MLG are extended and locked in the down position in a maximum of 20 seconds, and that the green−color DN indications come into view in the three GEAR boxes on the EICAS primary page. 4 The NLG doors close. With the hydraulic pump No. 3B switch in the ON position, set the hydraulic pump No. 3A switch to the ON position to pressurize both hydraulic systems No. 3A and No. 3B. NOTE: The extension/retraction times are decreased in the steps that follow because both ACMPs (No. 3A and No. 3B) are in use. Monitor the hydraulic PSI indication on the EICAS display until the hydraulic pressure of hydraulic system No. 3A has become stable at 3000 ±200 psi (20954 ±1378 kpa). Put the LDG GEAR control handle to the UP position and make sure that the NLG and the MLG are retracted and locked in the up position in 12 to 14 seconds maximum. Monitor the hydraulic PSI indication on the EICAS display until the hydraulic pressure has become stable at 3000 ±200 psi (20954 ±1378 kpa) and do the steps that follow: (a) Put the LDG GEAR control handle in the DN position. Make sure that the NLG and the MLG are extended and locked in the down position in a maximum of 12 to 14 seconds. (b) Put the LDG GEAR control handle to the UP position; and when the landing gear has been retracted to approximately the middle of its travel, put the LDG GEAR control handle to the DN position. Make sure that the landing gear extends and locks immediately. (c) Put the LDG GEAR control handle to the UP position and make sure that the NLG and the MLG are retracted and locked in the up position. (d) Put the LDG GEAR control handle to the DN position; and when the landing gear has been extended to approximately the middle of its travel, put the LDG GEAR control handle to the UP position. Make sure that the landing gear retracts and locks immediately. Master EFFECTIVITY: See Pageblock 32−30−00 page 501 505 32−30−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 5. Close Out Subtask 32−30−00−840−002 A. Put the LDG GEAR control handle in the DN position and make sure that the NLG and the MLG are extended and locked in the down position, and that the green−color DN indications come into view in the three GEAR boxes on the EICAS primary page. Subtask 32−30−00−980−003 B. Move the throttle levers aft to the IDLE position again. Subtask 32−30−00−863−014 C. Release the pressure from hydraulic system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−30−00−867−002 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: D. Subtask 32−30−00−861−003 E. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802). Subtask 32−30−00−586−001 F. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−30−00−941−002 G. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−30−00 page 501 506 32−30−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL TASK 32−30−00−750−801 Landing Gear Extension/Retraction Gear Disagree Test 1. Job Set−Up Information Subtask 32−30−00−946−002 A. Reference Information TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−803 TASK 12−00−06−863−804 TASK 12−00−07−861−801 TASK 12−00−07−861−802 Put the Aircraft on Jacks Removal of the Aircraft from Jacks Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 Connect External AC Power Remove External AC Power 2. Job Set−Up Subtask 32−30−00−865−003 A. Make sure that the circuit breakers that follow are closed: CBP−1 CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−4 A2 F6 F7 G11 A2 F9 G15 P2 P3 B13 HYD PUMP 3B PROX SENS LGC/D1 PROX SENS WOW 1 HYD SYST AC PUMP CONT 3B HYD PUMP 3A PROX SENS WOW 2 HYD SYST AC PUMP CONT 3A PROX SENS LGC/D1 PROX SENS LGC/D2 WOW 1 + 2 PROX SENS LGC/D2 221 221 221 221 222 222 222 222 222 222 Subtask 32−30−00−490−006 WARNING: B. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Master EFFECTIVITY: See Pageblock 32−30−00 page 501 32−30−00 Page 507 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−30−00−582−002 C. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). Make sure that there is at least 4 inches (10 cm) of clearance between the tires and the ground. Subtask 32−30−00−861−004 D. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801). Subtask 32−30−00−863−002 E. Pressurize hydraulic system No. 3 (Ref. TASK 12−00−06−863−803). Subtask 32−30−00−861−005 F. Make sure that the green−color DN indications are shown in the three GEAR boxes on the EICAS primary page. 3. Procedure Subtask 32−30−00−867−004 A. With the safety lockpins installed at the nose landing gear (NLG) and at the main landing gear (MLG), put the LDG GEAR control handle to the UP position. (1) Make sure that the steps that follow occur: (a) The NLG doors open. NOTE: Usually, when the LDG GEAR control handle is selected to the UP position, the NLG will move forward slightly (due to normal manufacturing tolerances) and the NLG downlock 1 and 2 (inputs S21 and S35) will become FAR. When this occurs, the NOSE DOOR OPEN indication will not be shown on the EICAS primary page. If the inputs S21 or S35 stay near, the NOSE DOOR OPEN indication will is shown on the EICAS primary page approximately 10 seconds after the LDG GEAR control handle is selected to the UP position. (b) The GEAR DISAGREE indication comes into view on the EICAS primary page (after 6 seconds). Master EFFECTIVITY: See Pageblock 32−30−00 page 501 32−30−00 Page 508 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL B. C. (2) Any of the indications that follow can come into view on the EICAS primary page: NOTE: This step is used for fault isolation purposes only and is not a requirement for this test. ± Usually, both of the MLG position indication−boxes remain green because the related downlock 1 and 2 inputs (inputs S17, S19, S33, and S34) for the L/H and the R/H MLG stay NEAR. NOTE: With the MLG safety lockpins installed, it is possible that a MLG downlock proximity sensor (input S17, S19, S33, or S34) can become FAR when the MLG is unlocked from its downlock position (due to normal proximity sensor tolerances). If this occurs, the related MLG position indication−box will change to the color red when the PSEU calculates that the MLG was in−transit for more than 28 seconds. ± Usually, the NLG will move forward slightly (due to normal manufacturing tolerances) and the NLG downlock 1 and 2 (inputs S21 and S35) will become FAR. When this occurs, the NLG position indication−box will change to the color red when the PSEU calculates that the NLG was in−transit for more than 28 seconds. NOTE: It is possible that the NLG position indication−box will remain green if the NLG downlock 1 or 2 proximity sensors (input S21 or S35) stay NEAR. (3) Make sure that the indications that follow occur: (a) The MASTER WARNING lights on the glareshield come on. (b) The voice message GEAR DISAGREE is heard. NOTE: If the NOSE DOOR OPEN indication is shown on the EICAS primary page, the voice message NOSE DOOR is also heard. Push the MASTER WARNING lights off. Put the LDG GEAR control handle to the DN position. (1) Make sure that the steps that follow occur: (a) The NLG doors close. (b) The GEAR DISAGREE indication goes out of view on the EICAS primary page. NOTE: The NOSE DOOR OPEN indication will also go out of view if it was shown on the EICAS primary page. (c) The three GEAR boxes indicate DN in the color green on the EICAS primary page (all of the MLG and NLG downlock proximity−sensor inputs are NEAR). (d) The voice message GEAR DISAGREE is not heard. NOTE: The voice message NOSE DOOR will also not be heard if the NOSE DOOR OPEN indication went out of view on the EICAS primary page. Master EFFECTIVITY: See Pageblock 32−30−00 page 501 32−30−00 Page 509 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 4. Close Out Subtask 32−30−00−863−015 A. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−30−00−861−006 B. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802). Subtask 32−30−00−586−002 C. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−30−00−941−003 D. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−30−00 page 501 32−30−00 Page 510 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−30−00−730−801 System Test of the Landing Gear Priority Valves 1. Job Set−Up Information Subtask 32−30−00−946−003 A. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 10−11−00−000−801 TASK 10−11−00−000−802 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−803 TASK 12−00−06−863−804 TASK 12−00−07−861−801 TASK 12−00−07−861−802 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Removal of the Nose Landing Gear Lockpin Removal of the Main Landing Gear Lockpins Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 Connect External AC Power Remove External AC Power 2. Job Set−Up Subtask 32−30−00−865−004 A. Make sure that the circuit breakers that follow are closed: CB PANEL CBP−1 CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−4 CB NO. A2 F6 F7 G11 A2 F9 G15 P2 P3 B13 NAME HYD PUMP 3B PROX SENS LGC/D1 PROX SENS WOW 1 HYD SYST AC PUMP CONT 3B HYD PUMP 3A PROX SENS WOW 2 HYD SYST AC PUMP CONT 3A PROX SENS LGC/D1 PROX SENS LGC/D2 WOW 1 + 2 PROX SENS LGC/D2 ZONE 221 221 221 221 222 222 222 222 222 222 Subtask 32−30−00−582−003 B. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). Master EFFECTIVITY: See Pageblock 32−30−00 page 501 32−30−00 Page 511 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−30−00−861−007 C. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801). Subtask 32−30−00−867−005 D. Remove the safety lockpins from the nose landing gear and the main landing gear (Ref. TASK 10−11−00−000−801 and TASK 10−11−00−000−802). 3. Procedure Subtask 32−30−00−730−001 WARNING: A. MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF ALL FLIGHT CONTROL SURFACES. FLIGHT CONTROL MOVEMENTS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE EQUIPMENT. Do a system test of the landing gear priority valves as follows: NOTE: During landing gear extension/retraction (without flight control movement), the landing−gear priority valves will open when their inlet pressure is > 2200 ±50 psi (15858 ±689 kPa) (as measured at the priority valve). This will allow hydraulic fluid to flow through to the landing gear selector valves and is referred to as the cracking value for the priority valve. During landing gear extension/retraction (with flight control movement), the landing−gear priority valves will close when their nominal minimum inlet pressure is <2000 psi (13790 kPa) (as measured at the priority valve). This is referred to as the reseat value for the priority valve. The closed priority valves then prevent the flow of hydraulic fluid to the landing gear selector−valves and gives hydraulic system priority to the flight controls over the landing gear. NOTE: In the procedure that follows, it is possible that the minimum reseat value (that is indicated on the EICAS display for hydraulic system No. 3) can be as low as 2100 psi (14479 kPa). This is because: ± there is a system pressure loss of approximately 50 psi (345 kPa) between the EICAS pressure transducer and the priority valve, ± the EICAS display has a resolution of 100 psi (689 kPa), ± and the EICAS display has a hysteresis of 70 psi (483 kPa). There is a nominal ∆P of approximately 200 psi (1379 kPa) between the reseat value and the cracking value of the priority valve. (1) Set the secondary EICAS display to the hydraulic page. (2) Pressurize hydraulic system No. 3 with one pump (3A or 3B). Put the other hydraulic pump switch to the OFF position (Ref. TASK 12−00−06−863−803). (3) Put the LDG GEAR control handle to the UP position and, at the same time, operate the rudder, the elevator, and the ailerons. (4) Monitor the EICAS display and make sure that the landing gear momentarily stops its retraction when the hydraulic pressure in system No. 3 drops below the reseat value of 2100−2300 psi (14479−15858 kPa). Master EFFECTIVITY: See Pageblock 32−30−00 page 501 32−30−00 Page 512 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (5) Continue to operate the flight controls. (6) Monitor the EICAS display and make sure that the landing gear does not retract, but the flight controls operate, while the hydraulic pressure is < the reseat value of 2100−2300 psi (14479−15858 kPa). (7) Stop the operation of the flight controls. (8) Monitor the EICAS display and make sure that the landing gear continues to retract when the hydraulic pressure is > the cracking value of between 2100 and 2300 psi (14479−15858 kPa). (9) Make sure that the landing gear retracts and locks in the up position. (10) Put the LDG GEAR control handle to the DN position. (11) Make sure that the landing gear extends and locks in the down position (the green−color DN indications are displayed in the three GEAR boxes on the primary EICAS display). 4. Close Out Subtask 32−30−00−863−016 A. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−30−00−861−009 B. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802). Subtask 32−30−00−867−007 C. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Subtask 32−30−00−586−003 D. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−30−00−941−004 E. Remove all tools, placards, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−30−00 page 501 32−30−00 Page 513 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL LANDING GEAR CONTROL − DESCRIPTION AND OPERATION 1. 2. 3. 4. General A. The aircraft landing gear is operated at the LDG GEAR control panel assembly in the flight compartment. It contains the landing gear control handle (with a downlock release lever), and a mute button for the aural warning horn. Component Details Refer to Figure 1. A. Control Panel Assembly (1) The LDG GEAR control panel assembly is installed on the center pedestal, below the center instrument panel. A lever on the landing gear control handle is used to control the extension and retraction of the main and nose landing gear. The lever is moved up and down to select the landing gear position. The lever is held in position by two mechanical detents. (2) The control lever has a downlock mechanism which prevents inadvertent retraction of the landing gear while the aircraft is on the ground. The downlock mechanism is a solenoid−operated mechanical lock, which locks the control lever automatically at the DN (down) position when the aircraft is in a weight−on−wheels (WOW) condition. When the aircraft is in a weight−off−wheels condition (WOFFW), the downlock mechanism disengages and the lever can be moved to the UP position. An override feature to mechanically release the downlock mechanism is provided by a downlock release lever (DN LCK REL) installed on the lower left side of the landing gear control handle. Operation A. The extend or retract signal from the landing gear control handle is sent to the proximity sensor electronic unit (PSEU). The PSEU then collects and calculates signals from the different aircraft systems. If all of the necessary signals are present, the PSEU will energize the solenoid selector valves (SSV) for the main landing gear, nose landing gear, and the NLG doors. B. The PSEU sends the output control signals to the engine indication and crew alerting system (EICAS). The EICAS screen gives visual indications of the landing gear position and status. Landing Gear Aural Warning GEAR POSITION AIRSPEED <185 knots <185 knots WoffW >2 minutes and any one gear <163 knots not down and locked <163 knots <163 knots FLAPS <5° <5° <30° <30° Any position POWER LEVERS Both at idle One at idle Any position One at idle Both at idle HORN MUTE HORN POSSIBLE On No On Yes On No On Yes On No Logic Conditions for Landing Gear Aural Warning Table 1 Master EFFECTIVITY: See Pageblock 32−31−00 page 1 32−31−00 Page 1 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7033, 7041, 7052, 7138, 7149, 7180, 7189, 7193 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Pre SB601R−31−022 A. Other Conditions RADIO GEAR POSITION ALTIMETER VERTICAL AIRSPEED <400 ft/min in descent WoffW >2 minutes RADIO and any one gear ALTITUDE <400 ft/min in descent and vertical not down and locked <1000 ft speed indicator is not valid (failed) HORN MUTE HORN POSSIBLE On No On No Logic Conditions for Landing Gear Aural Warning Table 1 B. Refer to Table 1 and Table 2. A continuous aural warning horn will be heard if the aircraft is in a weight off wheels configuration for > two minutes AND any one gear is not down and locked AND any of the logic conditions that are given in the table that follows are satisfied. The warning horn is not mutable when it is activated by flaps > 30 degrees, or if both throttles are at idle. If one throttle lever only is set at IDLE, the aural warning horn can be cancelled. The MUTE HORN switch is located near the top left side of the landing gear control handle. **ON A/C 7032, 7059, 7061, 7063, 7094, 7103, 7110, 7115, 7125, 7133, 7142, 7148, 7154, 7166−7167, 7170, 7205, 7272, 7365, 7371, 7384, 7390−7990, 8000−8064, 8066−8068 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Post SB601R−31−022 C. Other Conditions RADIO GEAR POSITION ALTIMETER VERTICAL AIRSPEED <400 ft/min in descent WoffW >2 minutes RADIO and any one gear ALTITUDE <400 ft/min in descent and windshear not down and locked <1000 ft monitor has failed HORN MUTE HORN POSSIBLE On No On No Logic Conditions for Landing Gear Aural Warning Table 3 D. Refer to Table 1 and Table 3. If the throttle levers are in the IDLE position, the landing gear is not down and locked, and the logic state is satisfied for the landing gear horn to be heard for 10 seconds or more, one or more of the indications in the three GEAR boxes on the EICAS primary page will become amber and flash with a one second interval. This is a visual indication for additional landing safety and occurs even if the landing gear horn has been muted or disabled. A continuous aural warning horn will be heard if the aircraft is in a weight off wheels Master EFFECTIVITY: See Pageblock 32−31−00 page 1 Page 2 32−31−00 Dec 10/2005 C AIRCRAFT MAINTENANCE MANUAL configuration for > two minutes AND any one gear is not down and locked AND any of the logic conditions that are given in the table that follows are satisfied. The warning horn is not mutable when it is activated by flaps > 30 degrees, or if both throttles are at idle. If one throttle lever only is set at IDLE, the aural warning horn can be cancelled. The MUTE HORN switch is located near the top left side of the landing gear control handle. **ON A/C ALL 5. Component Location Index Refer to Figure 1. COMPONENT NAME Landing gear control handle QTY ACCESS/ZONE 1 Flight compartment Master EFFECTIVITY: See Pageblock 32−31−00 page 1 REFERENCE 32−31−01 Page 3 32−31−00 Dec 10/2005 C AIRCRAFT MAINTENANCE MANUAL NO.3 HYDRAULIC SYSTEM NO.2 HYDRAULIC SYSTEM ACCUMULATOR ACCUMULATOR LDG GEAR UP NLG DOORS SELECTOR VALVE NOSE LANDING GEAR SELECTOR VALVE NLG DOORS DUMP VALVE NOSE LANDING GEAR DUMP VALVE DN LCK REL LANDING GEAR CONTROL CENTRE INSTRUMENT PANEL NLG DOORS CAM LOCK NLG UPLOCK NOSE LANDING GEAR ACTUATOR DN NLG DOWNLOCK MAIN GEAR SELECTOR VALVE PSEU LH MAIN GEAR ACTUATOR RH MAIN GEAR ACTUATOR LH MAIN GEAR UPLOCK RH MAIN GEAR UPLOCK LH MAIN GEAR DOWNLOCK ASSIST ACTUATOR RH MAIN GEAR DOWNLOCK ASSIST ACTUATOR MAIN GEAR DOWNLOCK ASSIST SELECTOR VALVE M R A E L N E U A A S L E LG PULL L A N G D E I A N R G LANDING GEAR MANUAL RELEASE HANDLE CENTRE PEDESTAL ram3231000_001.dg, ks/pm, 06/09/95 MAIN GEAR DUMP VALVE Landing Gear Control − Block Diagram Figure 1 Master EFFECTIVITY: See Pageblock 32−31−00 page 1 32−31−00 Page 4 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL CONTROL HANDLE, LANDING GEAR − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the landing gear control handle. The landing gear control handle is installed in the forward end of the center pedestal, in the flight compartment. TASK 32−31−01−000−801 Removal of the Landing Gear Control Handle 1. Job Set−Up Subtask 32−31−01−865−001 A. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−4 CB NO. F6 F7 F9 P2 P3 B13 NAME PROX SENS LGC/D1 WOW1 PROX SENS WOW2 PROX SENS LGC/D1 PROX SENS LGC/D2 WOW 1+2 PROX SENS LGC/D2 ZONE 221 221 222 222 222 222 Subtask 32−31−01−010−001 B. Remove the access panel that follows: REFERENCE 221BZ DESIGNATION Access panel − center pedestal 2. Procedure Subtask 32−31−01−020−001 Refer to Figure 401. A. Remove the landing gear control handle (1) as follows: (1) Disconnect the electrical connector (2) from the receptacle on the bottom of landing gear control handle (1). (2) Install protective caps on the electrical connector (2) and on the receptacle on the bottom of the landing gear control handle (1). (3) Remove the two screws (3) that attach the knob (4) to the lever of the landing gear control handle (1). (4) Remove the knob (4). (5) Remove the screws (5), the washers (6), that attach the plastic lighting panel (7) to the mounting plate (10). Master EFFECTIVITY: See Pageblock 32−31−01 page 401 32−31−01 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (6) Remove the plastic lighting panel (7) from the mounting plate (10). (7) Remove the screws (8) and the washers (9) that attach the landing gear control handle (1) to the mounting plate (10). (8) Remove the landing gear control handle (1) from the cut−out in the mounting plate (10). Master EFFECTIVITY: See Pageblock 32−31−01 page 401 32−31−01 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A 3 4 7 5 6 LEGEND 1. Landing gear control handle. 2. Electrical connector. 3. Screw. 4. Knob. 5. Screw. 6. Washer. 7. Plastic lighting panel. 8. Screw. 9. Washer. 10. Mounting plate. 1 8 9 2 A ram3231014_001.dg, ik, 01/02/01 10 D FW Landing Gear Control Handle − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−31−01 page 401 32−31−01 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−31−01−400−801 Installation of the Landing Gear Control Handle 1. Job Set−Up Information Subtask 32−31−01−945−001 A. Parts REF 3 5 6 8 9 NAME OF PART Screw Screw Washer Screw Washer QTY 2 2 2 4 4 IPC SEQUENCE NO. IPC 32−31−01−01−082 IPC 32−31−01−01−010 IPC 32−31−01−01−015 IPC 32−31−01−01−075 IPC 32−31−01−01−080 Subtask 32−31−01−946−001 B. Reference Information REFERENCE TASK 32−30−00−720−801 DESIGNATION Functional Test of the Landing Gear Extension/Retraction System 2. Procedure Subtask 32−31−01−420−001 Refer to Figure 401. A. Install the landing gear control handle (1) as follows: (1) If installed, remove the two screws (3) that attach the knob (4) to the lever of the landing gear control handle (1). Remove the knob (4) from the lever of the landing gear control handle (1). (2) Put the landing gear control handle (1) in position in the cut−out of the mounting plate (10). (3) Attach the landing gear control handle (1) to the mounting plate (10) with the screws (8) and the washers (9). (4) Attach the plastic lighting panel (7) to the mounting plate (10), with the screws (5) and the washers (6). (5) Install the knob (4) on to the lever of the landing gear control handle (1) with the two screws (3). (6) Remove the protective caps from the electrical connector (2) and the receptacle on the bottom of the landing gear control handle (1). (7) Connect the electrical connector (2) to the landing gear control handle (1). Master EFFECTIVITY: See Pageblock 32−31−01 page 401 32−31−01 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. Close Out Subtask 32−31−01−865−002 A. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−4 CB NO. F6 F7 F9 P2 P3 B13 NAME PROX SENS LGC/D1 WOW1 PROX SENS WOW2 PROX SENS LGC/D1 PROX SENS LGC/D2 WOW 1+2 PROX SENS LGC/D2 ZONE 221 221 222 222 222 222 Subtask 32−31−01−720−001 B. Do a functional test of the extension and retraction system (Ref. TASK 32−30−00−720−801). Subtask 32−31−01−410−001 C. Install the access panel that follows: REFERENCE 221BZ DESIGNATION Access panel − center pedestal Master EFFECTIVITY: See Pageblock 32−31−01 page 401 32−31−01 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL LANDING GEAR CONTROL PANEL − ADJUSTMENT/TEST 1. General A. The maintenance procedure that follows is for the operational test of the switch/light (MUTE HORN) on the landing gear control panel. TASK 32−31−01−710−801 Operational Test of the Switch/Light (MUTE HORN) 1. Job Set−Up Information Subtask 32−31−01−946−003 A. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 10−11−00−000−801 TASK 10−11−00−000−802 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−803 TASK 12−00−06−863−804 TASK 12−00−07−861−801 TASK 12−00−07−861−802 TASK 27−54−00−866−802 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Removal of the Nose Landing Gear Lockpin Removal of the Main Landing Gear Lockpins Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 Connect External AC Power Remove External AC Power Electrical Retraction of the Flaps 2. Job Set−Up Subtask 32−31−01−861−001 A. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801). Subtask 32−31−01−582−001 B. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). Make sure that there is at least 4 inches (10 cm) of clearance between the tires and the ground. Subtask 32−31−01−861−002 C. Make sure that the LDG GEAR control handle is in the DN position and that the green−color DN indications are shown in the three GEAR boxes on the EICAS primary page. Master EFFECTIVITY: See Pageblock 32−31−01 page 501 501 32−31−01 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−31−01−090−002 D. Remove the safety lockpins from the nose landing gear and from the main landing gear (Ref. TASK 10−11−00−000−801 and TASK 10−11−00−000−802). Subtask 32−31−01−863−001 E. Pressurize hydraulic system No. 3 (Ref. TASK 12−00−06−863−803). Subtask 32−31−01−866−001 F. Make sure that the flaps are at 45 degrees (Ref. TASK 27−54−00−866−802). 3. Procedure Subtask 32−31−01−710−001 A. B. C. D. E. F. G. H. I. J. K. L. Put both the throttles above the idle position. NOTE: If necessary operate the gear UP/DN to complete the procedure that follows: Put the LDG GEAR control handle to the UP position. (1) The horn is heard when the gear is unlocked. Push the HORN MUTE switch. (1) The horn is heard (not mutable). (2) The switch/light is not ON. Move the flaps to zero degree. (1) The horn is not heard (horn muted) when the flaps are less than 30 degrees. (2) The switch/light is ON. Move the flaps to 45 degrees. (1) The horn is heard, when flaps are more than 30 degrees. Push the HORN MUTE switch. (1) The horn is heard (not mutable). Move the flaps to zero degree. (1) The horn is not heard (horn muted) when the flaps are less than 30 degrees. Put right throttle to idle position. (1) The horn is heard. Push HORN MUTE switch. (1) The horn is not heard (horn mutable). Put right throttle to above idle position. Put left throttle to idle position. (1) The horn is heard. Push HORN MUTE switch. (1) Horn is not heard (horn mutable). Master EFFECTIVITY: See Pageblock 32−31−01 page 501 502 32−31−01 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL 4. Close Out Subtask 32−31−01−840−002 A. Put the LDG GEAR control handle in the DN position and make sure that the NLG and the MLG are extended and locked in the down position, and that the green−color DN indications come into view in the three GEAR boxes on the EICAS primary page. Subtask 32−31−01−980−003 B. Move the throttle levers aft to the IDLE position again. Subtask 32−31−01−863−002 C. Release the pressure from hydraulic system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−31−01−867−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: D. Subtask 32−31−01−861−003 E. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802). Subtask 32−31−01−586−001 F. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−31−01−941−002 G. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−31−01 page 501 503 32−31−01 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL CONTROL HANDLE, LANDING GEAR − INSPECTION CHECK 1. General A. The maintenance procedure that follows gives the steps that are required to do an inspection for signs of cracks in the slider of the landing gear control handle. The slider is a part of the lever assembly in the landing gear control handle. TASK 32−31−01−290−801 Detailed Inspection of the Slider in the Landing Gear Control Handle 1. Reason for the Job Refer to MRM Part 2, AWL Supplementary Requirements R32−31−828−01. 2. Job Set−Up Information Subtask 32−31−01−943−001 A. Tools and Equipment REFERENCE GSB2000014 (or equivalent) None specified None specified None specified DESIGNATION Borescope kit Cotton swabs Magnifying glass (minimum 10X magnification) Portable light source Subtask 32−31−01−945−002 B. Parts REF 2 Screw 4 Screw 5 Washer NAME OF PART QTY 2 2 2 IPC SEQUENCE NO. IPC 32−31−01−01−082 IPC 32−31−01−01−010 IPC 32−31−01−01−015 Subtask 32−31−01−946−002 C. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−31−01−000−801 TASK 32−31−01−400−801 DESIGNATION Removal of the Nose Landing Gear Lockpin Removal of the Main Landing Gear Lockpins Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Removal of the Landing Gear Control Handle Installation of the Landing Gear Control Handle Master EFFECTIVITY: See Pageblock 32−31−01 page 601 32−31−01 Page 601 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. Job Set−Up Refer to Figure 601. Subtask 32−31−01−490−001 WARNING: A. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Subtask 32−31−01−865−003 B. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−4 CB NO. F6 F7 F9 P2 P3 B13 NAME PROX SENS LGC/D1 WOW1 PROX SENS WOW2 PROX SENS LGC/D1 PROX SENS LGC/D2 WOW 1+2 PROX SENS LGC/D2 ZONE 221 221 222 222 222 222 Subtask 32−31−01−840−001 C. Make sure that the lever assembly (1) is in the DN position. Subtask 32−31−01−900−001 D. E. F. Remove the two screws (2) that attach the knob (3) to the lever assembly (1). Remove the knob (3) from the lever assembly (1). Remove the screws (4) and the washers (5) that attach the plastic lighting panel (6) to the landing gear control handle (7). Remove the plastic lighting panel (6) from the landing gear control handle (7). Temporarily install the knob (3) on the lever assembly (1) again and secure it with the two screws (2). 4. Procedure Refer to Figure 601. Subtask 32−31−01−290−001 A. Do a visual inspection of the slider (8) of the lever assembly (1) as follows: (1) Move the red DN LCK REL lever (9) aft to manually retract the lock−out latch (10) from the lever assembly (1). NOTE: Keep the lock−out latch (10) in this position during the procedure that follows. This will allow the lever assembly (1) to be able to move freely up or down so that all of the slider (8) can be seen from both sides of the inspection hole. Master EFFECTIVITY: See Pageblock 32−31−01 page 601 32−31−01 Page 602 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL WARNING: (2) (3) (4) (5) DO NOT MOVE THE LANDING GEAR CONTROL LEVER FROM THE ‘LANDING GEAR DN’ POSITION WHEN YOU LIFT UP THE KNOB ON THE LEVER ASSEMBLY. IF THE AIRCRAFT IS NOT IN THE CORRECT CONFIGURATION, THE LANDING GEAR CAN ACCIDENTALLY RETRACT. DAMAGE TO EQUIPMENT AND INJURY TO PERSONS CAN OCCUR. Gently pull up on the knob (3), in−line with the axis of the lever assembly (1) until the critical inspection area of the slider (8) can be seen through the inspection hole in the outer tube (11). Do the steps that follow to inspect the slider (8) for cracks: NOTE: In the steps that follow, make sure that you carefully inspect the area that is adjacent to the notch in the slider (8). (a) Make sure that you can see the notch and adjacent surfaces in the slider (8) through the inspection hole. NOTE: Move the lever assembly (1) up or down as necessary (in−line with the axis of the lever assembly (1)) to get a clear view of this area. NOTE: If necessary, clean the area that is adjacent to the notch with a cotton swab to remove any grease or other unwanted contaminants. (b) Examine the surfaces that are adjacent to the notch for cracks with a magnifying glass (with a portable light source) or with a borescope. NOTE: The magnifying glass or the borescope must have a minimum of 10X magnification. NOTE: The slider (8) has a solid film lubricant finish. A crack will appear as a dark line or a point of contrast. (c) Examine the radius at the base of the notch in the slider (8) with the magnifying glass or with the borescope. (d) Examine the flat sides of the slider (8) with the magnifying glass or with the borescope. Make sure that you carefully examine the part of the flat side of the slider (8) that is immediately adjacent to the radius at the base of the notch. NOTE: Use the portable light source together with the magnifying glass or use the borescope with the light source that is included in the borescope kit. The examination must be done one side of the slider (8) at a time. NOTE: The slider (8) has a solid film lubricant finish. A crack will appear as a dark line or a point of contrast from the radius of the notch. If there is any visual evidence of a crack in the slider (8), remove and replace the landing gear control handle (7) (Ref. TASK 32−31−01−000−801 and TASK 32−31−01−400−801) and remove the unserviceable landing gear control handle (7) from service. If there was no visual evidence of a crack in the slider (8), do the steps that follow: (a) Gently push down on the knob (3) (in−line with the axis of the lever assembly (1)) to move the lever assembly (1) to the set detent position. (b) Make sure that the red DN LCK REL lever (9) moves forward to the locked position and that the lock−out latch (10) is engaged in the lever assembly (1). Master EFFECTIVITY: See Pageblock 32−31−01 page 601 32−31−01 Page 603 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 5. Close Out Refer to Figure 601. Subtask 32−31−01−900−002 A. If there was no visual evidence of a crack in the slider (8) and you did not need to remove and replace the landing gear control handle (7), do the steps that follow: (1) Remove the two screws (2) that attach the knob (3) to the lever assembly (1). (2) Remove the knob (3) from the lever assembly (1). (3) Put the plastic lighting panel (6) in position on the landing gear control handle (7). (4) Install the knob (3) on the lever assembly (1) again and secure it with the two screws (2). (5) Secure the plastic lighting panel (6) to the landing gear control handle (7) with the screws (4) and the washers (5). Subtask 32−31−01−865−004 B. If there was no visual evidence of a crack in the slider (8) and you did not need to remove and replace the landing gear control handle (7), remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−4 CB NO. F6 F7 F9 P2 P3 B13 NAME PROX SENS LGC/D1 WOW1 PROX SENS WOW2 PROX SENS LGC/D1 PROX SENS LGC/D2 WOW 1+2 PROX SENS LGC/D2 ZONE 221 221 222 222 222 222 Subtask 32−31−01−090−001 C. Remove the safety lockpins from the nose landing gear and from the main landing gear (Ref. TASK 10−11−00−000−801 and TASK 10−11−00−000−802). Subtask 32−31−01−941−001 D. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−31−01 page 601 32−31−01 Page 604 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A 2 3 6 4 4 LEGEND 1. Lever assembly. 2. Screw. 3. Knob. 4. Screw. 5. Washer. 6. Plastic lighting panel. 7. Landing gear control handle. 9. DN LCK REL lever. 10. Lock−out latch. 5 5 1 7 D FW 10 9 A ram3231015_001.dg, ik/kms, 01/02/01 B Detailed Inspection of the Slider Figure 601 (Sheet 1 of 2) Master EFFECTIVITY: See Pageblock 32−31−01 page 601 32−31−01 Page 605 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 11 CRITICAL AREA NOTCH RADIUS 8 FWD C EXTENDED RETRACTED B LEGEND 8. Slider. 11. Outer tube. ram3231015_002.dg, ik, 31/10/00 INSPECTION HOLE (REF) C Detailed Inspection of the Slider Figure 601 (Sheet 2 of 2) Master EFFECTIVITY: See Pageblock 32−31−01 page 601 32−31−01 Page 606 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL MAIN LANDING GEAR EXTENSION/RETRACTION − DESCRIPTION AND OPERATION 1. 2. General A. Normal control of the landing gear is through the operation of the selector lever on the center pedestal. The main landing gear (MLG) is retracted in the inboard direction and locked into a wheel bay located in the center fuselage. The MLG is hydraulically extended in the outboard direction and locked into the vertical position for landing. The MLG extension and retraction system includes the components that follow: ± MLG side stay actuator ± MLG uplock assembly ± MLG selector valve ± Priority valve ± Runaround and bypass valve ± Check valve ± Restrictor. Component Details Refer to Figure 1, Figure 2, and Figure 3. A. MLG Side Stay Actuator (1) The MLG side stay actuator is a two position actuator, used to extend and retract the main landing gear. Each actuator is attached, at one end to the main structure and at the other end to the main beam assembly. Each assembly includes a cylinder, a piston and an internal locking mechanism. (a) The cylinder is a steel part which includes a self aligning bearing, two hydraulic ports and a restrictor. One cylinder port is used for fluid flow to extend the actuator piston, while the other port is used to move fluid to the retract port on the rod end cap. The restrictor is installed in the retract port and is used to control the speed of the actuator during landing gear retraction. For gear extension hydraulic pressure is supplied to the extend port only. (b) The piston is a chromed steel part installed coaxially through the cylinder assembly. An attachment fitting with a self aligning bearing is installed in the piston end. (c) The actuator locking mechanism, which is installed inside the head of the piston, is used to lock the landing gear in the extend position. It contains four locking segments, a locking piston, two springs, and pressure seals. B. MLG Uplock Assembly (1) Each uplock assembly includes a latch, an uplock lever, an actuator, and a manual release lever all installed between two side plates. The uplock assemblies are used to lock the landing gear in the retracted position. They are attached to the bulkhead in the main gear bay. In normal mode of operation, the uplock assembly is mechanically locked in the up position and hydraulically released from this uplocked position. Master EFFECTIVITY: See Pageblock 32−32−00 page 1 32−32−00 Page 1 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. (a) A mount bracket for the proximity sensor is installed on the exterior surface of the side plate. The mechanical linkage for the uplock lever is installed horizontally through the uplock assembly. Attached to the end of this mechanical linkage is the target lever attachment. A pin installed in the uplock lever is used as an attachment point for two tension springs. (b) The uplock release actuator is used to release the mechanical uplock and permit the landing gear to be extended. Each actuator has two ports, the rod end port and the piston head port. The rod end port is always pressurized, while the piston head port is pressurized only during the landing gear release. (c) When the uplock release actuator is fully pressurized by system No. 3, the actuator piston extends and moves the uplock lever. As the uplock lever moves, it pushes up and lifts the roller out of engagement with the latch. The weight of the landing gear continues to turn the latch until the landing gear is free to fall to the down and locked position. (d) As the landing gear retracts, the gear uplock pin will make contact with the uplock latch. This movement causes the latch to turn. When the latch has moved the necessary distance, the roller will engage with the latch and safety the gear in the locked position. C. MLG Selector Valve (1) The MLG selector valve is a four way, three position, solenoid operated valve, which sends hydraulic pressure to the extend or retract hydraulic lines. Each valve has two solenoids, solenoid A and solenoid B. The selector valve is installed on the lower surface of the hydraulic beam in the MLG wheel bay. D. MLG Priority Valve (1) The priority valve is used to make sure that the flight controls have priority on hydraulic pressure during retraction of the landing gear. The MLG priority valve is installed on the aft bulkhead of the MLG bay. E. MLG Runaround and Bypass Valve (1) The runaround and bypass valve is used to release hydraulic pressure from the MLG side stay actuator actuator during manual extension. The bypass valve is also used to decrease the work load on the hydraulic pump during gear extension by the circulation of return fluid to the gear−up lines. The runaround and bypass valve is installed on the upper surface of the keel beam in the MLG bay. Operation A. MLG Extension (1) When the pilot sets the selector lever to the LANDING GEAR DN position, the extend signal is sent to the proximity sensing electronic unit (PSEU). The PSEU will then receive and analyze the input signals from the landing gear and other aircraft systems to control the actuation of the landing gear. (2) The PSEU will then supply an electrical signal to operate the MLG selector valve to the down position. Hydraulic fluid from system No. 3 is sent through the priority valves to the main gear selector valve. (3) Hydraulic fluid is then sent through a check valve and a restrictor in the runaround and bypass valve to the MLG uplock release actuator. (4) At the same time, hydraulic fluid is sent to the extend side of the MLG side stay actuator. When the gear is fully extended, the internal downlock mechanism in the Master EFFECTIVITY: See Pageblock 32−32−00 page 1 32−32−00 Page 2 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 4. MLG side stay actuator, automatically locks the gear in the down position. B. MLG Retraction (1) When the pilot sets the selector valve to the LANDING GEAR UP position, the retract signal is sent to the PSEU. If all of the necessary input signals are present, the PSEU will then send the necessary output signals to operate the gear to the retract position. (2) The PSEU will receive input signals, analyzes them, and then gives output signals to other aircraft systems. The PSEU will first energize the main gear selector valve to the up position. (3) Hydraulic fluid from system No. 3 is sent through the priority valve to the MLG selector valve. The selector valve opens and permits fluid to flow through the retract lines to the MLG side stay actuator and to the uplock release actuator. (4) To decrease the work load on the hydraulic pumps, the runaround and bypass valve moves the flow of fluid from the MLG side stay actuators back to the gear retract lines. (5) When the landing gear is fully retracted the uplock pin on the lower shock strut connects with the gear uplock and when fully engaged, safeties the landing gear for flight. Component Location Index COMPONENT NAME MLG side stay actuator MLG uplock assembly MLG selector valve Priority valve Runaround and bypass valve Check valve Restrictor QTY 2 2 1 1 1 1 1 Master EFFECTIVITY: See Pageblock 32−32−00 page 1 ACCESS/ZONE MLG bay MLG bay MLG bay MLG bay MLG bay MLG bay MLG bay REFERENCE 32−32−01 32−32−05 32−32−10 32−32−15 32−32−20 32−32−25 32−32−30 32−32−00 Page 3 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A ram3232000_001.dg, as, 02/10/01 MLG SIDE STAY ACTUATOR A MLG Side Stay Actuator Figure 1 Master EFFECTIVITY: See Pageblock 32−32−00 page 1 32−32−00 Page 4 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TARGET MANUAL RELEASE LEVER UPLOCK LEVER TENSION SPRING LATCH MAIN LANDING GEAR UPLOCK ASSEMBLY ram3232000_002.dc, rb/pb, 24/08/92 UPLOCK RELEASE ACTUATOR MLG Uplock Assembly Figure 2 Master EFFECTIVITY: See Pageblock 32−32−00 page 1 32−32−00 Page 5 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL B A MLG PRIORITY VALVE B RUNAROUND/BYPASS VALVE FWD C MLG SELECTOR VALVE ram3232000_003.dc, rf/pb, 24/08/92 A C MLG Extension/Retraction − Component Location Figure 3 Master EFFECTIVITY: See Pageblock 32−32−00 page 1 32−32−00 Page 6 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL ACTUATOR, MAIN LANDING GEAR (MLG) SIDE STAY− REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the side stay actuator for the main landing gear (MLG). TASK 32−32−01−000−801 Removal of the MLG Side Stay Actuator 1. Job Set−Up Information Subtask 32−32−01−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Container, hydraulic fluid, phosphate ester resistant Subtask 32−32−01−946−001 B. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 29−00−00−910−801 TASK 32−61−05−000−802 DESIGNATION Put the Aircraft on Jacks Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpin Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions Removal of the Proximity Sensor − MLG Downlock 2. Job Set−Up Subtask 32−32−01−941−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. Master EFFECTIVITY: See Pageblock 32−32−01 page 401 32−32−01 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−32−01−910−001 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: B. Subtask 32−32−01−865−001 C. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−32−01−582−001 D. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). Subtask 32−32−01−863−001 E. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−32−01−010−001 F. Remove the two MLG downlock proximity sensors and their related harnesses from the MLG side stay actuator (Ref. TASK 32−61−05−000−802). 3. Procedure Subtask 32−32−01−020−001 Refer to Figure 401. A. Remove the side stay actuator (3) as follows: (1) Put the hydraulic fluid container below the work area. (2) Disconnect the hydraulic lines (1) and (2) from the side stay actuator (3). Install protective caps on all open hydraulic lines and ports. (3) Remove and discard the cotter pin (4). (4) Remove the nut (5), the washer(s) (6), and the bolt (7). (5) Remove the side stay nut (8). Do not disconnect the side stay actuator (3) from the side stay pin at this time. (6) Remove and discard the cotter pin (9). (7) Remove the nut (10) and the washer (11). (8) Carefully remove the side stay actuator (3) and the washer (12). (9) Drain the hydraulic fluid from the side stay actuator (3) into the hydraulic fluid container. Master EFFECTIVITY: See Pageblock 32−32−01 page 401 32−32−01 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL B A 2 1 C 11 10 9 12 3 B 1. Hydraulic line. 2. Hydraulic line. 3. Side stay actuator. 4. Cotter pin. 5. Nut. 6. Washer. 7. Bolt. 8. Sidestay nut. 9. Cotter pin. 10. Nut. 11. Washer. 12. Washer. A 3 7 8 6 6 4 5 C ram3232014_001(1).dg, as, 03/10/01 LEGEND. MLG Side Stay Actuator − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−32−01 page 401 32−32−01 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−32−01−400−801 Installation of the MLG Side Stay Actuator 1. Job Set−Up Information Subtask 32−32−01−943−002 A. Tools and Equipment REFERENCE None specified None specified DESIGNATION Torque wrench, torque range 0 to 50 lbf·in (0 to 10 N·m) Torque wrench, torque range 1000 to 1500 lbf·in (0 to 150 N·m) Subtask 32−32−01−944−001 B. Consumable Materials REFERENCE None specified DESIGNATION Paint, red Subtask 32−32−01−945−001 C. Parts REF 4 5 6 7 8 9 10 11 12 NAME OF PART Cotter pin Nut Washer Bolt Side stay nut Cotter pin Nut Washer Washer QTY 1 1 AR 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−32−01−01−060 IPC 32−32−01−01−070 IPC 32−32−01−01−055 IPC 32−32−01−01−045 IPC 32−32−01−01−050 IPC 32−32−01−01−030 IPC 32−32−01−01−015 IPC 32−32−01−01−020 IPC 32−32−01−01−025 Subtask 32−32−01−946−002 D. Reference Information REFERENCE TASK 07−11−01−582−804 TASK 12−20−32−640−802 TASK 29−10−00−870−803 TASK 32−00−00−790−801 TASK 32−30−00−720−801 DESIGNATION Removal of the Aircraft from Jacks Lubrication of the Main Landing Gear Bleed Hydraulic System No. 3 External Leak Check of the Landing Gear Functional Test of the Landing Gear Extension/Retraction System Master EFFECTIVITY: See Pageblock 32−32−01 page 401 404 32−32−01 SepPage 10/2004 C AIRCRAFT MAINTENANCE MANUAL REFERENCE TASK 32−61−05−400−802 DESIGNATION Installation of the Proximity Sensor − MLG Downlock 2. Job Set−Up Subtask 32−32−01−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. 3. Procedure Subtask 32−32−01−420−001 Refer to Figure 401. A. Install the side stay actuator (3) as follows: NOTE: If necessary, extend the side stay actuator (3) before installation. (1) Install the washer (12) on the support pin. (2) Install the cylinder end of the side stay actuator (3) on the support pin and attach it with the washer (11) and the nut (10). Torque the nut (10) from 360.04 to 1200.15 lbf·in (40.68 to 135.6 N·m). NOTE: If necessary, you can loosen the nut (10) to the next nearest bolt hole to align the cotter pin holes. (3) Safety the nut (10) with the cotter pin (9). (4) Paint a red stripe adjacent to the nut (10). (5) Install the piston end of the side stay actuator (3) on the side stay pin and attach it with the side stay nut (8). Torque the side stay nut (8) from 1100 to 1200 lbf·in (124.3 to 135.6 N·m). NOTE: If necessary, you can loosen the side stay nut (8) to the next nearest bolt hole to align the holes to install the bolt (7). It is permitted for the torque value of the side stay nut (8) to reach zero. (6) Install the bolt (7) and the washer(s) (6) (if required) through the side stay nut (8) and then install the washer(s) (6) and the nut (5). Torque the nut (5) from 30 to 35 lbf·in (3.39 to 3.95 N·m). NOTE: Use a combination of washers (6) to make sure that the nut (5) can be safetied correctly as follows: ± A maximum of two washers can be under the nut (5) ± A maximum of two washers can be under the head of the bolt (7). (7) Safety the nut (5) with the cotter pin (4). (8) Paint a red stripe adjacent to the nut (5). (9) Remove the protective caps from the hydraulic lines. Connect the hydraulic lines (1) and (2) to the side stay actuator (3). Master EFFECTIVITY: See Pageblock 32−32−01 page 401 405 32−32−01 SepPage 10/2004 C AIRCRAFT MAINTENANCE MANUAL 4. Close Out Subtask 32−32−01−410−001 A. Install the MLG downlock proximity switches and their related harnesses on the MLG side stay actuator (Ref. TASK 32−61−05−400−802). Subtask 32−32−01−640−001 B. Lubricate the MLG side stay actuator (Ref. TASK 12−20−32−640−802). Subtask 32−32−01−865−002 C. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−32−01−870−001 D. Bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−32−01−710−001 E. Do a functional test of the extension and retraction system (Ref. TASK 32−30−00−720−801). Subtask 32−32−01−210−001 F. Examine the side stay actuator and related connections for hydraulic leaks (Ref. TASK 32−00−00−790−801). Subtask 32−32−01−941−002 G. Remove all tools, equipment, and unwanted materials from the work area. Subtask 32−32−01−586−001 H. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Master EFFECTIVITY: See Pageblock 32−32−01 page 401 406 32−32−01 SepPage 10/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL UPLOCK ASSEMBLY, MLG − REMOVAL/INSTALLATION 1. General A. The maintenance procedure that follows is for the removal and installation of the uplock assembly of the main landing gear (MLG). There are two uplock assemblies installed on the left and right pressure bulkhead walls of the main wheel well. B. The removal and installation procedure for the MLG uplock assemblies is the same. TASK 32−32−05−000−801 Removal of the MLG Uplock Assembly 1. Job Set−Up Information Subtask 32−32−05−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Container, fluid Subtask 32−32−05−946−001 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 29−00−00−910−801 TASK 53−83−01−000−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions Removal of the MLG Wheel Bin 2. Job Set−Up Subtask 32−32−05−910−001 WARNING: A. OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). Master EFFECTIVITY: See Pageblock 32−32−05 page 401 32−32−05 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−32−05−490−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: B. Subtask 32−32−05−865−001 C. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−32−05−863−001 D. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−32−05−010−001 E. Remove the applicable MLG wheel bin (Ref. TASK 53−83−01−000−801). 3. Procedure Subtask 32−32−05−020−001 Refer to Figure 401. A. Remove the MLG uplock assembly as follows: NOTE: Right side components are given in brackets. (1) Put the fluid container below the work area. (2) Remove the lockwire from the nuts (1) and (2) of the PS11GA (PS7GA) proximity sensor (3). (3) Remove the nut (1) and remove the PS11GA (PS7GA) proximity sensor (3) (with a nut (2) and a keywasher (4) still attached) from the mounting bracket on the MLG uplock assembly (5). (4) Temporarily install the nut (1) on to the PS11GA (PS7GA) proximity sensor (3) to retain the keywasher (4). (5) Disconnect the hydraulic lines (6) from the MLG uplock assembly (5). Install protective caps on all open hydraulic lines and/or ports. (6) Remove and discard the cotter pins (7). (7) Remove the nuts (8), and the bolts (9). Make sure the spacers (10) and (11) are not removed. Master EFFECTIVITY: See Pageblock 32−32−05 page 401 32−32−05 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (8) (9) (10) (11) Remove the MLG uplock assembly (5) from between the structural fittings. Remove and discard the cotter pin (12). Remove the washer (13), the pin (14), the spacers (15). Remove the uplock assembly (5). Master EFFECTIVITY: See Pageblock 32−32−05 page 401 32−32−05 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND A 11. Spacer. 12. Cotter pin. 13. Washer. 14. Pin. 15. Spacer. 16. Release lever. 17. Link−lock release. 1. Nut. 2. Nut. 3. PS11GA (LH) proximity sensor. 4. Keywasher. 5. MLG uplock assembly. 6. Hydraulic lines. 7. Cotter pin. 8. Nut. 9. Bolt. 10. Spacer. A 3 FW D 3 B 1 PS11GA (LH) (PS7GA) 5 6 2 4 1 1 NOTE Right proximity sensor identification shown in brackets. 16 12 17 9 MOUNTING BRACKET (REF) 13 15 14 0.035 − 0.045 in. (0.9 − 1.14 mm) 8 10 8 7 B A 7 ram3232054_001(2).dc, dm/rm, 03/04/97 11 MLG Uplock Assembly − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−32−05 page 401 32−32−05 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−32−05−400−801 Installation of the MLG Uplock Assembly 1. Job Set−Up Information Subtask 32−32−05−944−001 A. Consumable Material REFERENCE 05−004 DESIGNATION Lockwire Subtask 32−32−05−945−001 B. Parts REF 1 2 4 7 8 9 10 11 12 13 14 15 NAME OF PART Nut Nut Keywasher Cotter pin Nut Bolt Spacer Spacer Cotter pin Washer Pin Spacer QTY 1 1 1 2 2 2 1 1 1 1 1 2 IPC SEQUENCE NO. IPC 32−61−05−01−035 IPC 32−61−05−01−035 IPC 32−61−05−01−030 IPC 32−32−05−01−035 IPC 32−32−05−01−030 IPC 32−32−05−01−015 IPC 32−32−05−01−025 IPC 32−32−05−01−020 IPC 32−34−00−03−270 IPC 32−34−00−03−265 IPC 32−34−00−03−245 IPC 32−34−00−03−250 Subtask 32−32−05−946−002 C. Reference Information REFERENCE TASK 29−10−00−870−803 TASK 32−00−00−790−801 TASK 32−30−00−720−801 TASK 32−34−00−710−801 TASK 32−61−00−710−801 TASK 53−83−01−400−801 DESIGNATION Bleed Hydraulic System No. 3 External Leak Check of the Landing Gear Functional Test of the Landing Gear Extension/Retraction System Operational Test of the Landing Gear Manual−Release−System Operational Test of the PSS Installation of the MLG Wheel Bin Master EFFECTIVITY: See Pageblock 32−32−05 page 401 32−32−05 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 2. Procedure Subtask 32−32−05−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Subtask 32−32−05−420−001 Refer to Figure 401. B. Install the MLG uplock assembly as follows: NOTE: Right side components are given in brackets. (1) Put the spacers (15) on each side of the link−lock release (17). Align the spacers (15) with the release lever (16) and the link−lock release (17). Install the pin (14), the washer (13), and the cotter pin (12). (2) Put the uplock assembly (5) between the fittings and align the uplock assembly (5) with the attaching holes. Install the uplock assembly (5) with the bolts (9), the nuts (8), and the cotter pins (7). (3) Remove the protective caps from the hydraulic lines and/or ports. (4) Connect the hydraulic lines (6). (5) Remove the nut (1) from the PS11GA (PS7GA) proximity sensor (3). (6) Loosely install the PS11GA (PS7GA) proximity sensor (3) with the nut (2) and the keywasher (4) in the mounting bracket. NOTE: Make sure that the locking tab on the keywasher (4) under the nut (2) is engaged in the mounting bracket for the PS11GA (PS7GA) proximity sensor (3). (7) Loosely install the nut (1). Subtask 32−32−05−820−002 C. If necessary, adjust the sensor−to−target clearance as follows: (1) Manually close the uplock latch to adjust the PS11GA (PS7GA) proximity sensor (3) with its target. NOTE: Make sure that the uplock latch is unlocked after the adjustment is done. (2) Adjust the nuts (1) and (2) to get a sensor−to−target clearance of 0.035 to 0.045 inch (0.9 mm to 1.14 mm). NOTE: Each turn of the adjusting nuts (1) and (2) increases or decreases the sensor−to−target clearance by 0.042 inch (1.07 mm). (3) Manually move the manual release lever (in the MLG bay) to unlock the MLG uplock latches. (4) Safety the two adjusting nuts (1) and (2) together with 05−004 lockwire. Master EFFECTIVITY: See Pageblock 32−32−05 page 401 32−32−05 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. Close Out Subtask 32−32−05−160−001 A. Clean all signs of hydraulic fluid from the uplock assembly and the surrounding area. Subtask 32−32−05−941−002 B. Remove all tools, equipment, and unwanted materials from the work area. Subtask 32−32−05−865−002 C. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−32−05−870−001 D. Bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−32−05−750−001 E. Do the operational test of the proximity sensor system (Ref. TASK 32−61−00−710−801). Subtask 32−32−05−720−002 F. Do a functional test of the extension and retraction system (Ref. TASK 32−30−00−720−801). Subtask 32−32−05−710−001 G. Do an operational test of the manual release system of the landing gear (Ref. TASK 32−34−00−710−801). Subtask 32−32−05−210−001 H. Examine the work area for leaks (Ref. TASK 32−00−00−790−801). Subtask 32−32−05−410−001 I. Install the applicable MLG wheel bin (Ref. TASK 53−83−01−400−801). Master EFFECTIVITY: See Pageblock 32−32−05 page 401 32−32−05 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL VALVE, MAIN LANDING GEAR SELECTOR − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the main−landing−gear (MLG) selector valve (written as the ‘selector valve’ in this procedure). The selector valve is installed in the main wheel well, on the aft end of the hydraulic beam. TASK 32−32−10−000−801 Removal of the Main Landing Gear Selector Valve 1. Job Set−Up Information Subtask 32−32−10−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Container, fluid Subtask 32−32−10−946−001 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 29−00−00−910−801 TASK 53−83−01−000−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions Removal of the MLG Wheel Bin 2. Job Set−Up Subtask 32−32−10−490−001 WARNING: A. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Master EFFECTIVITY: See Pageblock 32−32−10 page 401 32−32−10 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−32−10−910−001 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: B. Subtask 32−32−10−865−001 C. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CB NO. A2 F6 G11 A2 G15 P2 NAME HYD PUMP 3B PROX SENS LGC/D1 HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A PROX SENS LGC/D1 ZONE 221 221 221 222 222 222 Subtask 32−32−10−010−001 D. Remove the left wheel bin (Ref. TASK 53−83−01−000−801). Subtask 32−32−10−863−001 E. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). 3. Procedure Subtask 32−32−10−030−001 Refer to Figure 401. A. Put a fluid container below the work area. B. Disconnect the electrical connector from the solenoid on the selector valve (1). Install protective caps on the electrical connector and the solenoid receptacle. C. Disconnect the hydraulic lines from the selector valve (1). Install protective plugs and caps on all open hydraulic lines and ports. Subtask 32−32−10−020−001 D. E. F. Remove the nut (2), the washers (3) and (4), and the bolt (5). Remove the nuts (6), the washers (7), and the bolts (8). Remove the selector valve (1). Master EFFECTIVITY: See Pageblock 32−32−10 page 401 32−32−10 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−32−10−030−002 G. H. If necessary (for installation to a new selector valve), remove the restrictors (9) and (10), the reducer (11), and the check valve (12). Remove and discard the preformed packings (13). Master EFFECTIVITY: See Pageblock 32−32−10 page 401 32−32−10 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Selector valve. 2. Nut. 3. Washer. 4. Washer. 5. Bolt. 6. Nut. 7. Washer. 8. Bolt. 9. Restrictor. 10. Restrictor. 11. Reducer. 12. Check valve. 13. Preformed packing. A 6 7 HYDRAULIC BEAM (REF.) 2 3 HYDRAULIC LINE (DOWN−C1) 10 HYDRAULIC LINE (UP−C2) 11 13 13 8 13 13 12 C2 HYDRAULIC LINE (RETURN) HYDRAULIC LINE (PRESSURE) 4 1 5 RTN A ELECTRICAL CONNECTOR (REF.) ram3232104_001(2).dc, rt, 14/07/95 9 Main Landing Gear Selector Valve − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−32−10 page 401 32−32−10 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−32−10−400−801 Installation of the Main Landing Gear Selector Valve 1. Job Set−Up Information Subtask 32−32−10−944−001 A. Consumable Materials REFERENCE 02−001 DESIGNATION Hydraulic fluid, phosphate ester base Subtask 32−32−10−945−001 B. Parts REF 1 2 3 4 5 6 7 8 9 10 11 12 NAME OF PART Selector valve Nut Washer Washer Bolt Nut Washer Bolt Restrictor Restrictor Reducer Check valve 13 Preformed Packing QTY 1 1 1 1 1 3 3 3 1 1 1 1 4 IPC SEQUENCE NO. IPC 32−32−10−01−040 IPC 32−32−10−01−035 IPC 32−32−10−01−030 IPC 32−32−10−01−025 IPC 32−32−10−01−020 IPC 32−32−10−01−035 IPC 32−32−10−01−030 IPC 32−32−10−01−015 IPC 32−32−10−01−050 IPC 32−32−10−01−095 IPC 32−32−10−01−080 IPC 32−32−10−01−065 IPC 32−32−10−01−045 IPC 32−32−10−01−060 IPC 32−32−10−01−075 IPC 32−32−10−01−090 Subtask 32−32−10−946−002 C. Reference Information REFERENCE TASK 29−10−00−870−803 TASK 32−30−00−720−801 TASK 51−80−00−100−802 TASK 53−83−01−400−801 DESIGNATION Bleed Hydraulic System No. 3 Functional Test of the Landing Gear Extension/Retraction System Surface Preparation for Electrical Bonding Installation of the MLG Wheel Bin Master EFFECTIVITY: See Pageblock 32−32−10 page 401 32−32−10 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 2. Job Set−Up Subtask 32−32−10−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. 3. Procedure Subtask 32−32−10−430−001 Refer to Figure 401. A. Install the restrictors (9) and (10), the reducer (11), and the check valve (12) on the selector valve (1) as follows: (1) Lightly lubricate the preformed packings (13) with clean hydraulic fluid and install them on the restrictors (9) and (10), the reducer (11), and the check valve (12). NOTE: Make sure that you install all of the preformed packings on the ends of the fittings that go into the selector valve. (2) Install the restrictor (9) in the port identified as PRESS on the selector valve. (3) Install the restrictor (10) in the port identified as C1 on the selector valve (1). NOTE: Make sure that the flow−arrow on the restrictor (10) points into the selector valve (1). (4) Install the reducer (11) in the port identified as C2 on the selector valve (1). (5) Install the check valve (12) in the port identified as RTN on the selector valve. NOTE: Make sure that the flow−arrow on the check valve (12) points away from the selector valve (1). Subtask 32−32−10−100−001 B. Make sure that the contact surfaces of the selector valve (1) and the mounting bracket at the forward−left mounting point are prepared to give a good electrical bond (Ref. TASK 51−80−00−100−802). Subtask 32−32−10−420−001 C. Install the selector valve (1) as follows: (1) Put the selector valve (1) on the hydraulic beam with the RTN port at the aft position. (2) On the aft−right mounting−point of the selector valve (1), install the bolt (5), the washers (4) and (3), and the nut (2). NOTE: Install the washer (4) under the head of the of the bolt (5) with the countersink of the washer facing the bolt head. (3) On the remaining mounting−positions, install the bolts (8), the washers (7), and the nuts (6). Master EFFECTIVITY: See Pageblock 32−32−10 page 401 32−32−10 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−32−10−430−002 D. Connect the hydraulic lines to the ports of the selector valve (1) as follows: (1) Remove the protective caps and plugs from the hydraulic lines and ports. (2) Connect the MLG DOWN line to the C1 port on the selector valve. (3) Connect the MLG UP line to the C2 port on the selector valve. (4) Connect the MLG PRESSURE line to the PRESS port on the selector valve. (5) Connect the MLG RETURN line to the RTN port on the selector valve. (6) Remove the protective caps from the electrical connector and valve solenoid. (7) Connect the electrical connector to the solenoid. 4. Close Out Subtask 32−32−10−140−001 A. Remove the fluid container and clean all signs of hydraulic fluid from the work area. Subtask 32−32−10−865−002 B. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CB NO. A2 F6 G11 A2 G15 P2 NAME HYD PUMP 3B PROX SENS LGC/D1 HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A PROX SENS LGC/D1 ZONE 221 221 221 222 222 222 Subtask 32−32−10−870−001 C. Bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−32−10−941−002 D. Remove all tools, equipment, and unwanted materials from the work area. Subtask 32−32−10−720−001 E. Do a functional test of the landing gear extension and retraction system (Ref. TASK 32−30−00−720−801). Subtask 32−32−10−210−001 F. Examine the work area for leaks. Master EFFECTIVITY: See Pageblock 32−32−10 page 401 32−32−10 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−32−10−410−001 G. Install the left wheel bin (Ref. TASK 53−83−01−400−801). Master EFFECTIVITY: See Pageblock 32−32−10 page 401 32−32−10 Page 408 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL VALVE, MLG PRIORITY − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the main−landing−gear priority valve. The priority valve is installed in the main wheel well, on the center of the aft pressure bulkhead. TASK 32−32−15−000−801 Removal of the MLG Priority Valve 1. Job Set−Up Information Subtask 32−32−15−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Container, fluid − phosphate−ester−base hydraulic−fluid resistant Subtask 32−32−15−946−001 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 29−00−00−910−801 TASK 53−83−01−000−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions Removal of the MLG Wheel Bin 2. Job Set−Up Subtask 32−32−15−490−004 WARNING: MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. A. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: MAKE SURE THAT THE WHEEL CHOCKS ARE PUT AT THE MAIN WHEELS. IF YOU DO NOT DO THIS, THE AIRCRAFT CAN MOVE. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. B. Install the wheel chocks. Master EFFECTIVITY: See Pageblock 32−32−15 page 401 32−32−15 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL WARNING: C. OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). Subtask 32−32−15−863−005 D. Release the pressure from hydraulic system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−32−15−865−003 E. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−32−15−010−001 F. Remove the left wheel bin (Ref. TASK 53−83−01−000−801). 3. Procedure **ON A/C 7004−7010, 7012, 7014, 7016, 7021, 7023−7024 Pre SB601R−32−008 Subtask 32−32−15−020−003 Refer to Figure 401. A. Put the fluid container below the work area. B. Remove the priority valve (1) as follows: (1) Disconnect the hydraulic lines (2). Install protective caps and plugs on the open hydraulic lines and ports. (2) Remove the screws (3) and the washers (4) from the brackets (5) and (6). (3) Remove the priority valve (1) with the brackets (5) and (6). Subtask 32−32−15−030−003 C. D. E. Remove the nuts (7) and (8), and remove the brackets (5) and (6) from the priority valve (1). If necessary, remove the unions (9) and (10) from the priority valve (1). Remove the preformed packings (11) and (12) from the unions (9) and (10). Discard the preformed packings. Master EFFECTIVITY: See Pageblock 32−32−15 page 401 32−32−15 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7003, 7011, 7013, 7015, 7017−7020, 7022, 7025−7067, 7069−7990, 8000−8064, 8066−8068 and ON A/C 7004−7010, 7012, 7014, 7016, 7021, 7023−7024 Post SB601R−32−008 Subtask 32−32−15−020−002 Refer to Figure 402. F. Put the fluid container below the work area. G. Remove the priority valve (1) as follows: (1) Disconnect the hydraulic lines (2). Install protective caps and plugs on the open hydraulic lines and ports. (2) Remove the screws (3) and the washers (4) from the brackets (5) and (6). (3) Remove the priority valve (1) with the brackets (5) and (6). Subtask 32−32−15−030−004 H. I. J. Remove the nuts (7) and (8), the washers (9) and (10), and remove the brackets (5) and (6) from the priority valve (1). If necessary, remove the unions (11) and (12) from the priority valve (1). Remove the preformed packings (13) and (14) from the unions (11) and (12). Discard the preformed packings. Master EFFECTIVITY: See Pageblock 32−32−15 page 401 403 32−32−15 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL LEGEND. 1. Priority valve. 2. Hydraulic line. 3. Screw. 4. Washer. 5. Bracket. 6. Bracket. 7. Nut. 8. Nut. 9. Union. 10. Union. 11. Preformed Packing. 12. Preformed Packing. 2 S. 8 SY 6 S. ES PR 10 12 9 ram3232154_001(1).dc ab/pm 20/04/95 1 11 5 2 7 4 3 Priority Valve − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−32−15 page 401 32−32−15 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Priority valve. 2. Hydraulic line. 3. Screw. 4. Washer. 5. Bracket. 6. Bracket. 7. Nut. 8. Nut. 9. Washer. 10. Washer. 11. Union. 12. Union. 13. Preformed Packing. 14. Preformed Packing. 2 8 S. SY 6 S. ES PR 10 12 14 11 ram3232154_002(1).dc pm/pt 10/03/96 1 13 5 2 7 9 4 3 Priority Valve − Removal/Installation Figure 402 Master EFFECTIVITY: See Pageblock 32−32−15 page 401 32−32−15 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL TASK 32−32−15−400−801 Installation of the MLG Priority Valve 1. Job Set−Up Information Subtask 32−32−15−944−001 A. Consumable Materials REFERENCE 02−001 None specified DESIGNATION Hydraulic fluid, phosphate ester base Cloths, cleaning **ON A/C 7004−7010, 7012, 7014, 7016, 7021, 7023−7024 Pre SB601R−32−008 Subtask 32−32−15−945−001 B. Parts REF 1 3 4 5 6 7 8 9 10 11 12 NAME OF PART Priority valve Screw Washer Bracket Bracket Nut Nut Union Union Preformed packing Preformed packing QTY 1 4 4 1 1 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−32−10−01−245 IPC 32−32−10−01−220 IPC 32−32−10−01−225 IPC 32−32−10−01−215 IPC 32−32−10−01−210 IPC 32−32−10−01−235 IPC 32−32−10−01−240 IPC 32−32−10−01−255 IPC 32−32−10−01−275 IPC 32−32−10−01−250 IPC 32−32−10−01−270 **ON A/C 7003, 7011, 7013, 7015, 7017−7020, 7022, 7025−7067, 7069−7990, 8000−8064, 8066−8068 and ON A/C 7004−7010, 7012, 7014, 7016, 7021, 7023−7024 Post SB601R−32−008 Subtask 32−32−15−945−002 C. Parts REF 1 3 4 5 6 7 8 NAME OF PART Priority valve Screw Washer Bracket Bracket Nut Nut Master EFFECTIVITY: See Pageblock 32−32−15 page 401 QTY 1 4 4 1 1 1 1 IPC SEQUENCE NO. IPC 32−32−10−01−245 IPC 32−32−10−01−220 IPC 32−32−10−01−225 IPC 32−32−10−01−215 IPC 32−32−10−01−210 IPC 32−32−10−01−235 IPC 32−32−10−01−240 406 32−32−15 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL REF 9 10 11 12 13 14 NAME OF PART Washer Washer Union Union Preformed packing Preformed packing QTY 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−32−10−01−242 IPC 32−32−10−01−241 IPC 32−32−10−01−255 IPC 32−32−10−01−275 IPC 32−32−10−01−250 IPC 32−32−10−01−270 **ON A/C ALL Subtask 32−32−15−946−002 D. Reference Information REFERENCE TASK 29−10−00−870−803 TASK 32−30−00−720−801 TASK 53−83−01−400−801 DESIGNATION Bleed Hydraulic System No. 3 Functional Test of the MLG Priority Valve Installation of the MLG Wheel Bin 2. Job Set−Up Subtask 32−32−15−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. 3. Procedure **ON A/C 7004−7010, 7012, 7014, 7016, 7021, 7023−7024 Pre SB601R−32−008 Subtask 32−32−15−430−001 Refer to Figure 401. A. Install the unions (9) and (10) with new preformed packings (11) and (12) on the priority valve (1) as follows: (1) Lightly lubricate the preformed packings (11), and (12) with clean hydraulic fluid. (2) Install the preformed packing (11) on the union (9). (3) Install the union (9) on the PRESS port of the priority valve (1). (4) Install the preformed packing (12) on the union (10). (5) Install the union (10) on the SYS port of the priority valve (1). B. Put the bracket (5) on the union (9) and install the nut (7). Do not tighten the nut fully. C. Put the bracket (6) on the union (10) and install the nut (8). Do not tighten the nut fully. D. Put the priority valve (1), with the mounting surfaces of the brackets (5) and (6), on a flat surface and tighten the nuts (7) and (8). Master EFFECTIVITY: See Pageblock 32−32−15 page 401 32−32−15 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−32−15−420−001 E. F. Put the priority valve in position on the pressure bulkhead with the PRESS port on your left, as seen in the aft direction. Attach the priority valve (1) to the pressure bulkhead with the screws (3) and the washers (4). **ON A/C 7003, 7011, 7013, 7015, 7017−7020, 7022, 7025−7067, 7069−7990, 8000−8064, 8066−8068 and ON A/C 7004−7010, 7012, 7014, 7016, 7021, 7023−7024 Post SB601R−32−008 Subtask 32−32−15−430−002 Refer to Figure 402. G. Install the unions (11) and (12) with new preformed packings (13) and (14) on the priority valve (1) as follows: (1) Lightly lubricate the preformed packings (13) and (14) with clean hydraulic fluid. (2) Install the preformed packing (13) on the union (11). (3) Install the union (11) on the PRESS port of the priority valve (1). (4) Install the preformed packing (14) on the union (12). (5) Install the union (12) on the SYS port of the priority valve (1). H. Put the bracket (5) on the union (11), and install the washer (9) and the nut (7). Do not tighten the nut fully. I. Put the bracket (6) on the union (12), and install the washer (10) and the nut (8). Do not tighten the nut fully. J. Put the priority valve (1), with the mounting surfaces of the brackets (5) and (6), on a flat surface and tighten the nuts (7) and (8). Subtask 32−32−15−420−002 K. L. Put the priority valve (1) in position on the pressure bulkhead with the PRESS port on your left, as seen in the aft direction. Attach the priority valve (1) to the aircraft structure with the screws (3) and the washers (4). **ON A/C ALL Subtask 32−32−15−430−003 M. N. Remove the protective plugs and caps from the hydraulic lines and ports. Connect the hydraulic lines (2) to the priority valve (1). 4. Close Out Subtask 32−32−15−140−002 A. Remove the fluid container and clean all hydraulic fluid from the work area. Master EFFECTIVITY: See Pageblock 32−32−15 page 401 408 32−32−15 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−32−15−865−002 B. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−32−15−870−001 C. Bleed the hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−32−15−720−001 D. Do a functional test of the main landing gear priority valve (Ref. TASK 32−32−15−720−801). Subtask 32−32−15−790−002 E. Do a leak check of the priority valve (1). Subtask 32−32−15−410−002 F. Install the left wheel bin (Ref. TASK 53−83−01−400−801). Subtask 32−32−15−941−004 G. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−32−15 page 401 32−32−15 Page 409 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL VALVE, PRIORITY − ADJUSTMENT/TEST 1. General A. The procedure that follows is for the functional test of the main−landing−gear priority valve. A ground hydraulic−power−unit and fuselage/wing jacks are necessary to do this test. An alternative procedure is referred to if there is no ground hydraulic power unit available. TASK 32−32−15−720−801 Functional Test of the MLG Priority Valve 1. Job Set−Up Information Subtask 32−32−15−946−003 A. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 10−11−00−000−802 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−05−090−802 TASK 12−00−05−490−802 TASK 12−00−06−863−804 TASK 12−00−07−861−801 TASK 12−00−07−861−802 TASK 32−30−00−730−801 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Removal of the Main Landing gear Lockpins Installation of the Nose Landing gear Lockpin Installation of the Main Landing gear Lockpins Remove Ground Hydraulic Power − Hydraulic System No. 3 Connect Ground Hydraulic Power − Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 Connect External AC Power Remove External AC Power System Test of the Landing gear Priority Valves 2. Job Set−Up Subtask 32−32−15−490−003 WARNING: A. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Master EFFECTIVITY: See Pageblock 32−32−15 page 501 32−32−15 Page 501 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−32−15−582−001 B. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). Subtask 32−32−15−861−001 C. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801). Subtask 32−32−15−863−002 D. Make sure that the hydraulic pressure is released from hydraulic system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−32−15−090−001 E. Remove the safety lockpins from the main landing gear (Ref. TASK 10−11−00−000−802). Subtask 32−32−15−863−003 WHEN THE GROUND−HYDRAULIC POWER UNIT IS USED TO PRESSURIZE THE HYDRAULIC SYSTEM, DO NOT OPERATE THE AIRCRAFT HYDRAULIC PUMPS ON THAT SAME SYSTEM. YOU CAN CAUSE DAMAGE TO THE SYSTEM. Connect the ground hydraulic power unit to hydraulic system No. 3 (Ref. TASK 12−00−05−490−802). NOTE: If there is no ground hydraulic power unit available to do this test, it is satisfactory to do the system test for the landing gear priority valves. (Ref. TASK 32−30−00−730−801). CAUTION: F. 3. Procedure Subtask 32−32−15−720−002 WARNING: A. MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF FLIGHT CONTROLS AND HYDRAULIC COMPONENTS WHEN YOU PRESSURIZE THE HYDRAULIC SYSTEMS. IF YOU DO NOT DO THIS, INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT CAN OCCUR. Do a functional test of the main−landing−gear priority valve as follows: NOTE: The main−landing−gear priority valve prevents the flow of hydraulic fluid to the landing gear selector valve until the hydraulic pressure reaches 2300±100 psi (15,858±689 kPa). This gives priority to the flight controls when hydraulic system pressure is below that set value. (1) Put the landing−gear selector handle to the UP position. (2) Slowly increase the pressure on the hydraulic power unit. (3) At 2300±100 psi (15,858±689 kPa), make sure that the main landing gear begins to retract. (4) Keep the pressure at 2300±100 psi (15,858±689 kPa) and make sure that the main landing gear retracts and locks. Master EFFECTIVITY: See Pageblock 32−32−15 page 501 32−32−15 Page 502 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (5) (6) (7) (8) Decrease the pressure on the hydraulic power unit to 2000 psi (13,790 kPa). Put the landing−gear selector handle to the DN position. Make sure that the main landing gear stays up and locked. Slowly increase the pressure and make sure that the main landing gear uplocks release at 2300±100 psi (15,858±689 kPa). (9) Keep the pressure at 2300±100 psi (15,858±689 kPa) and make sure that the main landing gear extends and locks in the down position (the green DN messages are displayed in the landing gear boxes on the primary EICAS display). (10) Decrease the pressure on the hydraulic power unit to 0 psi (0 kPa). (11) Operate the rudder pedals to release the pressure from hydraulic system No. 3. 4. Close Out Subtask 32−32−15−863−004 A. Disconnect the ground hydraulic power unit (Ref. TASK 12−00−05−090−802). Subtask 32−32−15−861−002 B. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802). Subtask 32−32−15−490−001 C. Install the safety lockpins at the main landing gear again (Ref. TASK 10−11−00−400−802). Subtask 32−32−15−582−002 D. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Subtask 32−32−15−941−002 E. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−32−15 page 501 32−32−15 Page 503 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL VALVE, RUNAROUND AND BYPASS − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the runaround and bypass valve. The runaround and bypass valve is installed in the center of the main wheel well, on top of the hydraulic beam. TASK 32−32−20−000−801 Removal of the Runaround and Bypass Valve 1. Job Set−Up Information Subtask 32−32−20−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Container, fluid Subtask 32−32−20−946−001 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 29−00−00−910−801 TASK 53−83−01−000−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions Removal of the MLG Wheel Bin 2. Job Set−Up Subtask 32−32−20−490−002 WARNING: A. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK10−11−00−400−801 and TASK 10−11−00−400−802). Subtask 32−32−20−910−001 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: B. Master EFFECTIVITY: See Pageblock 32−32−20 page 401 32−32−20 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−32−20−865−001 C. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−32−20−863−001 D. Release the hydraulic pressure from the hydraulic system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−32−20−930−002 DO NOT OPERATE THE LANDING GEAR MANUAL RELEASE HANDLE. INJURIES TO PERSONS CAN OCCUR. On the landing−gear manual release handle in the flight compartment, install a DO NOT OPERATE warning placard. WARNING: E. Subtask 32−32−20−010−001 F. Remove the left and right main landing gear wheel bins (Ref. TASK 53−83−01−000−801). 3. Procedure **ON A/C 7008, 7018 Pre SB601R−32−015 Subtask 32−32−20−030−001 Refer to Figure 401. A. Put the fluid container below the work area. B. Disconnect the hydraulic lines (1). Install protective caps and plugs on all open hydraulic lines and ports. C. Remove the bolts (2) and the washers (3). Subtask 32−32−20−020−003 D. E. F. G. H. Remove and discard the cotter pin (5). Remove the nut (6) and the washer (7). Remove the bolt (9). Remove the cotter pin (4) and the washer (8). Remove the pin (10). Remove the runaround and bypass valve (11). Master EFFECTIVITY: See Pageblock 32−32−20 page 401 32−32−20 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7003−7007, 7009−7017, 7019−7067, 7069−7990, 8000−8064, 8066−8068 and ON A/C 7008, 7018 Post SB601R−32−015 Subtask 32−32−20−030−004 Refer to Figure 402. I. Put the fluid container below the work area. J. Disconnect the hydraulic lines (1). Install protective caps and plugs on all open hydraulic lines and ports. K. Remove the bolts (2) and the washers (3). Subtask 32−32−20−020−002 L. M. N. O. P. Remove and discard the cotter pin (5). Remove the nut (6) and the washer (7). Remove the bolt (9). Remove the cotter pin (4) and the spacer (8). Remove the pin (10). Remove the runaround and bypass valve (11). **ON A/C ALL Subtask 32−32−20−030−003 Q. Do the steps that follow if you replace the runaround and bypass valve (11): (1) Remove the unions (12) and the preformed packings (14). Discard the preformed packings (14). (2) Remove the unions (13) and the preformed packings (15). Discard the preformed packings (15). (3) Loosen the nut (16) and remove the elbow (17), the retainer (18), and the preformed packing (19). Discard the preformed packing (19). Master EFFECTIVITY: See Pageblock 32−32−20 page 401 403 32−32−20 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 1 13 15 1 12 14 2 REF. LEVER 11 19 AU 18 AD 10 16 14 VU R REF. SPOOL 17 1 VD 9 12 8 4 7 1 6 3 15 1 LEGEND. 1. Hydraulic line. 2. Bolt. 3. Washer. 4. Cotter pin. 5. Cotter pin. 6. Nut. 7. Washer. 8. Washer. 9. Bolt. 10. Pin. 13 11. Runaround and bypass valve. 12. Union. 13. Union. 14. Preformed packing 15. Preformed packing. 16. Nut. 17. Elbow. 18. Retainer. 19. Preformed packing. REF.HYDRAULIC BEAM ram3232204_001(1).dc, ab, 22/02/93 5 Runaround and Bypass Valve − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−32−20 page 401 32−32−20 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 1 13 15 1 12 14 2 11 AU LEVER (REF) 19 AD 10 VU R SPOOL (REF) 18 16 14 VD 1 17 9 12 8 4 7 1 5 6 3 1 LEGEND 1. Hydraulic line. 2. Bolt. 3. Washer. 4. Cotter pin. 5. Cotter pin. 6. Nut. 7. Washer. 8. Spacer. 9. Bolt. 10. Pin. 13 11. Runaround and bypass valve. 12. Union. 13. Union. 14. Preformed packing 15. Preformed packing. 16. Nut. 17. Elbow. 18. Retainer. 19. Preformed packing. HYDRAULIC BEAM (REF) ram3232204_002.dc, ab/pm, 20/11/95 15 Runaround and Bypass Valve − Removal and Installation Figure 402 Master EFFECTIVITY: See Pageblock 32−32−20 page 401 32−32−20 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−32−20−400−801 Installation of the Runaround and Bypass Valve 1. Job Set−Up Information Subtask 32−32−20−944−001 A. Consumable Materials REFERENCE 02−001 DESIGNATION Hydraulic fluid, phosphate ester base **ON A/C 7008, 7018 Pre SB601R−32−015 Subtask 32−32−20−945−001 B. Parts REF 2 3 4 5 6 7 8 9 10 12 13 14 15 17 16 18 19 NAME OF PART Bolt Washer Cotter pin Cotter pin Nut Washer Washer Bolt Pin Union Union Preformed packing Preformed packing Elbow Nut Retainer Preformed packing QTY 3 3 1 1 1 1 1 1 1 2 2 2 2 1 1 1 1 IPC SEQUENCE NO. IPC 32−32−10−01−110 IPC 32−32−10−01−115 IPC 32−34−00−03−200 IPC 32−34−00−03−200 IPC 32−34−00−03−195 IPC 32−34−00−03−105 IPC 32−34−00−03−190 IPC 32−34−00−03−175 IPC 32−34−00−03−180 IPC 32−32−10−01−145 IPC 32−32−10−01−130 IPC 32−32−10−01−140 IPC 32−32−10−01−125 IPC 32−32−10−01−200 IPC 32−32−10−01−195 IPC 32−32−10−01−190 IPC 32−32−10−01−185 **ON A/C 7003−7007, 7009−7017, 7019−7067, 7069−7990, 8000−8064, 8066−8068 and ON A/C 7008, 7018 Post SB601R−32−015 Subtask 32−32−20−945−002 C. Parts REF 2 Bolt 3 Washer 4 Cotter pin NAME OF PART Master EFFECTIVITY: See Pageblock 32−32−20 page 401 QTY 3 3 1 IPC SEQUENCE NO. IPC 32−32−10−01−110 IPC 32−32−10−01−115 IPC 32−34−00−03−201 406 32−32−20 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL REF 5 6 7 8 9 10 12 13 14 15 17 16 18 19 NAME OF PART Cotter pin Nut Washer Spacer Bolt Pin Union Union Preformed packing Preformed packing Elbow Nut Retainer Preformed packing QTY 1 1 1 1 1 1 2 2 2 2 1 1 1 1 IPC SEQUENCE NO. IPC 32−34−00−03−200 IPC 32−34−00−03−195 IPC 32−34−00−03−105 IPC 32−34−00−03−202 IPC 32−34−00−03−175 IPC 32−34−00−03−182 IPC 32−32−10−01−145 IPC 32−32−10−01−130 IPC 32−32−10−01−140 IPC 32−32−10−01−125 IPC 32−32−10−01−200 IPC 32−32−10−01−195 IPC 32−32−10−01−190 IPC 32−32−10−01−185 **ON A/C ALL Subtask 32−32−20−946−002 D. Reference Information REFERENCE TASK 29−10−00−870−803 TASK 32−00−00−790−801 TASK 32−30−00−720−801 TASK 32−34−00−710−801 TASK 53−83−01−400−801 DESIGNATION Bleed Hydraulic System No. 3 External Leak Check of the Landing Gear Functional Test of the Landing Gear Extension/Retraction System Operational Test of the Landing Gear Manual−Release−System Installation of the MLG Wheel Bin 2. Job Set−Up Subtask 32−32−20−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. 3. Procedure **ON A/C 7008, 7018 Pre SB601R−32−015 Subtask 32−32−20−430−001 Refer to Figure 401. Master EFFECTIVITY: See Pageblock 32−32−20 page 401 32−32−20 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A. Do the steps that follow if you install a new runaround and bypass valve: (1) Lightly lubricate the preformed packings (14), (15) and (19) with clean hydraulic fluid. (2) Install the elbow (17) with the preformed packing (19) and the retainer (18) on the port of the runaround and bypass valve identified VU. Tighten the nut (16). (3) Install the unions (12) with the preformed packings (14) on the ports of the runaround and bypass valve identified AD and VD. (4) Install the unions (13) with the preformed packings (15) on the ports of the runaround and bypass valve identified AU and R. Subtask 32−32−20−420−001 B. C. D. E. Attach the lever to the runaround and bypass valve (11) with the bolt (9), the washer (7), and the nut (6). Install the cotter pin (5). Put the pin (10) through the spool of the runaround and bypass valve (11) and the lever. Install the washer (8) and the cotter pin (4). Attach the runaround and bypass valve (11) to the hydraulic beam with the bolts (2) and the washers (3). **ON A/C 7003−7007, 7009−7017, 7019−7067, 7069−7990, 8000−8064, 8066−8068 and ON A/C 7008, 7018 Post SB601R−32−015 Subtask 32−32−20−430−004 Refer to Figure 402. F. Do the steps that follow if you install a new runaround and bypass valve: (1) Lightly lubricate the preformed packings (14), (15) and (19) with clean hydraulic fluid. (2) Install the elbow (17) with the preformed packing (19) and the retainer (18) on the port of the runaround and bypass valve identified VU. Tighten the nut (16). (3) Install the unions (12) with the preformed packings (14) on the ports of the runaround and bypass valve identified AD and VD. (4) Install the unions (13) with the preformed packings (15) on the ports of the runaround and bypass valve identified AU and R. Subtask 32−32−20−420−002 G. H. I. J. Attach the lever to the runaround and bypass valve (11) with the bolt (9), the washer (7), and the nut (6). Install the cotter pin (5). Put the pin (10) through the spool of the runaround and bypass valve (11) and the lever. Install the spacer (8) and the cotter pin (4). Attach the runaround and bypass valve (11) to the hydraulic beam with the bolts (2) and the washers (3). Master EFFECTIVITY: See Pageblock 32−32−20 page 401 408 32−32−20 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL Subtask 32−32−20−430−003 K. L. Remove the protective caps from all the open hydraulic lines and/or ports. Connect the hydraulic lines (1) to the runaround and bypass valve (11). 4. Close Out Subtask 32−32−20−160−002 A. Clean all signs of hydraulic fluid from the runaround and bypass valve (11) and the surrounding work area. Subtask 32−32−20−941−001 B. Remove all tools, equipment, and unwanted materials from the work area. Subtask 32−32−20−865−002 C. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−32−20−870−001 D. Bleed the hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−32−20−720−001 E. F. Do a functional test of the landing gear extension and retraction system (Ref. TASK 32−30−00−720−801). Do an operational test of the manual release system for the landing gear (Ref. TASK 32−34−00−710−801). Subtask 32−32−20−210−001 G. Examine the work area for leaks (Ref. TASK 32−00−00−790−801). Subtask 32−32−20−410−001 H. Install the wheel bins for the main landing gear (Ref. TASK 53−83−01−400−801). Master EFFECTIVITY: See Pageblock 32−32−20 page 401 32−32−20 Page 409 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL CHECK VALVE (RETURN), MAIN LANDING GEAR SELECTOR VALVE − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the return check valve for the main−landing−gear (MLG) selector valve (written as the ‘check valve’ in this procedure). The check valve is installed on the MLG selector valve, which is located on the hydraulic beam in the main wheel well. TASK 32−32−25−000−801 Removal of the Return Check Valve 1. Job Set−Up Information Subtask 32−32−25−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Fluid container, (resistant to phosphate ester based hydraulic fluid) Subtask 32−32−25−946−001 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 29−00−00−910−801 TASK 53−83−01−000−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions Removal of the MLG Wheel Bin 2. Job Set−Up Subtask 32−32−25−941−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Install the chocks at the main wheels. WARNING: A. B. Master EFFECTIVITY: See Pageblock 32−32−25 page 401 32−32−25 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−32−25−863−002 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). Release the pressure from hydraulic system No. 3 (Ref. TASK 12−00−06−863−804). WARNING: C. D. Subtask 32−32−25−865−001 E. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−32−25−930−001 F. Install a DO NOT OPERATE THE HYDRAULIC SYSTEM warning tag on hydraulic−system No. 3 control−panel in the flight compartment. Subtask 32−32−25−010−001 G. Remove the left wheel bin (Ref. TASK 53−83−01−000−801). 3. Procedure Subtask 32−32−25−020−001 Refer to Figure 401. A. Remove the check valve (2) as follows: (1) Put the fluid container below the work area. (2) Disconnect the hydraulic line (1). (3) Remove the check valve (2) and the preformed packing (3). Discard the preformed packing. (4) Install protective plugs and caps on the open hydraulic line and ports. Master EFFECTIVITY: See Pageblock 32−32−25 page 401 32−32−25 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND. 3 2 1 SELECTOR VALVE (REF) ram3232254_001(1).dc, dm/ks, 22/02/93 1. Hydraulic line. 2. Check valve. 3. Preformed packing. Return Check Valve (MLG Selector Valve) − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−32−25 page 401 32−32−25 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−32−25−400−801 Installation of the Return Check Valve 1. Job Set−Up Information Subtask 32−32−25−944−001 A. Consumable Materials REFERENCE 02−001 DESIGNATION Hydraulic fluid, phosphate ester base Subtask 32−32−25−945−001 B. Parts REF NAME OF PART 2 Check valve 3 Preformed packing QTY 1 1 IPC SEQUENCE NO. IPC 32−32−10−01−065 IPC 32−32−10−01−060 Subtask 32−32−25−946−002 C. Reference Information REFERENCE TASK 29−10−00−870−803 TASK 32−30−00−720−801 TASK 53−83−01−400−801 DESIGNATION Bleed Hydraulic System No. 3 Functional Test of the Landing Gear Extension/Retraction System Installation of the MLG Wheel Bin 2. Job Set−Up Subtask 32−32−25−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. 3. Procedure Subtask 32−32−25−430−001 Refer to Figure 401. A. Install the check valve (2) as follows: (1) Remove the protective caps and plugs from the hydraulic line and ports. (2) Lightly lubricate the preformed packing (3) with clean hydraulic fluid. (3) Install the preformed packing (3) on the end of the check valve (2) that goes into the selector valve. (4) Install the check valve (2) in the selector valve. NOTE: Make sure that the flow indication arrow of the check valve (2) points away from the selector valve when installed. Master EFFECTIVITY: See Pageblock 32−32−25 page 401 32−32−25 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (5) Connect the hydraulic line (1). 4. Close Out Subtask 32−32−25−140−001 A. Clean all signs of hydraulic fluid from the work area. Subtask 32−32−25−941−002 B. Remove all tools, equipment, warning tags, and unwanted materials from the aircraft and the work area. Subtask 32−32−25−865−002 C. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−32−25−870−001 D. Bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−32−25−720−001 E. Do a functional test of the landing gear extension/retraction system (Ref. TASK 32−30−00−720−801). Subtask 32−32−25−790−001 F. Examine the work area for leaks. Subtask 32−32−25−410−001 G. Install the left wheel bin (Ref. TASK 53−83−01−400−801). Master EFFECTIVITY: See Pageblock 32−32−25 page 401 32−32−25 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL RESTRICTOR (C1 PORT), MAIN LANDING GEAR SELECTOR VALVE − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the restrictor that is installed in the C1 port of the main−landing−gear (MLG) selector valve (written as the ‘restrictor’ in this procedure). The selector valve is installed on the hydraulic beam in the main wheel well. TASK 32−32−30−000−801 Removal of the Restrictor 1. Job Set−Up Information Subtask 32−32−30−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Fluid container − phosphate ester based resistant Subtask 32−32−30−946−001 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 29−00−00−910−801 TASK 53−83−01−000−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions Removal of the MLG Wheel Bin 2. Job Set−Up Subtask 32−32−30−941−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Install the chocks at the main wheels. WARNING: A. B. Master EFFECTIVITY: See Pageblock 32−32−30 page 401 32−32−30 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−32−30−863−002 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). Release the pressure from hydraulic system No. 3 (Ref. TASK 12−00−06−863−804). WARNING: C. D. Subtask 32−32−30−865−001 E. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−32−30−930−001 F. Install a warning placard (DO NOT OPERATE THE HYDRAULIC SYSTEM) on hydraulic−system No. 3 control−panel in the flight compartment. Subtask 32−32−30−010−001 G. Remove the left wheel bin (Ref. TASK 53−83−01−000−801). 3. Procedure Subtask 32−32−30−020−001 Refer to Figure 401. A. Remove the restrictor (2) as follows: (1) Put the fluid container below the work area. (2) Disconnect the hydraulic line (1). (3) Remove the restrictor (2) and the preformed packing (3). Discard the preformed packing. (4) Install protective caps and plugs on the open hydraulic line and ports. Master EFFECTIVITY: See Pageblock 32−32−30 page 401 32−32−30 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 1 2 ram3232304_001(1).dc, dm/ks, 22/02/93 3 LEGEND. 1. Hydraulic line. 2. Restrictor. 3. Preformed packing. Restrictor, C1 Port (MLG Selector Valve) − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−32−30 page 401 32−32−30 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−32−30−400−801 Installation of the Restrictor 1. Job Set−Up Information Subtask 32−32−30−944−001 A. Consumable Materials REFERENCE 02−001 DESIGNATION Hydraulic fluid, phosphate ester base Subtask 32−32−30−945−001 B. Parts REF NAME OF PART 2 Restrictor 3 Preformed packing QTY 1 1 IPC SEQUENCE NO. IPC 32−32−10−01−095 IPC 32−32−10−01−090 Subtask 32−32−30−946−002 C. Reference Information REFERENCE TASK 29−10−00−870−803 TASK 32−30−00−720−801 TASK 53−83−01−400−801 DESIGNATION Bleed Hydraulic System No. 3 Functional Test of the Landing Gear Extension/Retraction System Installation of the MLG Wheel Bin 2. Job Set−Up Subtask 32−32−30−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. 3. Procedure Subtask 32−32−30−430−001 Refer to Figure 401. A. Install the restrictor (2) as follows: (1) Remove the protective caps and plugs from open hydraulic line and ports. (2) Lightly lubricate the preformed packing (3) with clean hydraulic fluid. (3) Install the preformed packing (3) on the end of the restrictor (2) that goes into the selector valve. (4) Install the restrictor (2) in the selector valve. NOTE: Make sure that the flow indication arrow on the restrictor (2) points into the selector valve when installed. Master EFFECTIVITY: See Pageblock 32−32−30 page 401 32−32−30 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL B. Connect the hydraulic line (1). 4. Close Out Subtask 32−32−30−140−001 A. Clean all signs of hydraulic fluid from the work area. Subtask 32−32−30−941−002 B. Remove all tools, equipment, warning placards, and unwanted materials from the aircraft and the work area. Subtask 32−32−30−865−002 C. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−32−30−870−001 D. Bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−32−30−720−001 E. Do a functional test of the landing gear extension and retraction system (Ref. TASK 32−30−00−720−801). Subtask 32−32−30−210−001 F. Examine the work area for leaks. Subtask 32−32−30−410−001 G. Install the left wheel bin (Ref. TASK 53−83−01−400−801). Master EFFECTIVITY: See Pageblock 32−32−30 page 401 32−32−30 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL NOSE LANDING GEAR EXTENSION/RETRACTION − DESCRIPTION AND OPERATION 1. 2. General A. Normal control of the landing gear is through the operation of the selector lever on the center pedestal. The nose landing gear (NLG) is hydraulically extended in the aft direction and mechanically locked in the vertical position for landing. It is retracted in the forward direction and locked into the NLG wheel well during flight. The NLG extension and retraction system includes the components that follow: ± Retraction actuator ± NLG uplock assembly ± NLG selector valve ± Priority valve ± Check valve ± Restrictor. Component Details Refer to Figure 1, Figure 2, and Figure 3. A. NLG Retraction Actuator (1) The NLG retraction actuator is a two−position hydraulic actuator used to extend and retract the NLG. The actuator is includes a piston, a cylinder, a restrictor, and the hydraulic seals. The cylinder end of the actuator is attached to the top of the main fitting, while the piston end is connected to the drag strut assembly. (a) The cylinder is a steel part which includes two eye fittings, two hydraulic ports, and a restrictor. One cylinder port is used for fluid flow to extend the actuator piston. The other port is used to permit fluid to the retract port on the opposite side of the cylinder. The restrictor is installed in the retract port and is used to control the speed of the actuator during landing gear extension and retraction. (b) The piston is a chromed steel part installed in the cylinder assembly. A scraper has been installed to prevent damage to the internal seals from the ingress of foreign objects. B. NLG Uplock Assembly (1) The uplock assembly is a mechanical/hydraulic lock used to lock the landing gear in the retracted position. The lock is connected mechanically and released hydraulically. The uplock is attached to the bulkhead in the nosewheel well. (2) Two mechanical release levers are installed on the body of the uplock. One lever is used to release the lock during emergency gear extension and the other is used for mechanical release during ground operations. (3) A mount bracket for the proximity sensor is installed between the actuator and the body of the uplock assembly. The targets for the proximity sensors are installed on the manual release lever and on the emergency release lever. (4) The actuator assembly is used to release the mechanical uplock and permit the landing gear to be extended. The actuator piston extends through the body to the latch lever. Each actuator has two ports, an extend port and a retract port. Master EFFECTIVITY: See Pageblock 32−33−00 page 1 32−33−00 Page 1 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. (5) When the uplock actuator is fully pressurized, the actuator piston extends and moves the uplock lever. As the uplock lever moves, it pushes up and lifts the roller out of engagement with the latch. The weight of the landing gear continues to turn the latch until the landing gear is free to fall to the down and locked position. C. NLG Selector Valve (1) The selector valve is a solenoid−operated, four−way, three−position valve used to control the flow of fluid to the extend or retract side of the NLG retraction actuator. The NLG selector valve is installed near the aft bulkhead of the NLG bay. D. NLG Priority Valve (1) The priority valve is used to make sure that the flight controls have priority on hydraulic pressure during the retraction of the landing gear. The NLG priority valve is installed near the aft bulkhead of the NLG wheel well. Operation A. NLG Extension (1) When the pilot sets the selector lever to the LANDING GEAR DN position, the extend signal is sent to the proximity sensor electronics unit (PSEU). The PSEU will then receive and analyze the input signals from the landing gear and other aircraft systems. If all of the necessary input signals are present, the PSEU sends a signal to energize the nose door and nose landing gear (NLG) selector valves to the down position. (2) When the selector valve for the NLG door opens, the flow of fluid is sent to the nose door actuator which extends the forward doors to the fully−open position. (3) When the nose doors are fully open, the PSEU sends a signal to energize the NLG selector valve to the down position. Hydraulic fluid from system No. 3 is then sent through the priority valve to the NLG selector valve. The selector valve opens and permits the flow of fluid to the NLG uplock actuator and the extend side of the NLG actuator. (4) When the NLG uplock is fully released, the nose gear actuator extends and the gear is mechanically locked in the down and locked position. (5) When the PSEU gets the gear−down indication, it will then energize the NLG door selector−valve to the closed position and the forward doors will close. B. NLG Retraction (1) When the pilot sets the selector lever to the LANDING GEAR UP position, the retract signal is sent to the PSEU. The PSEU will then receive and analyze the input signals from the landing gear and other aircraft systems. If all of the necessary input signals are present, the PSEU sends a signal to energize the nose door and MLG selector valves. (2) When the NLG door selector−valve opens, the flow of fluid is sent to the nose door actuator, thus the NLG forward doors extend to the fully−open position. (3) When the door−open connection is complete, the PSEU energizes the NLG selector valve to the up position. (4) Hydraulic fluid is sent through the priority valve to the NLG selector valve. The selector valve opens and permits the flow of fluid to the NLG actuator. Thus the nose gear retracts. Master EFFECTIVITY: See Pageblock 32−33−00 page 1 32−33−00 Page 2 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 4. (5) When the gear up and locked condition is complete, the PSEU sends a signal to energize the NLG door selector−valve and the forward doors will close. Component Location Index Refer to Figure 1, Figure 2, and Figure 3. COMPONENT NAME Extension/retraction actuator NLG uplock assembly NLG selector valve Priority valve Check valve Restrictor QTY 1 1 1 1 1 1 Master EFFECTIVITY: See Pageblock 32−33−00 page 1 ACCESS/ZONE 123 123 121AL 121AL 121AL 121AL REFERENCE 32−33−01 32−33−05 32−33−10 32−33−15 32−33−20 32−33−25 32−33−00 Page 3 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL C A A B NLG SELECTOR VALVE ZONE 121 ram3233000_001.dc, rf/fp, 24/08/92 C NLG DOOR SELECTOR VALVE ZONE 123 B NLG PRIORITY VALVE ZONE 121 NLG Extension/Retraction − Component Location Figure 1 Master EFFECTIVITY: See Pageblock 32−33−00 page 1 32−33−00 Page 4 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL MANUAL RELEASE LEVER EMERGENCY RELEASE LEVER PROXIMITY SWITCH PLATE UPLOCK ACTUATOR LATCH LEVER ROLLER NOSE LANDING GEAR UPLOCK ASSEMBLY (COVER REMOVED) LATCH ram3233000_002(1).dc, rf/pb, 04/01/93 BODY NLG Uplock Actuator Figure 2 Master EFFECTIVITY: See Pageblock 32−33−00 page 1 32−33−00 Page 5 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL ram3233000_003.dc, JR/GG, 16/08/91 NLG EXTENTION/RETRACTION ACTUATOR NLG Extension/Retraction Actuator Figure 3 Master EFFECTIVITY: See Pageblock 32−33−00 page 1 32−33−00 Page 6 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL NOSE LANDING GEAR EXTENSION/RETRACTION − MAINTENANCE PRACTICES 1. General A. The procedure that follows gives the maintenance practice for the extension and retraction of the nose landing gear (NLG). This procedure is used when it is necessary to do a basic extension and retraction of the NLG for other maintenance. B. Also included are the procedures that are required to install and remove the support equipment that is required for functional tests of the NLG. TASK 32−33−00−867−801 Nose Landing Gear Extension and Retraction − Maintenance Practices 1. Job Set−Up Information Subtask 32−33−00−946−001 A. Reference Information REFERENCE TASK 07−11−01−582−802 TASK 10−11−00−000−801 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−803 TASK 12−00−06−863−804 TASK 12−00−07−861−801 TASK 12−00−07−861−802 DESIGNATION Jacking of the Aircraft from the Nose Removal of the Nose Landing Gear Lockpin Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 Connect External AC Power Remove External AC Power 2. Job Set−Up Subtask 32−33−00−840−001 A. At the LDG GEAR control panel, make sure that the landing gear control handle is in the DN position. Subtask 32−33−00−865−001 B. Make sure that the circuit breakers that follow are closed: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−4 CB NO. F6 F7 F9 P2 P3 B13 NAME PROX SENS LGC/D1 PROX SENS WOW 1 PROX SENS WOW 2 PROX SENS LGC/D1 PROX SENS LGC/D2 WOW 1 + 2 PROX SENS LGC/D2 Master EFFECTIVITY: See Pageblock 32−33−00 page 201 32−33−00 ZONE 221 221 222 222 222 222 Page 201 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−33−00−582−001 C. Lift the aircraft at the nose jacking point at FS278.00 with a jack (Ref. TASK 07−11−01−582−802). Make sure that there is a minimum of 1.0 inch (2.5 cm) clearance and a maximum of 2.0 inches (5.0 cm) clearance between the NLG wheels and the ground. Subtask 32−33−00−090−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED AT THE MAIN LANDING GEAR BEFORE YOU RETRACT THE NOSE LANDING GEAR. THE MAIN LANDING GEAR CAN ACCIDENTLY RETRACT AND CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Remove the safety lockpin from the NLG (Ref. TASK 10−11−00−000−801). Make sure that the safety lockpins are installed at the main landing gear (Ref. TASK 10−11−00−400−802). WARNING: D. Subtask 32−33−00−861−001 E. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801). Subtask 32−33−00−863−001 WARNING: F. STAY AWAY FROM THE NOSE LANDING GEAR DOORS. IF THE DOORS ARE OPEN WHEN HYDRAULIC PRESSURE IS APPLIED TO HYDRAULIC SYSTEM NO. 3, THE DOORS WILL CLOSE. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Pressurize hydraulic system No. 3 (Ref. TASK 12−00−06−863−803). 3. Procedure Subtask 32−33−00−867−001 BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. At all times during the procedure that follows, only one person is permitted to be in the flight compartment. Do the retraction and extension of the NLG as follows: (1) To keep the landing gear horn from being heard during this procedure, move the WARNING: NOTE: A. Master EFFECTIVITY: See Pageblock 32−33−00 page 201 32−33−00 Page 202 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL throttle levers forward out of the IDLE position. **ON A/C 7032, 7059, 7061, 7063, 7094, 7103, 7110, 7115, 7125, 7133, 7142, 7148, 7154, 7166−7167, 7170, 7205, 7272, 7365, 7371, 7384, 7390−7990, 8000−8064, 8066−8068 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Post SB601R−31−022 NOTE: If the throttle levers are in the IDLE position, the landing gear is not down and locked, and the logic state is satisfied for the landing gear horn to be heard for 10 seconds or more, one or more of the indications in the three GEAR boxes on the EICAS primary page will become amber and flash with a one second interval. This is a visual indication for additional landing safety and occurs even if the landing gear horn has been muted or disabled. **ON A/C ALL (2) At the LDG GEAR control panel, push the DN LCK REL button and put the landing gear control handle in the UP position. (3) Let the NLG retract and lock in the UP position. NOTE: Ignore any gear disagree indications that are seen on the EICAS primary page. (4) Put the landing gear control handle to the DN position. (5) Let the NLG extend and lock in the DN position. B. If necessary, do the retraction and extension of the NLG again until the applicable maintenance procedure is completed. C. When the maintenance is complete and the NLG has been extended for the last time, make sure that: ± the landing gear control handle is in the DN position ± the NLG is down and locked ± the green−color DN indication is seen (in the GEAR box for the NLG) on the EICAS primary page. 4. Close Out Subtask 32−33−00−980−001 A. Move the throttle levers aft to the IDLE position again. Subtask 32−33−00−863−002 B. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−33−00−861−002 C. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802). Master EFFECTIVITY: See Pageblock 32−33−00 page 201 203 32−33−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−33−00−490−001 D. Install the safety lockpin at the NLG (Ref. TASK 10−11−00−400−801). Subtask 32−33−00−582−002 E. Lower the aircraft and remove the jack from the nose of the aircraft (Ref. TASK 07−11−01−582−802). Subtask 32−33−00−941−001 F. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−33−00 page 201 32−33−00 Page 204 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−33−00−840−801 Installation of the Support Equipment for NLG Extension and Retraction 1. Job Set−Up Information Subtask 32−33−00−943−001 A. Tools and Equipment REFERENCE MS21905J4 MS21904J4 MS21913J4 MS21914J4 None specified None specified None specified None specified (Ref. ITEM 29−00−00) None specified DESIGNATION Tee connection (three required) Elbow connection, (three required) Pressure plug (three required) Pressure cap (five required) Dust cap (three required) Flat pan, hydraulic fluid resistant Hydraulic hoses, flexible, with AN style fittings (size 4), 3000 psi (20684 kPa) pressure rating, (six required) (six lengths as required) Hydraulic power unit Hydraulic test stand Subtask 32−33−00−946−002 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 29−00−00−910−801 TASK 32−22−01−980−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions Open and Isolate the Nose−Landing−Gear Forward Doors 2. Job Set−Up Subtask 32−33−00−941−002 A. Put a flat pan or other container under the work area to collect any hydraulic fluid leakage that occurs during this procedure. Subtask 32−33−00−010−001 B. Open and isolate the NLG doors (Ref. TASK 32−22−01−980−801). Master EFFECTIVITY: See Pageblock 32−33−00 page 201 32−33−00 Page 205 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−33−00−910−001 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: C. 3. Procedure Subtask 32−33−00−490−002 Refer to Figure 201. A. Do the steps that follow to install the support equipment in the NLG wheel well: (1) Isolate the NLG bypass valve (1) from the hydraulic system as follows: (a) Disconnect the GEAR UP hydraulic line (2) from the hydraulic fitting in the port identified as AU in the NLG bypass valve (1). Connect an elbow fitting to the GEAR UP hydraulic line (2). (b) Disconnect the GEAR UP hydraulic line (3) from the hydraulic fitting in the port identified as VU in the NLG bypass valve (1). Connect an elbow fitting to the GEAR UP hydraulic line (3). (c) Disconnect the GEAR DOWN hydraulic line (4) from the check valve in the port identified as VD in the NLG bypass valve (1). Connect the elbow fitting to the GEAR DOWN hydraulic line (4). (d) To prevent contamination, install dust caps on the two hydraulic fittings and on the check valve in the NLG bypass valve (1). (2) Isolate the NLG selector valve in the nose hydraulics compartment as follows: (a) Disconnect the GEAR UP hydraulic line (5) from the fitting attached to the left side of the wheel well at FS 195.00 and LBL 13.7. (b) Disconnect the GEAR DOWN hydraulic line (6) from the hydraulic fitting attached to the left side of the wheel well at FS 196.50 and LBL 13.7. (c) Install pressure plugs in the two hydraulic lines (5) and (6). (d) To prevent contamination, install pressure caps on the two hydraulic fittings in the left side of the wheel well at FS 195.00 and at FS 196.50. (3) Do the steps that follow to connect the hydraulic power unit and the hydraulic test stand to the hydraulic system of the aircraft: NOTE: The hydraulic test stand must have the capablity to select and pressurize hydraulic hose No. 7 or hydraulic hose No. 8 independently. When one of these hydraulic hoses is selected to PRESSURIZE, the other hydraulic hose is to be selected to RETURN. (a) Connect the pressure and the return hoses from the hydraulic power unit to the hydraulic test stand. (b) Connect one end of hydraulic hose No. 7 to the hydraulic test stand (to the port that will be pressurized when the selection handle on the test stand is in the position A (GEAR UP)). Connect the other end of hydraulic hose No. 7 to one side of a tee fitting. Master EFFECTIVITY: See Pageblock 32−33−00 page 201 32−33−00 Page 206 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (c) Connect one end of hydraulic hose No. 8 to the hydraulic test stand (to the port that will be pressurized when the selection handle on the test stand is in position B (GEAR DOWN)). Connect the other end of hydraulic hose No. 8 to one side of a tee fitting. (d) Connect a short hydraulic hose between the two tee fittings. This hydraulic hose is referred to as the ‘jumper hose’ for the hydraulic power unit. NOTE: This hydraulic hose is used to bleed the hydraulic circuit and will be removed again in a later step. (e) Connect hydraulic hose No. 9 to one side of a tee fitting and connect the other end to the tee fitting that is attached to hydraulic hose No. 7 and to the jumper line. (f) Connect hydraulic hose No. 10 to the opposite side of the tee fitting that is attached to hydraulic hose No. 9 and then connect the other end to the elbow fitting that is connected to the GEAR UP hydraulic line (that was attached to the hydraulic fitting in the port identified as AU in the NLG bypass valve). (g) Connect hydraulic hose No. 11 to the remaining side of the tee fitting that is attached to hydraulic hose No. 9 and then connect the other end to the elbow fitting that is connected to the GEAR UP hydraulic line (that was attached to the hydraulic fitting in the port identified as VU in the NLG bypass valve). (h) Connect hydraulic hose No. 12 to the tee fitting that is connected to hydraulic hose No. 8 and to the jumper line and then connect the other end to the elbow fitting that is connected to the GEAR DOWN hydraulic line (that was attached to the check valve in the port identified as VD in the NLG bypass valve). WARNING: MAKE SURE THAT YOU BLEED THE HYDRAULIC LINES OF ANY AIR THAT IS CAUGHT IN THEM. IF YOU DO NOT DO THIS, THE LANDING GEAR CAN DROP SUDDENLY WHEN IT IS RELEASED FROM THE UPLOCK. (4) Pressurize hydraulic hose No. 7 or No. 8 to 50 psi (344.75 kPa) with the ground hydraulic unit. (5) To purge any air in the hydraulic circuit, allow hydraulic fluid to recirculate for a minimum of two minutes at a rate of five gallons/minute (19 litres/minute). (6) Make sure that there is no hydraulic fluid leakage at any of the installed fittings, pressure caps, or pressure plugs. (7) Release the hydraulic pressure from the ground hydraulic unit. Make sure the that the hydraulic pressure is reduced to zero. (8) Disconnect the jumper hose from the tee fitting that connects hydraulic lines No. 7 and No. 9 and from the tee fitting that connects hydraulic lines No. 8 and No. 12. Install pressure caps on the two tee fittings. Master EFFECTIVITY: See Pageblock 32−33−00 page 201 32−33−00 Page 207 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL PRESSURE CAP (REF) GEAR UP TEE (REF) GEAR DOWN HYDRAULIC HOSE NO.12 (REF) JUMPER (REF) 3 DUST CAP (REF) ELBOW (REF) N.L.G. WHEEL WELL PLAN VIEW ram3233002_001.dg, sb/rm, 03/02/03 DUST CAP 1 (REF) 6 LBL 13.70 4 AU VU ELBOW (REF) 5 FS 180.25 VD HYDRAULIC HOSE NO.10 (REF) PRESSURE CAP (REF) PRESSURE PLUG (REF) HYDRAULIC HOSE NO.8 (REF) GEAR DOWN GEAR UP TEE (REF) HYDRAULIC HOSE NO.9 TEE (REF) (REF) Hydraulic hoses No.9, 10, 11, and 12 must be made as short as possible. 2 FS 195.00 HYDRAULIC HOSE NO.11 (REF) NOTE DOWN LOCK ACTUATOR Test equipment. FS 196.50 UPLOCK ACTUATOR 1. NLG bypass valve. 2. GEAR UP hydraulic line. 3. GEAR UP hydraulic line. 4. GEAR DOWN hydraulic line. 5. GEAR UP hydraulic line. 6. GEAR DOWN hydraulic line. TO RETRACTION ACTUATOR LEGEND HYDRAULIC HOSE NO.7 (REF) HYDRAULIC TEST STAND Test Equipment Hydraulic Connections − NLG Extension/Retraction Figure 201 Master EFFECTIVITY: See Pageblock 32−33−00 page 201 32−33−00 Page 208 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−33−00−840−802 Removal of the Support Equipment for NLG Extension and Retraction 1. Job Set−Up Information Subtask 32−33−00−943−002 A. Tools and Equipment REFERENCE None specified DESIGNATION Flat pan, hydraulic fluid resistant Subtask 32−33−00−946−003 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 12−00−06−863−804 TASK 29−00−00−910−801 TASK 29−10−00−870−803 TASK 32−00−00−790−801 TASK 32−22−01−980−802 DESIGNATION Installation of the Nose Landing Gear Lockpin Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions Bleed Hydraulic System No. 3 Leak Check of the Landing Gear Close the Nose−Landing−Gear Forward Doors 2. Procedure Subtask 32−33−00−090−002 Refer to Figure 202. A. Do the steps that follow to remove the support equipment: (1) Release the hydraulic pressure from the ground hydraulic unit. Make sure the that the hydraulic pressure is reduced to zero. (2) Do the steps that follow to disonnect the hydraulic power unit and the hydraulic test stand from the hydraulic system of the aircraft: (a) Disconnect the hydraulic hose No. 12 from the tee fitting and from the elbow fitting that is connected to the GEAR DOWN hydraulic line (4). (b) Remove the elbow fitting from the GEAR DOWN hydraulic line (4). (c) Disconnect hydraulic hose No. 11 from the tee fitting and from the elbow fitting that is connected to the GEAR UP hydraulic line (3). (d) Remove the elbow fitting from the GEAR UP hydraulic line (3). (e) Disconnect hydraulic hose No. 10 from the tee fitting and from the elbow fitting that is connected to the GEAR UP hydraulic line (2). (f) Remove the elbow fitting from the GEAR UP hydraulic line (2). (g) Disconnect hydraulic hose No. 9 from the two tee fittings. (h) Disconnect the end of hydraulic hose No. 8 from the hydraulic test stand and from the tee fitting. Master EFFECTIVITY: See Pageblock 32−33−00 page 201 32−33−00 Page 209 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (i) (j) Disconnect the end of hydraulic hose No. 7 from the hydraulic test stand and from the tee fitting. Disconnect the pressure and the return lines from the hydraulic power unit from the hydraulic test stand. Subtask 32−33−00−430−001 B. Do the steps that follow to connect the hydraulic lines (6), (5), (4), (3), and (2) in the nosewheel well: (1) Connect the hydraulic lines (6) and (5) as follows: (a) Remove the pressure caps from the two hydraulic fittings at FS195.00 and FS196.50 in the left side of the wheel well at LBL 13.7. (b) Remove the pressure plugs from the GEAR UP hydraulic line (5) and the GEAR DOWN hydraulic line (6). (c) Connect the GEAR UP hydraulic line (5) to the fitting attached to the left side of the wheel well at FS195.00 at LBL 13.7. (d) Connect the GEAR DOWN hydraulic line (6) to the hydraulic fitting attached to the left side of the wheel well at FS196.50 at LBL 13.7. (2) Connect the hydraulic lines (4), (3), and (2) to the NLG bypass valve (1) as follows: (a) Remove the dust caps from the two hydraulic fittings and from the check valve in the NLG bypass valve (1). (b) Connect the GEAR DOWN hydraulic line (4) to the check valve in the port identified as VD in the NLG bypass valve (1). (c) Connect the GEAR UP hydraulic line (3) to the hydraulic fitting in the port identified as VU in the NLG bypass valve (1). (d) Connect the GEAR UP hydraulic line (2) from the hydraulic fitting in the port identified as AU in the NLG bypass valve (1). 3. Close Out Subtask 32−33−00−870−001 A. Bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−33−00−210−001 B. Check the work area for hydraulic fluid leaks (Ref. TASK 32−00−00−790−801). Subtask 32−33−00−410−001 C. Close the NLG doors (Ref. TASK 32−22−01−980−802). Subtask 32−33−00−867−003 D. NLG Extension and Retraction (Ref. TASK 32−33−00−867−801). Master EFFECTIVITY: See Pageblock 32−33−00 page 201 32−33−00 Page 210 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−33−00−863−003 E. Make sure that the hydraulic pressure is released from from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−33−00−490−004 F. Install the safety lockpin at the NLG (Ref. TASK 10−11−00−400−801). Subtask 32−33−00−941−003 G. Remove all tools, equipment, and unwanted materials from the work area. Master EFFECTIVITY: See Pageblock 32−33−00 page 201 32−33−00 Page 211 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL PRESSURE CAP (REF) GEAR UP TEE (REF) GEAR DOWN HYDRAULIC HOSE NO.12 (REF) JUMPER (REF) 3 DUST CAP (REF) ELBOW (REF) N.L.G. WHEEL WELL PLAN VIEW ram3233002_001.dg, sb/rm, 03/02/03 DUST CAP 1 (REF) 6 LBL 13.70 4 AU VU ELBOW (REF) 5 FS 180.25 VD HYDRAULIC HOSE NO.10 (REF) PRESSURE CAP (REF) PRESSURE PLUG (REF) HYDRAULIC HOSE NO.8 (REF) GEAR DOWN GEAR UP TEE (REF) HYDRAULIC HOSE NO.9 TEE (REF) (REF) Hydraulic hoses No.9, 10, 11, and 12 must be made as short as possible. 2 FS 195.00 HYDRAULIC HOSE NO.11 (REF) NOTE DOWN LOCK ACTUATOR Test equipment. FS 196.50 UPLOCK ACTUATOR 1. NLG bypass valve. 2. GEAR UP hydraulic line. 3. GEAR UP hydraulic line. 4. GEAR DOWN hydraulic line. 5. GEAR UP hydraulic line. 6. GEAR DOWN hydraulic line. TO RETRACTION ACTUATOR LEGEND HYDRAULIC HOSE NO.7 (REF) HYDRAULIC TEST STAND Test Equipment Hydraulic Connections − NLG Extension/Retraction Figure 202 Master EFFECTIVITY: See Pageblock 32−33−00 page 201 32−33−00 Page 212 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL ACTUATOR, NLG EXTENSION/RETRACTION − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the nose−landing−gear (NLG) extension/retraction actuator. The extension/retraction actuator uses hydraulic system No. 3 to extend and retract the NLG. TASK 32−33−01−000−801 Removal of the NLG Extension/Retraction Actuator 1. Job Set−Up Information Subtask 32−33−01−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Container, hydraulic fluid Subtask 32−33−01−946−001 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 29−00−00−910−801 TASK 32−22−01−980−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Hydraulic Safety Precautions Open and Isolate the Nose−Landing−Gear Forward Doors 2. Job Set−Up Subtask 32−33−01−490−001 WARNING: A. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Subtask 32−33−01−910−001 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: B. Master EFFECTIVITY: See Pageblock 32−33−01 page 401 32−33−01 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL WARNING: C. IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the forward doors of the NLG (Ref. TASK 32−22−01−980−801). 3. Procedure Subtask 32−33−01−020−001 Refer to Figure 401. A. Remove the extension/retraction actuator (2) as follows: (1) Put a hydraulic fluid container below the work area. (2) Disconnect the hydraulic lines (1) from the union fitting (21) on the extension/retraction actuator (2). (3) If the extension/retraction actuator (2) will not be the one that will be installed in the installation task, do the steps that follow: (a) Remove the union fittings (21) from the extension and retraction ports in the extension/retraction actuator (2). (b) Remove and discard the preformed packings (22) from the union fittings (21). (4) Install protective caps and plugs on all open hydraulic lines and union fittings/ports. (5) Remove and discard the cotter pin (3). (6) Remove the nut (4), and the washers (5) and (6). (7) Remove the bolt (7), the washers (8) and (9), and the retaining plate (10). NOTE: Leave the retract actuator pin (11) in position until the hardware on the opposite end of the extension/retraction actuator (2) is disconnected. (8) Remove and discard the cotter pin (12). (9) Remove the nut (13), and washers (14) and (15). (10) Remove the bolt (16), the washers (17) and (18), and the retaining plate (19). (11) Carefully remove the retract actuator pins (11) and (20) and remove the extension/retraction actuator (2). Master EFFECTIVITY: See Pageblock 32−33−01 page 401 32−33−01 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL A B LUBRICATION FITTING (REF) 11 10 1 9 8 7 2 A 21 22 4 5 6 3 13 14 15 LUBRICATION FITTING (REF) 17 12 19 18 20 B 16 1. Hydraulic line. 2. Extension retraction actuator. 3. Cotter pin. 4. Nut. 5. Washer. 6. Washer. 7. Bolt. 8. Washer. 9. Washer. 10. Retaining plate. 11. Retract actuator pin. 12. Cotter pin. 13. Nut. 14. Washer. 15. Washer. 16. Bolt. 17. Washer. 18. Washer. 19. Retaining plate. 20. Retract actuator pin. 21. Union fitting. 22. Preformed packing. ram3233014_001(2).dc, rs/rm, 22/02/97 LEGEND. NLG Extension/Retraction Actuator − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−33−01 page 401 32−33−01 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−33−01−400−801 Installation of the NLG Extension/Retraction Actuator 1. Job Set−Up Information Subtask 32−33−01−943−002 A. Tools and Equipment REFERENCE None specified DESIGNATION Torque wrench, torque range 0−50 pound−inches (0−5.7 N·m) Subtask 32−33−01−944−002 B. Consumable Materials REFERENCE 02−001 DESIGNATION Hydraulic fluid, phosphate ester base Subtask 32−33−01−945−001 C. Parts REF 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 NAME OF PART Cotter pin Nut Washer Washer Bolt Washer Washer Retaining plate Retract actuator pin Cotter pin Nut Washer Washer Bolt Washer Washer Retaining plate Retract actuator pin Master EFFECTIVITY: See Pageblock 32−33−01 page 401 QTY 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 IPC SEQUENCE NO. IPC 32−33−01−01−040 IPC 32−33−01−01−035 IPC 32−33−01−01−030 IPC 32−33−01−01−025 IPC 32−33−01−01−020 IPC 32−33−01−01−030 IPC 32−33−01−01−025 IPC 32−33−01−01−015 IPC 32−33−01−01−013 IPC 32−33−01−01−075 IPC 32−33−01−01−070 IPC 32−33−01−01−065 IPC 32−33−01−01−060 IPC 32−33−01−01−055 IPC 32−33−01−01−065 IPC 32−33−01−01−060 IPC 32−33−01−01−050 IPC 32−33−01−01−080 32−33−01 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−33−01−946−002 D. Reference Information REFERENCE TASK 12−20−32−640−801 TASK 29−10−00−870−803 TASK 32−00−00−790−801 TASK 32−30−00−720−801 TASK 32−22−01−980−801 TASK 32−22−01−980−802 DESIGNATION Lubrication of the Nose Landing Gear Bleed Hydraulic System No. 3 External Leak Check of the Landing Gear Functional Test of the Landing Gear Extension/ Retraction System Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors 2. Job Set−Up Subtask 32−33−01−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. 3. Procedure Subtask 32−33−01−420−001 Refer to Figure 401. A. Install the extension/retraction actuator (2) as follows: (1) Put the extension/retraction actuator (2) in position on the NLG assembly and install the pins (11) and (20). (2) Put the retaining plate (19) in position at the lower end of the extension/retraction actuator (2) to lock the pin (20). Make sure that the flat sides of the pin are correctly engaged with the contour of the retaining plate. (3) Install the bolt (16) with the washers (17) and (18). (4) Install the washers (15) and (14), and the nut (13). (5) Torque the nut (13) to 25−30 pound−inches (2.82−3.39 N·m). (6) Safety the nut (13) with the cotter pin (12). (7) Put the retaining plate (10) in position at the upper end of the extension/retraction actuator (2) to lock the pin (11). Make sure that the flat sides of the pin are correctly engaged with the contour of the retaining plate. (8) Install the bolt (7) with the washers (8) and (9). (9) Install the washers (6) and (5), and the nut (4). (10) Torque the nut (4) to 25−30 pound−inches (2.82−3.39 N·m). (11) Safety the nut (4) with the cotter pin (3). (12) Remove the protective caps and plugs from all open hydraulic lines and union fittings or ports. Master EFFECTIVITY: See Pageblock 32−33−01 page 401 32−33−01 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (13) If the extension/retraction actuator (2) that was installed in this task is not the one that was removed in the removal task, do the steps that follow: (a) Lightly lubricate two new preformed packings (22) with 02−001 hydraulic fluid. (b) Install the preformed packings (22) on the union fittings (21). (c) Install the union fittings (21) into the extension and retraction ports in the extension/retraction actuator (2). (14) Connect the hydraulic lines (1) to the union fittings (21). 4. Close Out Subtask 32−33−01−640−001 A. Lubricate the grease fittings on each end of the extension/retraction actuator (Ref. TASK 12−20−32−640−801). Subtask 32−33−01−160−001 B. Clean all signs of hydraulic fluid from the extension/retraction actuator (2) and the surrounding work area. Subtask 32−33−01−941−002 C. Remove all tools, equipment, and unwanted materials from the work area. Subtask 32−33−01−410−001 D. Close the NLG forward doors (Ref. TASK 32−22−01−980−802). Subtask 32−33−01−870−001 E. Bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−33−01−710−001 F. Do an functional test of the extension and retraction system (Ref. TASK 32−30−00−720−801). Master EFFECTIVITY: See Pageblock 32−33−01 page 401 32−33−01 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−33−01−010−002 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the NLG forward doors (Ref. TASK 32−22−01−980−801). WARNING: G. Subtask 32−33−01−210−001 H. Examine the work area for leaks (Ref. TASK 32−00−00−790−801). Subtask 32−33−01−410−002 I. Close the NLG forward doors (Ref. TASK 32−22−01−980−802). Master EFFECTIVITY: See Pageblock 32−33−01 page 401 32−33−01 Page 407 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL UPLOCK ASSEMBLY, NLG − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the uplock assembly for the nose landing gear (NLG). The NLG uplock assembly is installed on the center of the nosewheel well ceiling. TASK 32−33−05−000−801 Removal of the NLG Uplock Assembly 1. Job Set−Up Information Subtask 32−33−05−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Flat pan, hydraulic fluid resistant Subtask 32−33−05−946−001 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 32−22−01−980−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Open and Isolate the Nose−Landing−Gear Forward Doors 2. Job Set−Up Subtask 32−33−05−490−002 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. Master EFFECTIVITY: See Pageblock 32−33−05 page 401 32−33−05 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−33−05−010−001 IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Open and isolate the NLG forward doors (Ref. TASK 32−22−01−980−801). WARNING: B. 3. Procedure Subtask 32−33−05−020−001 Refer to Figure 401. A. Remove the NLG uplock assembly (6) as follows: (1) Put a hydraulic fluid resistant flat pan (or equivalent container) under the work area to collect any hydraulic fluid leakage. (2) Disconnect the hydraulic lines (7) and (8). Install protective caps and plugs on all open hydraulic lines and ports. (3) Remove and discard the lockwire from the nuts (14) and (15). (4) Remove the nut (14) and remove the proximity sensor(1), the keywasher (16), and the nut (15) from the mounting bracket on the NLG uplock assembly (6). (5) Remove and discard the cotter pin (2) from the collar (3). (6) Remove the collar (3) from the pin of the emergency release lever (5). (7) From each mounting point (three places), remove the cotter pin (9), the nut (10), and the washer (11). Discard the cotter pins. (8) Hold the NLG uplock assembly (6) and carefully remove the bolts (12) and the spacers (13). (9) Disengage the pin of the emergency release lever (5) from the emergency release link (4) and remove the NLG uplock assembly (6) from the support structure. Master EFFECTIVITY: See Pageblock 32−33−05 page 401 32−33−05 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3 2 A LEGEND. 1. PS3GA proximity sensor. 2. Cotter pin. 3. Collar. 4. Emergency release link. 5. Emergency release lever. 6. Uplock assembly. 7. Hydraulic line. 8. Hydraulic line. 9. Cotter pin. FW 10. Nut. D 11. Washer. 12. Bolt. 13. Spacer. 14. Nut. 15. Nut. 7 16. Keywasher. 4 10 11 9 12 1 15 14 16 B 1 0.035−0.045 in. (0.90−1.14 mm). B 8 MOUNTING BRACKET (REF) 13 NOTE 1 NLG uplock to be locked to adjust the proximity sensor. 6 A UPLOCK ASSEMBLY ram3233054_001(1).dc, rs/rm, 31/03/97 5 NLG Uplock Assembly − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−33−05 page 401 32−33−05 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−33−05−400−801 Installation of the NLG Uplock Assembly 1. Job Set−Up Information Subtask 32−33−05−944−001 A. Consumable Materials REFERENCE 05−004 DESIGNATION Lockwire Subtask 32−33−05−945−001 B. Parts REF 2 3 9 10 11 12 13 14 15 16 NAME OF PART Cotter pin Collar Cotter pin Nut Washer Bolt Spacer Nut Nut Keywasher QTY 1 1 3 3 3 3 3 1 1 1 IPC SEQUENCE NO. IPC 32−33−05−01−045 IPC 32−33−05−01−040 IPC 32−33−05−01−030 IPC 32−33−05−01−025 IPC 32−33−05−01−020 IPC 32−33−05−01−010 IPC 32−33−05−01−015 IPC 32−61−05−02−030 IPC 32−61−05−02−030 IPC 32−61−05−02−025 Subtask 32−33−05−946−002 C. Reference Information REFERENCE TASK 32−33−05−820−801 TASK 32−34−00−710−801 TASK 32−61−00−710−801 DESIGNATION Alignment of the NLG Uplock Pin with the NLG Uplock Assembly Operational Test of the Landing Gear Manual−Release−System Operational Test of the PSS 2. Job Set−Up Subtask 32−33−05−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. Master EFFECTIVITY: See Pageblock 32−33−05 page 401 32−33−05 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 3. Procedure Subtask 32−33−05−420−001 Refer to Figure 401. A. Install the NLG uplock assembly (6) as follows: (1) Hold the NLG uplock assembly (6) in position in its support structure and engage the pin of the emergency release lever (5) with the emergency release link (4). (2) Install the spacers (13), the bolts (12), the washers (11), and the nuts (10) (three places). (3) Safety the nuts (10) with the cotter pins (9). (4) Install the collar (3) on the pin of the emergency release lever (5). (5) Safety the collar (3) with the cotter pin (2). (6) Put the PS3GA proximity sensor (1) (with the nut (15) and the keywasher (16) attached) in the mounting bracket on the uplock assembly (6). Loosely install the nut (14) on the PS3GA proximity sensor (1). (7) Manually close the uplock latch to adjust the PS3GA proximity sensor (3) with its target. NOTE: Make sure that the uplock latch is unlocked after the adjustment is done. (8) Adjust the nuts (14) and (15) to get a sensor−to−target clearance of 0.035 to 0.045 inch (0.9 mm to 1.14 mm). NOTE: Each turn of the adjusting nuts (14) and (15) increases or decreases the sensor−to−target clearance by 0.042 inch (1.07 mm). (9) Manually move the manual release lever (in the NLG bay) to unlock the NLG uplock latch. (10) Safety the two adjusting nuts (14) and (15) together with 05−004 lockwire. (11) Remove the protective caps and plugs from the hydraulic lines and ports and connect the hydraulic lines (7) and (8) to the NLG uplock assembly (6). 4. Close Out Subtask 32−33−05−100−001 A. Clean all signs of hydraulic fluid from the uplock assembly and the surrounding area. Subtask 32−33−05−941−001 B. Remove all tools, equipment, and unwanted materials from the work area. Subtask 32−33−05−820−001 C. Do the alignment of the NLG uplock pin (Ref. TASK 32−33−05−820−801). Subtask 32−33−05−720−001 D. E. Do an operational test of the proximity sensor system (Ref. TASK 32−61−00−710−801). Do an operational test of the manual release system of the landing gear (Ref. TASK 32−34−00−710−801). Master EFFECTIVITY: See Pageblock 32−33−05 page 401 32−33−05 Page 405 Apr 20/2004 C See Effective TR AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL UPLOCK ASSEMBLY, NOSE LANDING GEAR (NLG) − ADJUSTMENT/TEST 1. General A. The maintenance procedures that follow are for the alignment of the nose landing gear (NLG) uplock pin with the latch of the NLG uplock assembly using a hydraulic test stand or the aircraft ACMP 3A hydraulic pump. The NLG uplock pin is installed on the forward side of the NLG shock strut piston at its lower end. The NLG uplock assembly is installed in the ceiling of the nosewheel well at BL 0.00. TASK 32−33−05−820−801 Alignment of the NLG Uplock Pin with the NLG Uplock Assembly (Hydraulic Test Stand Method) 1. Job Set−Up Information Subtask 32−33−05−943−002 A. Tools and Equipment REFERENCE None specified DESIGNATION Torque wrench 0 to 100 pound−inches (0 to 11.6 N·m) Subtask 32−33−05−944−002 B. Consumable Materials REFERENCE 05−004 05−015 DESIGNATION Lockwire Plasticine (rigging compound) Subtask 32−33−05−946−005 C. Reference Information REFERENCE TASK 07−11−01−582−802 TASK 10−11−00−000−801 TASK 10−11−00−400−802 TASK 29−00−00−910−801 TASK 32−33−00−840−801 TASK 32−33−00−840−802 DESIGNATION Jacking of the Aircraft from the Nose Removal of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Hydraulic Safety Precautions Installation of the Support Equipment for NLG Extension and Retraction Removal of the Support Equipment for NLG Extension and Retraction Master EFFECTIVITY: See Pageblock 32−33−05 page 501 501 32−33−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 2. Job Set−Up Subtask 32−33−05−582−001 A. Lift the aircraft at the nose jacking point at FS278.00 with a jack (Ref. TASK 07−11−01−582−802). Make sure that there is a minimum of 1.0 inch (2.5 cm) clearance and a maximum of 2.0 inches (5.0 cm) clearance between the NLG wheels and the ground. Subtask 32−33−05−910−005 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: B. Subtask 32−33−05−490−003 C. D. Install the support equipment that is required to isolate the hydraulic system (Ref. TASK 32−33−00−840−801). If installed, remove the safety lockpin from the NLG (Ref. TASK 10−11−00−000−801). Make sure that the safety lockpins are installed at the MLG (Ref. TASK 10−11−00−400−802). Subtask 32−33−05−840−001 **ON A/C 7011−7014, 7017−7018, 7022, 7026, 7028−7031, 7034−7035, 7037−7038, 7040, 7042−7044, 7046, 7048, 7050, 7052, 7055, 7059, 7061−7063, 7066−7067, 7069−7070, 7072, 7074−7077 Pre SBA601R−32−041 Refer to Figure 502. **ON A/C 7003−7067, 7069−7990, 8000−8010 Pre VSBM−DTSB16040−32−23 Refer to Figure 503. **ON A/C 7003−7010, 7015−7016, 7019−7021, 7023−7025, 7027, 7032−7033, 7036, 7039, 7041, 7045, 7047, 7049, 7051, 7053−7054, 7056−7058, 7060, 7064−7065, 7071, 7073, 7078−7990, 8000−8064, 8066−8068 and ON A/C 7011−7014, 7017−7018, 7022, 7026, 7028−7031, 7034−7035, 7037−7038, 7040, 7042−7044, 7046, 7048, 7050, 7052, 7055, 7059, 7061−7063, 7066−7067, 7069−7070, 7072, 7074−7077 Post SBA601R−32−041 Refer to Figure 504. **ON A/C 8011−8064, 8066−8068 and ON A/C 7003−7067, 7069−7990, 8000−8010 Post VSBM−DTSB16040−32−23 Refer to Figure 505. **ON A/C ALL E. Do the steps that follow to prepare for the alignment of the NLG uplock assembly (1) with the NLG uplock pin (2): (1) Make sure that the uplock pin (2) at the bottom of the NLG shock strut piston can rotate freely in the uplock pin bracket (3). If the uplock pin (2) at the bottom of the NLG shock strut piston cannot rotate freely in the uplock pin bracket (3), do the steps that follow: Master EFFECTIVITY: See Pageblock 32−33−05 page 501 502 32−33−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (a) Remove the cotter pin (4) from the uplock pin (2). (b) Adjust the nut (5) on the uplock pin (2) so that the uplock pin (2) can rotate freely and that it has a maximum sideplay of 0.020 inch (0.05 cm) between the washer (6) and the uplock pin bracket (3). (c) Do not install the cotter pin (4) or torque the nut (5) at this time. This will be done in a later step. (2) Apply a layer of 05−015 plasticine (or other equivalent rigging compound) to the root of the uplock latch (7) in the NLG uplock assembly (1). NOTE: When the gear is retracted, the plasticine will be deformed to the clearance dimension between the uplock pin (2) at the bottom of the NLG and the root of the uplock latch (7). 3. Procedure Refer to Figure 501. **ON A/C 7011−7014, 7017−7018, 7022, 7026, 7028−7031, 7034−7035, 7037−7038, 7040, 7042−7044, 7046, 7048, 7050, 7052, 7055, 7059, 7061−7063, 7066−7067, 7069−7070, 7072, 7074−7077 Pre SBA601R−32−041 Refer to Figure 502. **ON A/C 7003−7067, 7069−7990, 8000−8010 Pre VSBM−DTSB16040−32−23 Refer to Figure 503. **ON A/C 7003−7010, 7015−7016, 7019−7021, 7023−7025, 7027, 7032−7033, 7036, 7039, 7041, 7045, 7047, 7049, 7051, 7053−7054, 7056−7058, 7060, 7064−7065, 7071, 7073, 7078−7990, 8000−8064, 8066−8068 and ON A/C 7011−7014, 7017−7018, 7022, 7026, 7028−7031, 7034−7035, 7037−7038, 7040, 7042−7044, 7046, 7048, 7050, 7052, 7055, 7059, 7061−7063, 7066−7067, 7069−7070, 7072, 7074−7077 Post SBA601R−32−041 Refer to Figure 504. **ON A/C 8011−8064, 8066−8068 and ON A/C 7003−7067, 7069−7990, 8000−8010 Post VSBM−DTSB16040−32−23 Refer to Figure 505. **ON A/C ALL Subtask 32−33−05−820−007 A. Do the alignment test of the NLG uplock assembly (1) using the hydraulic test stand as follows: (1) At the test stand, slowly increase the hydraulic fluid pressure in hydraulic hose No. 7 and slowly retract the NLG. When the uplock pin (2) is approximately 1 inch (2.54 cm) from the NLG uplock assembly (1), reduce the hydraulic fluid pressure in hydraulic hose No. 7 to stop the retraction of the NLG. (2) Make sure that the NLG uplock assembly (1) is in the center of the uplock pin Master EFFECTIVITY: See Pageblock 32−33−05 page 501 503 32−33−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL bracket (3). NOTE: Make sure that there will be a minimum clearance of 0.150 inch (0.381 cm) between the NLG uplock assembly (1) on both sides of the uplock pin bracket (3). (3) Slowly increase the hydraulic fluid pressure in hydraulic hose No. 7 until the uplock pin (2) is locked in the uplock latch (7). NOTE: Make sure that the retract pressure is not more than 650 psi (4482 kPa). (4) Keep the hydraulic fluid pressure applied for 2 minutes and make sure that there are no hydraulic fluid leaks around the work area. (5) Release the hydraulic fluid pressure from hydraulic hose No. 7. (6) Wait for a minimum of two minutes and then make sure that the NLG stayed locked in the uplock latch (7). **ON A/C 7003−7067, 7069−7200 Pre VSBM−DT−16600−32−1 WITH 601R85002−91 UP LOCK ASSEMBLY NOT INSTALLED (7) After the two minute period, slowly increase the hydraulic fluid pressure in hose No. 8 until the NLG is released from the NLG uplock assembly (1). Make sure that the NLG uplock assembly (1) releases between 350 and 550 psig (2413 and 3792 kPa). **ON A/C 7201−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7200 Post VSBM−DT−16600−32−1 (8) After the two minute period, slowly increase the hydraulic fluid pressure in hose No. 8 until the NLG is released from the NLG uplock assembly (1). Make sure that the NLG uplock assembly (1) releases between 150 and 400 psig (1034 and 2758 kPa). **ON A/C ALL (9) Adjust the hydraulic fluid pressure in hose No. 8 to a minimum of 200 psi (1379 kPa) and extend the NLG. (10) Make sure that the NLG is down and locked. (11) Increase the hydraulic fluid pressure to 3000 psi (20684 kPa) in hose No. 8. Keep the hydraulic fluid pressure applied for 2 minutes and make sure that there are no hydraulic fluid leaks around the work area. (12) Release the hydraulic fluid pressure from hose No. 8. **ON A/C 7011−7014, 7017−7018, 7022, 7026, 7028−7031, 7034−7035, 7037−7038, 7040, 7042−7044, 7046, 7048, 7050, 7052, 7055, 7059, 7061−7063, 7066−7067, 7069−7070, 7072, 7074−7077 Pre SBA601R−32−041 (13) Measure the thickness of the deformed 05−015 plasticine where the uplock pin (2) engaged the uplock latch (7). Make sure that the thickness is 0.110−0.190 inch (0.279−0.483 cm). NOTE: The thickness of the deformed 05−015 plasticine shows the clearance that was between the uplock pin (2) and the root of the uplock latch (7) when the NLG was retracted and locked. **ON A/C 7003−7067, 7069−7990, 8000−8010 Pre VSBM−DTSB16040−32−23 (14) Measure the thickness of the deformed 05−015 plasticine where the uplock pin (2) engaged the uplock latch (7). Make sure that the thickness is 0.110−0.190 inch Master EFFECTIVITY: See Pageblock 32−33−05 page 501 504 32−33−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (0.279−0.483 cm). NOTE: The thickness of the deformed 05−015 plasticine shows the clearance that was between the uplock pin (2) and the root of the uplock latch (7) when the NLG was retracted and locked. **ON A/C 7003−7010, 7015−7016, 7019−7021, 7023−7025, 7027, 7032−7033, 7036, 7039, 7041, 7045, 7047, 7049, 7051, 7053−7054, 7056−7058, 7060, 7064−7065, 7071, 7073, 7078−7990, 8000−8064, 8066−8068 and ON A/C 7011−7014, 7017−7018, 7022, 7026, 7028−7031, 7034−7035, 7037−7038, 7040, 7042−7044, 7046, 7048, 7050, 7052, 7055, 7059, 7061−7063, 7066−7067, 7069−7070, 7072, 7074−7077 Post SBA601R−32−041 (15) Measure the thickness of the deformed 05−015 plasticine where the uplock pin (2) engaged the uplock latch (7). Make sure that the thickness is 0.125−0.205 inch (0.318−0.520 cm). NOTE: The thickness of the deformed 05−015 plasticine shows the clearance that was between the uplock pin (2) and the root of the uplock latch (7) when the NLG was retracted and locked. **ON A/C 8011−8064, 8066−8068 and ON A/C 7003−7067, 7069−7990, 8000−8010 Post VSBM−DTSB16040−32−23 (16) Measure the thickness of the deformed 05−015 plasticine where the uplock pin (2) engaged the uplock latch (7). Make sure that the thickness is 0.125−0.205 inch (0.318−0.520 cm). NOTE: The thickness of the deformed 05−015 plasticine shows the clearance that was between the uplock pin (2) and the root of the uplock latch (7) when the NLG was retracted and locked. **ON A/C ALL (17) If the specified dimension between the uplock pin (2) and the uplock latch (7) is correct, do the steps that follow: (a) If it was removed, safety the nut (5) on the uplock pin (2) with the cotter pin (4). NOTE: Make sure that the uplock pin (2) can rotate easily and that there is a maximum sideplay of 0.020 inch (0.05 cm) between the washer (6) and the uplock pin bracket (3). (b) Go to the Close−Out section of this procedure. (18) If you did not get the dimension specified in the step above, do the steps that follow to adjust the uplock pin bracket (3): (a) If it was not removed in an earlier step, remove the cotter pin (4) from the uplock pin (2). (b) Remove the nut (5) and the washer (6) from the uplock pin (2). (c) Remove the uplock pin (2) from the uplock pin bracket (3). (d) Remove the lockwire that secures the bolts (8) to the uplock pin bracket (3). (e) Loosen the bolts (8) (with the washers (9)) a sufficient amount so that the uplock pin bracket (3) can be moved vertically on the serrated uplock plate (10). (f) Move the uplock pin bracket (3) up or down on the serrated uplock plate (10) as necessary to get the required dimension between the uplock pin (2) and the Master EFFECTIVITY: See Pageblock 32−33−05 page 501 505 32−33−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL root of the uplock latch (7) when the NLG is retracted and locked. NOTE: The movement of one serration up of the uplock pin bracket (3) on the serrated uplock plate (10) is equal to a increase of 0.080 inch (0.20 cm) in the required dimension between the uplock pin (2) and the root of the uplock latch (7). (g) Temporarily tighten the bolts (8) to secure the uplock pin bracket (3) and the serrated uplock plate (10) to the NLG. (h) Temporarily install the uplock pin (2) in the uplock pin bracket (3), the washer (6), and the nut (5). (i) Temporarily tighten the nut (5). Make sure that the uplock pin (2) can rotate freely in the uplock pin bracket (3). (19) If you did not get the clearance between the NLG uplock assembly (1) and both sides of the uplock pin bracket (3), do the steps that follow to adjust the uplock pin bracket (3): (a) If it was not removed in an earlier step, remove the cotter pin (4) from the uplock pin (2). (b) Remove the nut (5) and the washer (6) from the uplock pin (2). (c) Remove the uplock pin (2) from the uplock pin bracket (3). (d) Remove the lockwire that secures the bolts (8) to the uplock pin bracket (3). (e) Loosen the bolts (8) (with the washers (9)) a sufficient amount so that the uplock pin bracket (3) can be moved horizontally but not vertically on the serrated uplock plate (10). (f) Adjust the uplock pin bracket (3) to get a minimum clearance of 0.150 inch (0.381 cm) between the NLG uplock assembly (1) and both sides of the uplock pin bracket (3). (g) Temporarily tighten the bolts (8) to secure the uplock pin bracket (3) and the serrated uplock plate (10) to the NLG. (h) Temporarily install the uplock pin (2) in the uplock pin bracket (3), the washer (6), and the nut (5). (i) Temporarily tighten the nut (5). Make sure that the uplock pin (2) can rotate freely in the uplock pin bracket (3). Subtask 32−33−05−820−003 B. If the specified gap (step A−13 or step A−14) was not obtained, apply more plasticine to the root of the uplock latch assembly. Retract the NLG and repeat steps A−13 and subsequent until you get the specified dimension between the uplock pin (2) and the uplock latch (7). Subtask 32−33−05−430−001 C. If the specified dimension between the uplock pin (2) and the uplock latch (7) is now correct, do the steps that follow: (1) To get access to the two bolts (8), remove the nut (5), the washer (6), and the uplock pin (2) from the uplock pin bracket (3). Master EFFECTIVITY: See Pageblock 32−33−05 page 501 32−33−05 Page 506 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL (2) (3) (4) (5) (6) (7) Torque the two bolts (8) from 50 to 60 pound−inches (5.7 to 6.8 N·m). Safety the two bolts (8) together with 05−004 lockwire. Safety the two bolts (8) to the uplock pin bracket (3) with 05−004 lockwire. Install the uplock pin (2) in the uplock pin bracket (3). Install the washer (6), and the nut (5) on the uplock pin (2). Safety the nut (5) on the uplock pin (2) with the cotter pin (4). NOTE: Make sure that the uplock pin (2) can rotate easily and that there is a maximum sideplay of 0.020 inch (0.05 cm) between the washer (6) and the uplock pin bracket (3). Subtask 32−33−05−140−001 D. Remove any 05−015 plasticine (or equivalent) that remains on the uplock pin (2) and on the uplock latch (7). 4. Close Out Subtask 32−33−05−820−006 A. At the test stand, make sure the hydraulic fluid pressure is released from hydraulic hoses No. 7 and No. 8. Subtask 32−33−05−090−001 B. Remove the support equipment that was required to isolate the hydraulic system (Ref. TASK 32−33−00−840−802). Subtask 32−33−05−582−002 C. Lower the aircraft at the nose jacking point at FS278.00 and remove the jack (Ref. TASK 07−11−01−582−802). Master EFFECTIVITY: See Pageblock 32−33−05 page 501 507 32−33−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL FS 196.50 FS 195.00 GEAR UP UPLOCK ACTUATOR GEAR DOWN TO RETRACTION ACTUATOR DOWN LOCK ACTUATOR Test equipment. HYDRAULIC HOSE NO.8 (REF) GEAR DOWN GEAR UP HYDRAULIC HOSE NO.7 (REF) HYDRAULIC TEST STAND LBL 13.70 FS 180.25 AU VU NLG BYPASS VALVE (REF) NLG WHEEL WELL PLAN VIEW ram3233055_001.dg, sb/rm, 03/02/03 VD Hydraulic Test Circuit − Adjustment/Test Figure 501 Master EFFECTIVITY: See Pageblock 32−33−05 page 501 32−33−05 Page 508 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL 1 0.150 in. (0.381 cm) MINIMUM 0.150 in. (0.381 cm) MINIMUM A 5 2 6 3 0.020 in. (0.050 cm) MAXIMUM AND FREE TO ROTATE LEGEND 1. NLG uplock assembly. 2. Uplock pin. 3. Uplock pin bracket. 4. Cotter pin. 5. Nut. 6. Washer. 7. Uplock latch. 8. Bolt. 9. Washer. 10. Serrated uplock plate. 1 0.110 − 0.190 in. (0.279 − 0.483 cm) 7 2 4 5 6 3 2 9 8 ram3233055_002.dg, gv/rm, 03/02/03 10 NLG Uplock Assembly Clearances − Adjustment/Test Figure 502 Master EFFECTIVITY: See Pageblock 32−33−05 page 501 32−33−05 Page 509 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL 1 0.150 in. (0.381 cm) MINIMUM 0.150 in. (0.381 cm) MINIMUM 5 A 2 6 3 0.020 in. (0.050 cm) MAXIMUM AND FREE TO ROTATE LEGEND 1. NLG uplock assembly. 2. Uplock pin. 3. Uplock pin bracket. 4. Cotter pin. 5. Nut. 6. Washer. 7. Uplock latch. 8. Bolt. 9. Washer. 10. Serrated uplock plate. 1 0.110 − 0.190 in. (0.279 − 0.483 cm) 7 2 4 5 6 3 2 9 8 ram3233055_004.dg, gv/lr, 23/11/04 10 NLG Uplock Assembly Clearances − Adjustment/Test Figure 503 Master EFFECTIVITY: See Pageblock 32−33−05 page 501 32−33−05 Page 510 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL 1 0.150 in. (0.381 cm) MINIMUM 0.150 in. (0.381 cm) MINIMUM 5 A 2 6 3 0.020 in. (0.050 cm) MAXIMUM AND FREE TO ROTATE LEGEND 1. NLG uplock assembly. 2. Uplock pin. 3. Uplock pin bracket. 4. Cotter pin. 5. Nut. 6. Washer. 7. Uplock latch. 8. Bolt. 9. Washer. 10. Serrated uplock plate. 1 0.125 − 0.205 in. (0.318 − 0.520 cm) 7 2 4 5 6 3 2 9 8 ram3233055_003.dg, gv/rm, 03/02/03 10 NLG Uplock Assembly Clearances − Adjustment/Test Figure 504 Master EFFECTIVITY: See Pageblock 32−33−05 page 501 32−33−05 Page 511 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL 1 0.150 in. (0.381 cm) MINIMUM 0.150 in. (0.381 cm) MINIMUM 5 A 2 6 3 0.020 in. (0.050 cm) MAXIMUM AND FREE TO ROTATE LEGEND 1. NLG uplock assembly. 2. Uplock pin. 3. Uplock pin bracket. 4. Cotter pin. 5. Nut. 6. Washer. 7. Uplock latch. 8. Bolt. 9. Washer. 10. Serrated uplock plate. 1 0.125 − 0.205 in. (0.318 − 0.520 cm) 7 2 4 5 6 3 2 9 8 ram3233055_005.dg, gv/lr, 24/11/04 10 NLG Uplock Assembly Clearances − Adjustment/Test Figure 505 Master EFFECTIVITY: See Pageblock 32−33−05 page 501 32−33−05 Page 512 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL TASK 32−33−05−820−802 Alignment of the NLG Uplock Pin with the NLG Uplock Assembly (ACMP 3A Method) 1. Job Set−Up Information Subtask 32−33−05−943−003 A. Tools and Equipment REFERENCE None specified DESIGNATION Torque wrench 0 to 100 pound−inches (0 to 11.6 N·m) Subtask 32−33−05−944−003 B. Consumable Materials REFERENCE 05−004 05−015 DESIGNATION Lockwire Plasticine (rigging compound) Subtask 32−33−05−946−003 C. Reference Information REFERENCE TASK 07−11−01−582−802 TASK 10−11−00−000−801 TASK 10−11−00−400−802 TASK 29−00−00−910−801 DESIGNATION Jacking of the Aircraft from the Nose Removal of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Hydraulic Safety Precautions 2. Job Set−Up Subtask 32−33−05−010−002 A. Open the access panel that follows: ACCESS 122CR DESIGNATION Door, external service panel Subtask 32−33−05−582−003 B. Lift the aircraft at the nose jacking point at FS278.00 with a jack (Ref. TASK 07−11−01−582−802). Make sure that there is a minimum of 1.0 inch (2.5 cm) clearance and a maximum of 2.0 inches (5.0 cm) clearance between the NLG wheels and the ground. Master EFFECTIVITY: See Pageblock 32−33−05 page 501 513 32−33−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−33−05−910−001 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: C. Subtask 32−33−05−840−003 D. At the external services panel, put the NOSE DOOR maintenance switch to the OPEN position. Subtask 32−33−05−030−001 E. If installed, remove the safety lockpin from the NLG (Ref. TASK 10−11−00−000−801). Make sure that the safety lockpins are installed at the MLG (Ref. TASK 10−11−00−400−802). Subtask 32−33−05−840−002 **ON A/C 7011−7014, 7017−7018, 7022, 7026, 7028−7031, 7034−7035, 7037−7038, 7040, 7042−7044, 7046, 7048, 7050, 7052, 7055, 7059, 7061−7063, 7066−7067, 7069−7070, 7072, 7074−7077 Pre SBA601R−32−041 Refer to Figure 506. **ON A/C 7003−7067, 7069−7990, 8000−8010 Pre VSBM−DTSB16040−32−23 Refer to Figure 507. **ON A/C 7003−7010, 7015−7016, 7019−7021, 7023−7025, 7027, 7032−7033, 7036, 7039, 7041, 7045, 7047, 7049, 7051, 7053−7054, 7056−7058, 7060, 7064−7065, 7071, 7073, 7078−7990, 8000−8064, 8066−8068 and ON A/C 7011−7014, 7017−7018, 7022, 7026, 7028−7031, 7034−7035, 7037−7038, 7040, 7042−7044, 7046, 7048, 7050, 7052, 7055, 7059, 7061−7063, 7066−7067, 7069−7070, 7072, 7074−7077 Post SBA601R−32−041 Refer to Figure 508. **ON A/C 8011−8064, 8066−8068 and ON A/C 7003−7067, 7069−7990, 8000−8010 Post VSBM−DTSB16040−32−23 Refer to Figure 509. **ON A/C ALL F. Do the steps that follow to prepare for the alignment of the NLG uplock assembly (1) with the NLG uplock pin (2): (1) Make sure that the uplock pin (2) at the bottom of the NLG shock strut piston can rotate freely in the uplock pin bracket (3). If the uplock pin (2) at the bottom of the NLG shock strut piston cannot rotate freely in the uplock pin bracket (3), do the steps that follow: (a) Remove the cotter pin (4) from the uplock pin (2). (b) Adjust the nut (5) on the uplock pin (2) so that the uplock pin (2) can rotate freely and that it has a maximum sideplay of 0.020 inch (0.05 cm) between the washer (6) and the uplock pin bracket (3). Master EFFECTIVITY: See Pageblock 32−33−05 page 501 514 32−33−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (c) Do not install the cotter pin (4) or torque the nut (5) at this time. This will be done in a later step. (2) Apply a layer of 05−015 plasticine (or other equivalent rigging compound) to the root of the uplock latch (7) in the NLG uplock assembly (1). NOTE: When the gear is retracted, the plasticine will be deformed to the clearance dimension between the uplock pin (2) at the bottom of the NLG and the root of the uplock latch (7). 3. Procedure **ON A/C 7011−7014, 7017−7018, 7022, 7026, 7028−7031, 7034−7035, 7037−7038, 7040, 7042−7044, 7046, 7048, 7050, 7052, 7055, 7059, 7061−7063, 7066−7067, 7069−7070, 7072, 7074−7077 Pre SBA601R−32−041 Refer to Figure 506. **ON A/C 7003−7067, 7069−7990, 8000−8010 Pre VSBM−DTSB16040−32−23 Refer to Figure 507. **ON A/C 7003−7010, 7015−7016, 7019−7021, 7023−7025, 7027, 7032−7033, 7036, 7039, 7041, 7045, 7047, 7049, 7051, 7053−7054, 7056−7058, 7060, 7064−7065, 7071, 7073, 7078−7990, 8000−8064, 8066−8068 and ON A/C 7011−7014, 7017−7018, 7022, 7026, 7028−7031, 7034−7035, 7037−7038, 7040, 7042−7044, 7046, 7048, 7050, 7052, 7055, 7059, 7061−7063, 7066−7067, 7069−7070, 7072, 7074−7077 Post SBA601R−32−041 Refer to Figure 508. **ON A/C 8011−8064, 8066−8068 and ON A/C 7003−7067, 7069−7990, 8000−8010 Post VSBM−DTSB16040−32−23 Refer to Figure 509. **ON A/C ALL Subtask 32−33−05−820−008 A. Do the alignment of the NLG assembly using the hydraulic ACMP 3A as follows: (1) Push the HYD push−button on the engine indication and crew alerting system (EICAS) control panel to get the hydraulic synoptic page on the display. NOTE: Make sure the No. 3 hydraulic system pressure is zero. (2) Put the LDG GEAR control handle to the UP position. (3) To retract the NLG slowly to check for proper alignment, quickly put the ACMP 3A switch from ON to OFF several times. When the uplock pin (2) is approximately 1 inch (2.54 cm) from the NLG uplock assembly (1) put the ACMP 3A to OFF to stop the retraction of the NLG. NOTE: The residual hydraulic pressure in the No. 3 system will keep the NLG in position while the clearances are checked. (4) Make sure that the NLG uplock assembly (1) is in the center of the uplock pin bracket (3). NOTE: Make sure that there will be a minimum clearance of 0.150 inch (0.381 cm) between the NLG uplock assembly (1) on both sides of the uplock pin bracket (3). Master EFFECTIVITY: See Pageblock 32−33−05 page 501 515 32−33−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (5) Put the ACMP 3A switch to ON and make sure the uplock pin (2) is locked in the uplock latch (7). (6) Keep the hydraulic fluid pressure applied for 2 minutes and make sure that there are no hydraulic fluid leaks around the work area. (7) Put the ACMP 3A switch to OFF and deplete the No. 3 hydraulic pressure to zero. (8) Wait for a minimum of two minutes and then make sure that the NLG stayed locked in the uplock latch (7). (9) Put the ACMP 3A switch to ON and make sure the No. 3 hydraulic system pressure is 3000 psi (20684 kPa). (10) Put the LDG GEAR control handle to the DOWN position and make sure that the NLG is down and locked. (11) Keep the hydraulic fluid pressure applied for 2 minutes and make sure that there are no hydraulic fluid leaks around the work area. (12) Put the ACMP 3A switch to OFF and deplete the No. 3 hydraulic pressure to zero. **ON A/C 7011−7014, 7017−7018, 7022, 7026, 7028−7031, 7034−7035, 7037−7038, 7040, 7042−7044, 7046, 7048, 7050, 7052, 7055, 7059, 7061−7063, 7066−7067, 7069−7070, 7072, 7074−7077 Pre SBA601R−32−041 (13) Measure the thickness of the deformed 05−015 plasticine where the uplock pin (2) engaged the uplock latch (7). Make sure that the thickness is 0.110−0.190 inch (0.279−0.483 cm). NOTE: The thickness of the deformed 05−015 plasticine shows the clearance that was between the uplock pin (2) and the root of the uplock latch (7) when the NLG was retracted and locked. **ON A/C 7003−7067, 7069−7990, 8000−8010 Pre VSBM−DTSB16040−32−23 (14) Measure the thickness of the deformed 05−015 plasticine where the uplock pin (2) engaged the uplock latch (7). Make sure that the thickness is 0.110−0.190 inch (0.279−0.483 cm). NOTE: The thickness of the deformed 05−015 plasticine shows the clearance that was between the uplock pin (2) and the root of the uplock latch (7) when the NLG was retracted and locked. **ON A/C 7003−7010, 7015−7016, 7019−7021, 7023−7025, 7027, 7032−7033, 7036, 7039, 7041, 7045, 7047, 7049, 7051, 7053−7054, 7056−7058, 7060, 7064−7065, 7071, 7073, 7078−7990, 8000−8064, 8066−8068 and ON A/C 7011−7014, 7017−7018, 7022, 7026, 7028−7031, 7034−7035, 7037−7038, 7040, 7042−7044, 7046, 7048, 7050, 7052, 7055, 7059, 7061−7063, 7066−7067, 7069−7070, 7072, 7074−7077 Post SBA601R−32−041 (15) Measure the thickness of the deformed 05−015 plasticine where the uplock pin (2) engaged the uplock latch (7). Make sure that the thickness is 0.125−0.205 inch (0.318−0.520 cm). NOTE: The thickness of the deformed 05−015 plasticine shows the clearance that was between the uplock pin (2) and the root of the uplock latch (7) when the NLG was retracted and locked. **ON A/C 8011−8064, 8066−8068 and ON A/C 7003−7067, 7069−7990, 8000−8010 Post VSBM−DTSB16040−32−23 (16) Measure the thickness of the deformed 05−015 plasticine where the uplock pin (2) engaged the uplock latch (7). Make sure that the thickness is 0.125−0.205 inch Master EFFECTIVITY: See Pageblock 32−33−05 page 501 516 32−33−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (0.318−0.520 cm). NOTE: The thickness of the deformed 05−015 plasticine shows the clearance that was between the uplock pin (2) and the root of the uplock latch (7) when the NLG was retracted and locked. **ON A/C ALL (17) If the specified dimension between the uplock pin (2) and the uplock latch (7) is correct, do the steps that follow: (a) If it was removed, safety the nut (5) on the uplock pin (2) with the cotter pin (4). NOTE: Make sure that the uplock pin (2) can rotate easily and that there is a maximum sideplay of 0.020 inch (0.05 cm) between the washer (6) and the uplock pin bracket (3). (b) Go to the Close−Out section of this procedure. (18) If you did not get the dimension specified in the step above, do the steps that follow to adjust the uplock pin bracket (3): (a) If it was not removed in an earlier step, remove the cotter pin (4) from the uplock pin (2). (b) Remove the nut (5) and the washer (6) from the uplock pin (2). (c) Remove the uplock pin (2) from the uplock pin bracket (3). (d) Remove the lockwire that secures the bolts (8) to the uplock pin bracket (3). (e) Loosen the bolts (8) (with the washers (9)) a sufficient amount so that the uplock pin bracket (3) can be moved vertically on the serrated uplock plate (10). (f) Move the uplock pin bracket (3) up or down on the serrated uplock plate (10) as necessary to get the required dimension between the uplock pin (2) and the root of the uplock latch (7) when the NLG is retracted and locked. NOTE: The movement of one serration up of the uplock pin bracket (3) on the serrated uplock plate (10) is equal to a increase of 0.080 inch (0.20 cm) in the required dimension between the uplock pin (2) and the root of the uplock latch (7). (g) Temporarily tighten the bolts (8) to secure the uplock pin bracket (3) and the serrated uplock plate (10) to the NLG. (h) Temporarily install the uplock pin (2) in the uplock pin bracket (3), the washer (6), and the nut (5). (i) Temporarily tighten the nut (5). Make sure that the uplock pin (2) can rotate freely in the uplock pin bracket (3). (19) If you did not get the clearance between the NLG uplock assembly (1) and both sides of the uplock pin bracket (3), do the steps that follow to adjust the uplock pin bracket (3): (a) If it was not removed in an earlier step, remove the cotter pin (4) from the uplock pin (2). (b) Remove the nut (5) and the washer (6) from the uplock pin (2). (c) Remove the uplock pin (2) from the uplock pin bracket (3). Master EFFECTIVITY: See Pageblock 32−33−05 page 501 32−33−05 Page 517 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL (d) Remove the lockwire that secures the bolts (8) to the uplock pin bracket (3). (e) Loosen the bolts (8) (with the washers (9)) a sufficient amount so that the uplock pin bracket (3) can be moved horizontally but not vertically on the serrated uplock plate (10). (f) Adjust the uplock pin bracket (3) to get a minimum clearance of 0.150 inch (0.381 cm) between the NLG uplock assembly (1) and both sides of the uplock pin bracket (3). (g) Temporarily tighten the bolts (8) to secure the uplock pin bracket (3) and the serrated uplock plate (10) to the NLG. (h) Temporarily install the uplock pin (2) in the uplock pin bracket (3), the washer (6), and the nut (5). (i) Temporarily tighten the nut (5). Make sure that the uplock pin (2) can rotate freely in the uplock pin bracket (3). Subtask 32−33−05−820−009 B. If the specified gap (step A−13 or step A−14) was not obtained, apply more plasticine to the root of the uplock latch assembly. Retract the NLG and repeat steps A−13 and subsequent until you get the specified dimension between the uplock pin (2) and the uplock latch (7). Subtask 32−33−05−430−003 C. If the specified dimension between the uplock pin (2) and the uplock latch (7) is now correct, do the steps that follow: (1) To get access to the two bolts (8), remove the nut (5), the washer (6), and the uplock pin (2) from the uplock pin bracket (3). (2) Torque the two bolts (8) from 50 to 60 pound−inches (5.7 to 6.8 N·m). (3) Safety the two bolts (8) together with 05−004 lockwire. (4) Safety the two bolts (8) to the uplock pin bracket (3) with 05−004 lockwire. (5) Install the uplock pin (2) in the uplock pin bracket (3). (6) Install the washer (6), and the nut (5) on the uplock pin (2). (7) Safety the nut (5) on the uplock pin (2) with the cotter pin (4). NOTE: Make sure that the uplock pin (2) can rotate easily and that there is a maximum sideplay of 0.020 inch (0.05 cm) between the washer (6) and the uplock pin bracket (3). Subtask 32−33−05−140−002 D. Remove any 05−015 plasticine (or equivalent) that remains on the uplock pin (2) and on the uplock latch (7). Master EFFECTIVITY: See Pageblock 32−33−05 page 501 518 32−33−05 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 4. Close Out Subtask 32−33−05−582−004 A. Lower the aircraft at the nose jacking point at FS278.00 and remove the jack (Ref. TASK 07−11−01−582−802). Subtask 32−33−05−840−004 B. At the external services panel, put the NOSE DOOR maintenance switch to the FLT/NORM position. Subtask 32−33−05−410−003 C. Close the access panel that follows: ACCESS 122CR DESIGNATION Door, external service panel Master EFFECTIVITY: See Pageblock 32−33−05 page 501 32−33−05 Page 519 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL 1 0.150 in. (0.381 cm) MINIMUM 0.150 in. (0.381 cm) MINIMUM A 5 2 6 3 0.020 in. (0.050 cm) MAXIMUM AND FREE TO ROTATE LEGEND 1. NLG uplock assembly. 2. Uplock pin. 3. Uplock pin bracket. 4. Cotter pin. 5. Nut. 6. Washer. 7. Uplock latch. 8. Bolt. 9. Washer. 10. Serrated uplock plate. 1 0.110 − 0.190 in. (0.279 − 0.483 cm) 7 2 4 5 6 3 2 9 8 ram3233055_002.dg, gv/rm, 03/02/03 10 NLG Uplock Assembly Clearances − Adjustment/Test Figure 506 Master EFFECTIVITY: See Pageblock 32−33−05 page 501 32−33−05 Page 520 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL 1 0.150 in. (0.381 cm) MINIMUM 0.150 in. (0.381 cm) MINIMUM 5 A 2 6 3 0.020 in. (0.050 cm) MAXIMUM AND FREE TO ROTATE LEGEND 1. NLG uplock assembly. 2. Uplock pin. 3. Uplock pin bracket. 4. Cotter pin. 5. Nut. 6. Washer. 7. Uplock latch. 8. Bolt. 9. Washer. 10. Serrated uplock plate. 1 0.110 − 0.190 in. (0.279 − 0.483 cm) 7 2 4 5 6 3 2 9 8 ram3233055_004.dg, gv/lr, 23/11/04 10 NLG Uplock Assembly Clearances − Adjustment/Test Figure 507 Master EFFECTIVITY: See Pageblock 32−33−05 page 501 32−33−05 Page 521 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL 1 0.150 in. (0.381 cm) MINIMUM 0.150 in. (0.381 cm) MINIMUM 5 A 2 6 3 0.020 in. (0.050 cm) MAXIMUM AND FREE TO ROTATE LEGEND 1. NLG uplock assembly. 2. Uplock pin. 3. Uplock pin bracket. 4. Cotter pin. 5. Nut. 6. Washer. 7. Uplock latch. 8. Bolt. 9. Washer. 10. Serrated uplock plate. 1 0.125 − 0.205 in. (0.318 − 0.520 cm) 7 2 4 5 6 3 2 9 8 ram3233055_003.dg, gv/rm, 03/02/03 10 NLG Uplock Assembly Clearances − Adjustment/Test Figure 508 Master EFFECTIVITY: See Pageblock 32−33−05 page 501 32−33−05 Page 522 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL 1 0.150 in. (0.381 cm) MINIMUM 0.150 in. (0.381 cm) MINIMUM 5 A 2 6 3 0.020 in. (0.050 cm) MAXIMUM AND FREE TO ROTATE LEGEND 1. NLG uplock assembly. 2. Uplock pin. 3. Uplock pin bracket. 4. Cotter pin. 5. Nut. 6. Washer. 7. Uplock latch. 8. Bolt. 9. Washer. 10. Serrated uplock plate. 1 0.125 − 0.205 in. (0.318 − 0.520 cm) 7 2 4 5 6 3 2 9 8 ram3233055_005.dg, gv/lr, 24/11/04 10 NLG Uplock Assembly Clearances − Adjustment/Test Figure 509 Master EFFECTIVITY: See Pageblock 32−33−05 page 501 32−33−05 Page 523 Mar 15/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL VALVE, NOSE LANDING GEAR SELECTOR − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the nose landing gear (NLG) selector valve. The NLG selector valve is installed in the nose hydraulics compartment, on the forward pressure−bulkhead at approximately FS200 and LBL22. Access is through panel 121AL. TASK 32−33−10−000−801 Removal of the Nose Landing Gear Selector Valve 1. Job Set−Up Information Subtask 32−33−10−943−001 A. Tools and Equipment REFERENCE None specified DESIGNATION Cloths, absorbent Subtask 32−33−10−946−001 B. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 29−00−00−910−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions 2. Job Set−Up Subtask 32−33−10−490−005 WARNING: A. MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Subtask 32−33−10−863−001 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all the hydraulic safety precautions (Ref. TASK 29−00−00−910−801). WARNING: B. Master EFFECTIVITY: See Pageblock 32−33−10 page 401 32−33−10 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL C. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−33−10−865−001 D. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CB NO. A2 F6 G11 A2 G15 P2 NAME HYD PUMP 3B PROX SENS LGC/D1 HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A PROX SENS LGC/D1 ZONE 221 221 221 222 222 222 Subtask 32−33−10−010−001 E. Open the access panel that follows: ACCESS 121AL DESIGNATION Access panel, nose hydraulics compartment **ON A/C 7003−7020, 7022−7039, 7041−7067, 7069−7147, 7149−7204, 7206−7479, 7481−7604, 7606−7990 Pre SB601R−32−048 Subtask 32−33−10−030−005 Refer to Figure 401. F. Prepare the NLG selector valve (1) for removal as follows: NOTE: Use absorbent cloths to collect hydraulic fluid leakage when you disconnect the hydraulic lines. (1) Disconnect the electrical connector from the NLG selector valve (1). (2) Install protective caps on the electrical connector and on the receptacle of the NLG selector valve (1). (3) Disconnect the hydraulic lines from the NLG selector valve (1). NOTE: When you remove the NLG−down hydraulic line, make sure that you hold the check valve (14). Do not let the check valve (14) turn while you loosen the hydraulic line. **ON A/C 7021, 7040, 7148, 7205, 7480, 7605 and ON A/C 7003−7020, 7022−7039, 7041−7067, 7069−7147, 7149−7204, 7206−7479, 7481−7604, 7606−7990 Post SB601R−32−048 Subtask 32−33−10−030−006 Refer to Figure 402. G. Prepare the NLG selector valve (1) for removal as follows: NOTE: Use absorbent cloths to collect hydraulic fluid leakage when you disconnect the hydraulic lines. Master EFFECTIVITY: See Pageblock 32−33−10 page 401 402 32−33−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (1) Disconnect the electrical connector from the NLG selector valve (1). (2) Install protective caps on the electrical connector and on the receptacle of the NLG selector valve (1). (3) Disconnect the hydraulic lines from the NLG selector valve (1). NOTE: When you remove the NLG−down hydraulic line, make sure that you hold the check valve (14). Do not let the check valve (14) turn while you loosen the hydraulic line. **ON A/C 7003−7020, 7022−7039, 7041−7067, 7069−7147, 7149−7204, 7206−7479, 7481−7604, 7606−7990 Pre SB601R−32−048 3. Procedure Refer to Figure 401. Subtask 32−33−10−020−001 A. B. Remove the NLG selector valve (1) and the attached support plate from the support structure as follows: (1) Remove the nuts (2), the washers (3), and the screws (4) that attach the NLG selector valve/support plate assembly to the mounting bracket. (2) Remove the nuts (5), the washers (6), and the screws (7) that attach the support plate (8) to the mounting bracket. (3) Remove the NLG selector valve (1) with the support plate (8). (4) Install protective caps and plugs on the open hydraulic lines and ports. If a different NLG selector valve (1) will be installed, remove the nuts (9), the washers (10), and the countersunk screws (11) that attach the support plate (8) to the NLG selector valve (1). Subtask 32−33−10−030−003 C. If it is necessary to install the hydraulic fittings on a new NLG selector valve (1), remove them as follows: (1) Loosen the nut (12) and remove the tee−fitting (13) and the check valve (14) together. Discard the retainer (15) and the preformed packing (16). NOTE: Unless necessary, do not remove the check valve (14) from the tee−fitting (13). (2) Remove the restrictor (17), the check valve (18), and the union (19) with the related preformed packings (16). Discard the preformed packings (16). **ON A/C 7021, 7040, 7148, 7205, 7480, 7605 and ON A/C 7003−7020, 7022−7039, 7041−7067, 7069−7147, 7149−7204, 7206−7479, 7481−7604, 7606−7990 Post SB601R−32−048 4. Procedure Refer to Figure 402. Master EFFECTIVITY: See Pageblock 32−33−10 page 401 403 32−33−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−33−10−020−003 A. B. C. Remove the four screws (2) and the four washers (3) that attach the NLG selector valve/support plate assembly to the mounting bracket. Remove the NLG selector valve (1) and the attached support plate (4). Install protective caps and plugs on the open hydraulic lines and ports. If a different NLG selector valve (1) will be installed, remove the four nuts (5), the four washers (6), and the four countersunk screws (7) that attach the support plate (4) to the NLG selector valve (1). Subtask 32−33−10−030−004 D. If it is necessary to install the hydraulic fittings on to a new NLG selector valve (1), remove them as follows: (1) Loosen the nut (8) and remove the tee−fitting (9) and the check valve (10) together. Discard the retainer (11) and the preformed packing (12). NOTE: Unless necessary, do not remove the check valve (10) from the tee−fitting (9). (2) Remove the restrictor (13), the check valve (14), and the union (15) with the related preformed packings (12). Discard the preformed packings (12). Master EFFECTIVITY: See Pageblock 32−33−10 page 401 32−33−10 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND A HYRAULIC LINE (NLG DOWN) 14 13 HYDRAULIC LINE (STRG PRESS) 12 15 16 HYDRAULIC LINE (NLG UP) 7 1. Selector valve. 2. Nut. 3. Washer. 4. Screw. 5. Nut. 6. Washer. 7. Screw. 8. Support plate. 9. Nut. 10. Washer. 11. Screw. 12. Nut. 13. Tee fitting. 14. Check valve. 15. Retainer. 16. Preformed packing. 17. Restrictor. 18. Check valve. 19. Union. 8 5 6 11 17 16 4 C2 C1 MOUNTING BRACKET 1 10 2 STRUCTURE (REF) 3 16 16 19 18 HYDRAULIC LINE (RTN #3) HYDRAULIC LINE (PRESS #3) ELECTRICAL CONNECTOR A ram3233104_001.dg, rt/lr, 14/09/05 9 Nose Landing Gear Selector Valve − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−33−10 page 401 405 32−33−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL LEGEND A HYRAULIC LINE (NLG DOWN) 10 9 HYDRAULIC LINE (STRG PRESS) 1. Selector valve. 2. Screw. 3. Washer. 4. Support plate. 5. Nut. 6. Washer. 7. Countersink screw. 8. Nut. 9. Tee fitting. 10. Check valve. 11. Retainer. 12. Preformed packing. 13. Restrictor. 14. Check valve. 15. Union. 8 11 12 3 HYDRAULIC LINE (NLG UP) 4 2 13 MOUNTING BRACKET 12 C2 C1 1 6 7 STRUCTURE (REF) 12 12 15 14 HYDRAULIC LINE (PRESS #3) HYDRAULIC LINE (RTN #3) ELECTRICAL CONNECTOR A ram3233104_002.dg, rt/rm, 20/04/00 5 Nose Landing Gear Selector Valve − Removal/Installation Figure 402 Master EFFECTIVITY: See Pageblock 32−33−10 page 401 32−33−10 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL TASK 32−33−10−400−801 Installation of the Nose Landing Gear Selector Valve 1. Job Set−Up Information Subtask 32−33−10−944−001 A. Consumable Materials REFERENCE 02−001 None specified DESIGNATION Hydraulic fluid, phosphate ester base Cloths, absorbent **ON A/C 7003−7020, 7022−7039, 7041−7067, 7069−7147, 7149−7204, 7206−7479, 7481−7604, 7606−7990 Pre SB601R−32−048 Subtask 32−33−10−945−001 B. Parts REF 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 NAME OF PART Nut Washer Screw Nut Washer Screw Support plate Nut Washer Screw, countersunk Nut Tee−fitting Check valve Retainer Preformed packing Restrictor Check valve Union Master EFFECTIVITY: See Pageblock 32−33−10 page 401 QTY 2 2 2 2 2 2 1 2 2 2 1 1 1 1 4 1 1 1 IPC SEQUENCE NO. IPC 32−33−10−01−020 IPC 32−33−10−01−022 IPC 32−33−10−01−015 IPC 32−33−10−01−035 IPC 32−33−10−01−032 IPC 32−33−10−01−030 IPC 32−33−10−01−025 IPC 32−33−10−01−020 IPC 32−33−10−01−022 IPC 32−33−10−01−010 IPC 32−33−00−01−195 IPC 32−33−00−01−200 IPC 32−33−00−01−210 IPC 32−33−00−01−190 IPC 32−33−00−01−205 IPC 32−33−00−01−215 IPC 32−33−00−01−220 IPC 32−33−00−01−225 407 32−33−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7021, 7040, 7148, 7205, 7480, 7605 and ON A/C 7003−7020, 7022−7039, 7041−7067, 7069−7147, 7149−7204, 7206−7479, 7481−7604, 7606−7990 Post SB601R−32−048 Subtask 32−33−10−945−003 C. Parts REF 2 3 4 5 6 7 8 9 10 11 12 13 14 15 NAME OF PART Screw Washer Support plate Nut Washer Screw, countersunk Nut Tee−fitting Check valve Retainer Preformed packing Restrictor Check valve Union QTY 2 2 1 2 2 2 1 1 1 1 4 1 1 1 IPC SEQUENCE NO. IPC 32−33−10−01−060 IPC 32−33−10−01−062 IPC 32−33−10−01−045 IPC 32−33−10−01−055 IPC 32−33−10−01−062 IPC 32−33−10−01−050 IPC 32−33−00−01−195 IPC 32−33−00−01−200 IPC 32−33−00−01−210 IPC 32−33−00−01−190 IPC 32−33−00−01−205 IPC 32−33−00−01−215 IPC 32−33−00−01−220 IPC 32−33−00−01−225 **ON A/C ALL Subtask 32−33−10−946−002 D. Reference Information REFERENCE TASK 29−10−00−870−803 TASK 32−30−00−720−801 DESIGNATION Bleed Hydraulic System No. 3 Functional Test of the Landing Gear Extension/Retraction System 2. Job Set−Up Subtask 32−33−10−869−005 A. Make sure that the aircraft is in the same configuration as in the removal task. **ON A/C 7003−7020, 7022−7039, 7041−7067, 7069−7147, 7149−7204, 7206−7479, 7481−7604, 7606−7990 Pre SB601R−32−048 3. Procedure Refer to Figure 401. Master EFFECTIVITY: See Pageblock 32−33−10 page 401 408 32−33−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−33−10−430−001 A. If required, install the hydraulic fittings on the new selector valve (1) as follows: (1) Lightly lubricate the preformed packings (16) with clean 02−001 hydraulic fluid. (2) Install a preformed packing (16) on the union (19), the check valve (18), and the restrictor (17). NOTE: Make sure that you install the preformed packings (16) on the fitting−end that goes in to the NLG selector valve (1). (3) Install the union (19), with the preformed packing (16), in the selector valve port identified as P (pressure port). (4) Install the check valve (18), with the preformed packing (16), in the selector valve port identified as R (return port). NOTE: Make sure that the flow indication arrow on the check valve (18) points away from the NLG selector valve (1) when installed. (5) Install the restrictor (17), with the preformed packing (16), in the selector valve port identified as C2. NOTE: Make sure that the flow indication arrow on the restrictor (17) points away from the NLG selector valve (1) when installed. (6) Install the nut (12) on the tee−fitting (13) until the nut is on the set of threads nearest the body of the tee−fitting (13). NOTE: Make sure that the recessed−face of the nut (12) will be adjacent to the retainer (15) when the retainer (15) is installed. (7) Install the retainer (15) and the preformed packing (16) in the space between the two sets of threads on the tee−fitting (13). (8) Install the tee−fitting (13) in the selector valve port identified as C1 as follows: (a) Turn the tee−fitting (13) until the preformed packing (16) and the retainer (15) touch the body of the NLG selector valve (1) and friction is felt. (b) Turn the tee−fitting (13) to a position such that it will be aligned with the STRG PRESS hydraulic−line when the NLG selector valve (1) is installed. (c) Tighten the nut (12) against the body of the NLG selector valve (1). NOTE: If the check valve (14) was removed from the tee−fitting (13) during the removal procedure, discard its preformed packing (16) and install a new one. The check valve (14) has a flow indication arrow. Make sure that the arrow points toward the NLG selector valve (1) when the tee−fitting/check valve assembly is installed. Subtask 32−33−10−420−001 B. Install the NLG selector valve (1) in the aircraft as follows: (1) If the support plate (8) was removed in the removal procedure, attach the support plate (8) to the NLG selector valve (1) with the screws (11), the washers (10), and the nuts (9). (2) Put the NLG selector valve/support plate assembly in position with the C1 and C2 ports at the top. Master EFFECTIVITY: See Pageblock 32−33−10 page 401 32−33−10 Page 409 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (3) Attach the NLG selector valve/support plate assembly to the mounting structure with the screws (7), the washers (6), and the nuts (5). (4) Attach the selector valve/support plate assembly to the mounting bracket with the screws (4), the washers (3), and the nuts (2). (5) Remove the protective caps and plugs from the hydraulic lines and ports. (6) Connect the hydraulic lines to the NLG selector valve (1) as follows: (a) Connect the STRG PRESS hydraulic−line to the tee−fitting (13). (b) Connect the NLG DOWN hydraulic−line to the check valve (14) (the port identified as C1 on the NLG selector valve (1)). (c) Connect the NLG UP hydraulic−line to the restrictor (17) (the port identified as C2 on the NLG selector valve (1)). (d) Connect the RTN #3 hydraulic−line to the check valve (18) (the port identified as R on the NLG selector valve (1)). (e) Connect the PRESS #3 hydraulic−line to the union (19) (the port identified as P on the NLG selector valve (1)). (7) Remove the protective caps from the electrical connector and from the solenoid of the NLG selector valve (1). (8) Connect the electrical connector to the NLG selector valve (1). **ON A/C 7021, 7040, 7148, 7205, 7480, 7605 and ON A/C 7003−7020, 7022−7039, 7041−7067, 7069−7147, 7149−7204, 7206−7479, 7481−7604, 7606−7990 Post SB601R−32−048 4. Procedure Refer to Figure 402. Subtask 32−33−10−430−003 A. If required, install the hydraulic fittings on the new selector valve (1) as follows: (1) Lightly lubricate the preformed packings (12) with clean 02−001 hydraulic fluid. (2) Install a preformed packing (12) on the union (15), the check valve (14), and the restrictor (13). NOTE: Make sure that you install the preformed packings (12) on the fitting−end that goes in to the NLG selector valve (1). (3) Install the union (15), with the preformed packing (12), in the selector valve port identified as P (pressure port). (4) Install the check valve (14), with the preformed packing (12), in the selector valve port identified as R (return port). NOTE: Make sure that the flow indication arrow on the check valve (14) points away from the NLG selector valve (1) when installed. (5) Install the restrictor (13), with the preformed packing (12), in the selector valve port identified as C2. NOTE: Make sure that the flow indication arrow on the restrictor (13) points away from the NLG selector valve (1) when installed. (6) Install the nut (8) on the tee−fitting (9) until the nut is on the set of threads nearest Master EFFECTIVITY: See Pageblock 32−33−10 page 401 410 32−33−10 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL the body of the tee−fitting (9). NOTE: Make sure that the recessed−face of the nut (8) will be adjacent to the retainer (11) when the retainer (11) is installed. (7) Install the retainer (11) and the preformed packing (12) in the space between the two sets of threads on the tee−fitting (9). (8) Install the tee−fitting (9) in the selector valve port identified as C1 as follows: (a) Turn the tee−fitting (9) until the preformed packing (12) and the retainer (11) touch the body of the NLG selector valve (1) and friction is felt. (b) Turn the tee−fitting (9) to a position such that it will be aligned with the STRG PRESS hydraulic−line when the NLG selector valve (1) is installed. (c) Tighten the nut (8) against the body of the NLG selector valve (1). NOTE: If the check valve (10) was removed from the tee−fitting (9) during the removal procedure, discard its preformed packing (12) and install a new one. The check valve (10) has a flow indication arrow. Make sure that the arrow points toward the NLG selector valve (1) when the tee−fitting/check valve assembly is installed. Subtask 32−33−10−420−003 B. Install the NLG selector valve (1) in the aircraft as follows: (1) If the support plate (4) was removed in the removal procedure, attach the support plate (4) to the NLG selector valve (1) with the four countersunk screws (7), the four washers (6), and the four nuts (8). (2) Put the NLG selector valve/support plate assembly in position with the C1 and C2 ports at the top. (3) Attach the NLG selector valve/support plate assembly to the mounting structure with the four screws (2), the four washers (3), and the four nuts (5). (4) Remove the protective caps and plugs from the hydraulic lines and ports. (5) Connect the hydraulic lines to the NLG selector valve (1) as follows: (a) Connect the STRG PRESS hydraulic−line to the tee−fitting (9). (b) Connect the NLG DOWN hydraulic−line to the check valve (10) (the port identified as C1 on the NLG selector valve (1)). (c) Connect the NLG UP hydraulic−line to the restrictor (13) (the port identified as C2 on the NLG selector valve (1)). (d) Connect the RTN #3 hydraulic−line to the check valve (14) (the port identified as R on the NLG selector valve (1)). (e) Connect the PRESS #3 hydraulic−line to the union (15) (the port identified as P on the NLG selector valve (1)). (6) Remove the protective caps from the electrical connector and from the solenoid of the NLG selector valve (1). (7) Connect the electrical connector to the NLG selector valve (1). Master EFFECTIVITY: See Pageblock 32−33−10 page 401 32−33−10 Page 411 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL 5. Close Out Subtask 32−33−10−140−005 A. Clean all signs of hydraulic fluid from the work area. Subtask 32−33−10−865−002 B. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CB NO. A2 F6 G11 A2 G15 P2 NAME HYD PUMP 3B PROX SENS LGC/D1 HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A PROX SENS LGC/D1 ZONE 221 221 221 222 222 222 Subtask 32−33−10−870−001 C. Bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−33−10−941−005 D. Remove all tools, equipment and unwanted materials from the work area. Subtask 32−33−10−720−001 E. Do a functional test of the extension and retraction system (Ref. TASK 32−30−00−720−801). Subtask 32−33−10−790−005 F. Examine the work area for leaks. Subtask 32−33−10−410−001 G. Close the access panel that follows: ACCESS 121AL DESIGNATION Access panel, nose hydraulics compartment Master EFFECTIVITY: See Pageblock 32−33−10 page 401 32−33−10 Page 412 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL VALVE, PRIORITY − REMOVAL/INSTALLATION 1. General A. The maintenance procedures that follow are for the removal and installation of the nose−landing−gear (NLG) priority valve. The priority valve is installed at approximately FS194 on the outboard−side of the nose hydraulics compartment, aft of access panel 121AL. TASK 32−33−15−000−801 Removal of the NLG Priority Valve 1. Job Set−Up Information Subtask 32−33−15−946−001 A. Reference Information REFERENCE TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 29−00−00−910−801 DESIGNATION Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − System No. 3 Hydraulic Safety Precautions 2. Job Set−Up Subtask 32−33−15−490−001 MAKE SURE THAT THE SAFETY LOCKPINS ARE INSTALLED ON THE NOSE AND MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). WARNING: A. Subtask 32−33−15−863−001 OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT. Obey all hydraulic safety precautions (Ref. TASK 29−00−00−910−801). Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). WARNING: B. C. Master EFFECTIVITY: See Pageblock 32−33−15 page 401 32−33−15 Page 401 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−33−15−865−001 D. Open, safety, and tag the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−33−15−010−001 E. Remove the access panel that follows: ACCESS 121AL DESIGNATION Access panel, nose hydraulics compartment 3. Procedure Subtask 32−33−15−020−001 Refer to Figure 401. A. Remove the priority valve (1) as follows: (1) Disconnect the hydraulic lines from the swivel valve (1). (2) Remove the screw (2) and the washer (3). (3) Remove the priority valve (1) with the clamp (4). (4) Install protective caps on all open hydraulic lines and ports. (5) Remove the clamp (4). B. If it is necessary to install the unions (6) on a new priority valve (1), remove the unions and the preformed packings (5) from the unserviceable priority valve. C. Discard the preformed packings (5). Master EFFECTIVITY: See Pageblock 32−33−15 page 401 32−33−15 Page 402 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL LEGEND 1. Swivel valve. 2. Screw. 3. Washer. 4. Clamp. 5. Preformed packing. 6. Union. HYDRAULIC LINE (REF) 6 5 4 1 S. ES PR 5 6 . ST SY 2 HYDRAULIC LINE (REF) BRACKET (REF) ram3233154_001(2).dc, gg/pt, 31/10/00 3 Priority Valve − Removal/Installation Figure 401 Master EFFECTIVITY: See Pageblock 32−33−15 page 401 32−33−15 Page 403 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−33−15−400−801 Installation of the NLG Priority Valve 1. Job Set−Up Information Subtask 32−33−15−944−001 A. Consumable Materials REFERENCE 02−001 DESIGNATION Hydraulic fluid, phosphate ester base Subtask 32−33−15−945−001 B. Parts REF 1 2 3 4 5 6 NAME OF PART Priority valve Screw Washer Clamp Preformed packing Union QTY 1 1 1 1 2 2 IPC SEQUENCE NO. IPC 32−33−15−01−005 IPC 32−33−15−01−020 IPC 32−33−15−01−025 IPC 32−33−15−01−015 IPC 32−33−00−01−270 IPC 32−33−00−01−265 Subtask 32−33−15−946−002 C. Reference Information REFERENCE TASK 29−10−00−870−803 TASK 32−00−00−790−801 TASK 32−30−00−730−801 DESIGNATION Bleed Hydraulic System No. 3 External Leak Check of the Landing Gear System Test of the Landing Gear Priority Valves 2. Job Set−Up Subtask 32−33−15−869−001 A. Make sure that the aircraft is in the same configuration as in the removal task. 3. Procedure Subtask 32−33−15−430−001 Refer to Figure 401. A. Install the unions (6) on the priority valve (1) as follows: (1) Lightly lubricate the preformed packings (5) with clean 02−001 hydraulic fluid. (2) On each union (6), install a preformed packing (5) on the end of the union that goes into the priority valve (1). Master EFFECTIVITY: See Pageblock 32−33−15 page 401 32−33−15 Page 404 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL (3) Install the unions (6) in the PRESS and SYST ports of the priority valve (1). (4) Install the clamp (4) on the priority valve (1). Subtask 32−33−15−420−001 B. Install the priority valve (1) as follows: (1) Remove the protective caps and plugs from the hydraulic lines and ports. (2) Put the priority valve (1) in position with the PRESS port at the top. (3) Attach the priority valve (1) to the mounting bracket with the clamp (4), the washer (3), and the screw (2). (4) Connect the hydraulic lines to the priority valve (1). 4. Close Out Subtask 32−33−15−140−001 A. Clean all signs of hydraulic fluid from the work area. Subtask 32−33−15−865−002 B. Remove the tags and close the circuit breakers that follow: CB PANEL CBP−1 CBP−1 CBP−2 CBP−2 CB NO. A2 G11 A2 G15 NAME HYD PUMP 3B HYD SYST AC PUMP CONT 3B HYD PUMP 3A HYD SYST AC PUMP CONT 3A ZONE 221 221 222 222 Subtask 32−33−15−870−001 C. Bleed hydraulic system No. 3 (Ref. TASK 29−10−00−870−803). Subtask 32−33−15−720−001 D. Do a functional test of the NLG priority valve (Ref. TASK 32−30−00−730−801). Subtask 32−33−15−210−001 E. Examine the fittings on the priority valve (1) for leaks (Ref. TASK 32−00−00−790−801). Subtask 32−33−15−941−002 F. Remove all tools. equipment, and unwanted materials from the work area. Subtask 32−33−15−410−001 G. Install the access panel that follows: Master EFFECTIVITY: See Pageblock 32−33−15 page 401 32−33−15 Page 405 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL ACCESS 121AL DESIGNATION Nose hydraulics compartment access panel Master EFFECTIVITY: See Pageblock 32−33−15 page 401 32−33−15 Page 406 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL MANUAL RELEASE SYSTEM, LANDING GEAR − DESCRIPTION AND OPERATION 1. 2. General A. If an electrical or mechanical malfunction occurs in the landing gear extension−system, the aircraft is equipped with a manual release system. The manual release system includes the components that follow: ± Manual release handle ± Downlock assist actuator ± Operating lever ± Nose landing gear (NLG) release mechanism ± Main landing gear (MLG) release mechanism ± Downlock assist valve ± NLG runaround and bypass valve ± NLG bypass valve ± NLG door bypass valve ± Cables. Component Details Refer to Figure 1, Figure 2, and Figure 3. A. Manual Release Handle (1) The manual release handle is a conventional T−shaped handle which is used to control the release of the landing gear during an electrical or hydraulic failure. It is located on the center pedestal, to the right of the aircraft parking brake handle. It is connected at its lower end to a cable which extends below the aircraft floor to the operating lever. (2) An anti return mechanism keeps the manual release handle in the operated position. To release the handle, the operator must push the release button installed on the top of the handle. This will release the anti return mechanism and permit the handle to move to the stowed position. B. Downlock Assist Actuator (1) The actuator is a single−action unit which includes a piston, a sealing system, and two bearings which are contained in a cylinder. The downlock assist actuator is used to help extend the MLG to the down and locked position during an electrical or hydraulic failure. The actuator is attached at one end to the bulkhead in the MLG wheel well and at the other end to the top of the main beam assembly. (2) During normal operation, the cylinder is not pressurized. The actuator moves freely when the landing gear extends and retracts. During emergency conditions, the downlock assist valve opens and permits pressurized fluid to flow to the cylinder and extend the actuator. (3) An excluder assembly installed at the bottom of the cylinder prevents the ingress of unwanted objects on the piston rod. Master EFFECTIVITY: See Pageblock 32−34−00 page 1 Page 1 32−34−00 Dec 15/2004 C AIRCRAFT MAINTENANCE MANUAL C. D. E. F. G. H. Operating Lever (1) The operating lever is used to transmit the movements of the manual release handle to the NLG lever assembly and to the runaround and bypass lever. The lever is installed in a bracket which is attached to the aft bulkhead of the nose gear well. (2) Two triangular−shaped plates are installed on the upper part of the lever, one on each side of the lever. The two plates contain a pulley which is used to transmit the movements of the release cable to the NLG lever assembly. Two tension springs are installed on the plates to keep the cable circuit tight. NLG Release Mechanism (1) The NLG release mechanism is used to transmit the movement of the manual release handle to open the NLG doors and extend the NLG. Various linkages and cable from the mechanism operate the NLG and NLG doors uplocks, the NLG bypass valve, and the NLG door bypass−valve. A mechanical stop on the bypass valve cross−shaft prevents an overtravel condition on the release mechanism. The NLG release mechanism is installed on the top bulkhead of the nose gear well, near the NLG uplock. MLG Release Mechanism (1) The release mechanism is used to transmit the movement of the manual release handle to extend the MLG. The release mechanism includes the runaround/bypass valve, the runaround/bypass valve lever, and the related linkage. The MLG release mechanism is installed on the aircraft center line in the MLG wheel well. (2) The manual release cable from the flight compartment extends along the fuselage to the MLG wheel well, where it attaches to the runaround/bypass valve lever. The lever has two outputs cables and one output control rod. The cables attach to each of the main gear uplocks while the control rod attaches to the selector valve for the MLG assist actuators. Downlock Assist Valve (1) The downlock assist valve is used to apply hydraulic pressure from system No. 2 to the downlock assist actuators during emergency extension of the landing gear. The downlock assist valve is installed on the top bulkhead of the MLG wheel well. (2) The valve has three hydraulic ports, a pressure inlet port, a return port, and a cylinder port. Also installed on the valve is a release lever which connects to the mechanical linkage for the runaround and bypass valve. NLG Runaround and Bypass Valve (1) The MLG runaround and bypass−valve is used to release hydraulic pressure from the side stay actuator and uplock hydraulic lines during emergency extension of the MLG. The runaround and bypass−valve is installed on the top bulkhead of the MLG wheel well. The runaround feature increases the speed of extension of the NLG by returning hydraulic fluid from the up side of the side stay actuator directly to the down side, during an extension. NLG Bypass Valve (1) The NLG bypass valve is a mechanically−operated valve, used to release hydraulic pressure from the NLG and permit its free fall during alternate extension. The NLG bypass valve is installed on the top bulkhead of the NLG wheel well. Master EFFECTIVITY: See Pageblock 32−34−00 page 1 Page 2 32−34−00 Dec 15/2004 C AIRCRAFT MAINTENANCE MANUAL I. 3. 4. NLG Door Bypass−Valve (1) The NLG door bypass−valve is a mechanically−operated valve used to release hydraulic pressure from the NLG doors and permit their free fall during emergency extension. The NLG bypass valve is installed on the top bulkhead of the NLG wheel well. Operation A. The alternate extension system is controlled by the vertical movement of the manual release handle. The movement of the handle is transmitted by the attached cable to the operating lever. B. The displacement of the operating lever is transmitted by a cable to the NLG uplock release−mechanism and to the MLG runaround and bypass valve lever. C. The movement of the runaround and bypass valve lever is transmitted by two cables to the left and right uplock release levers. The runaround and bypass valve releases the hydraulic pressure from the hydraulic lines of the MLG side stay and uplock actuators. The uplock release levers release the MLG uplocks and permit the gear to extend by gravity. D. At the same time, the movement of the runaround and bypass valve lever is transmitted by a control rod to operate the downlock assist valve. This sends hydraulic fluid from system No. 2 to extend the downlock assist actuators. E. Cable movement also moves the lever assembly on the NLG release mechanism. The movement of this lever releases the NLG forward doors, the NLG uplock, the NLG bypass valve, and the NLG door bypass−valve. The NLG and NLG doors are extended to the down and locked position by assist spring pressure and aerodynamic flow. Component Location Index Refer to Figure 1, Figure 2, and Figure 3. COMPONENT NAME Manual release handle Downlock assist actuator Nose landing gear release mechanism Main landing gear release mechanism Downlock assist valve Runaround and bypass valve Nose landing gear bypass valve Nose landing gear door bypass valve QTY 1 2 1 1 1 1 1 1 Master EFFECTIVITY: See Pageblock 32−34−00 page 1 ACCESS/ZONE REFERENCE Flight compartment 32−34−01 Main landing gear wheel well 32−34−05 Nose landing gear wheel well 32−34−15 Main landing gear wheel well 32−34−20 Main landing gear wheel well 32−34−25 Main landing gear wheel well 32−34−30 Nose landing gear wheel well 32−34−35 Nose landing gear wheel well 32−34−40 Page 3 32−34−00 Dec 15/2004 C AIRCRAFT MAINTENANCE MANUAL A DOWN LOCK ASSIST ACTUATOR ram3234000_001.dg, as, 04/10/01 MLG SIDE STAY ACTUATOR (REF) A Alternate Extension/Downlock Assist Actuator − Component Location Figure 1 Master EFFECTIVITY: See Pageblock 32−34−00 page 1 32−34−00 Page 4 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL DOWNLOCK ASSIST VALVE RUN−AROUND AND BYPASS VALVE LEVER TO LEFT MLG UPLOCK LEVER TO RIGHT MLG UPLOCK LEVER RELEASE CABLE RUN−AROUND AND BYPASS VALVE ram3234000_002.dg, om, 10/01/04 MLG UPLOCK LEVER CABLE LEFT MLG UPLOCK Alternate Extension/Components in Main Wheel Well − Component Location Figure 2 Master EFFECTIVITY: See Pageblock 32−34−00 page 1 32−34−00 Page 5 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL MANUAL RELEASE HANDLE CENTER PEDESTAL TO OPERATING LEVER NOSE DOOR OPERATING MECHANISM TO MANUAL RELEASE HANDLE RELEASE CABLE TO MLG RUN−AROUND AND BYPASS VALVE LEVER NLG DOOR BYPASS VALVE NLG BYPASS VALVE NLG UPLOCK ASSEMBLY NLG LEVER ASSEMBLY OPERATING LEVER OPERATING LEVER ASSEMBLY NLG RELEASE MECHANISM ram3234000_003.dc , JR/om, 10/01/04 RELEASE CABLE Alternate Extension/Components in Forward Fuselage − Component Location Figure 3 Master EFFECTIVITY: See Pageblock 32−34−00 page 1 32−34−00 Page 6 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL MANUAL RELEASE SYSTEM, LANDING GEAR − ADJUSTMENT/TEST 1. General A. The maintenance procedures that follow are for the operational test, the functional test, the adjustment of the manual release mechanism in the NLG bay, and also for the rigging of the manual release system for the landing gear. B. The operational test is a procedure that is currently referred to in other sections of the AMM. C. The functional test is similar to the operational test except that the functional test includes additional procedures to check the forces that are required to fully operate the manual release handle. D. The adjustment procedure gives the steps that are required to correctly adjust the manual release mechanism in the NLG bay (if necessary) before the rigging procedure is done. E. The rigging procedure gives the steps that are required to correctly rig the complete manual release system. TASK 32−34−00−710−801 Operational Test of the Landing Gear Manual−Release−System 1. Job Set−Up Information Subtask 32−34−00−946−001 A. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 10−11−00−000−801 TASK 10−11−00−000−802 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−803 TASK 12−00−06−863−804 TASK 12−00−07−861−801 TASK 12−00−07−861−802 TASK 27−54−00−866−802 TASK 32−22−01−980−802 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Removal of the Nose Landing Gear Lockpin Removal of the Main Landing Gear Lockpins Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 Connect External AC Power Remove External AC Power Electrical Retraction of the Flaps Close the Nose−Landing−Gear Forward Doors Master EFFECTIVITY: See Pageblock 32−34−00 page 501 32−34−00 Page 501 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL 2. Job Set−Up Subtask 32−34−00−582−007 A. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). Make sure that there is more than 4 inches (10 cm) between the landing gear tires and the ground. Subtask 32−34−00−865−001 B. Make sure that the circuit breakers that follow are closed: CB PANEL CBP−1 CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−4 CB NO. A2 F6 F7 G11 A2 F9 G15 P2 P3 B13 NAME HYD PUMP 3B PROX SENS LGC/D1 PROX SENS WOW 1 HYD SYST AC PUMP CONT 3B HYD PUMP 3A PROX SENS WOW 2 HYD SYST AC PUMP CONT 3A PROX SENS LGC/D1 PROX SENS LGC/D2 WOW 1 + 2 PROX SENS LGC/D2 ZONE 221 221 221 221 222 222 222 222 222 222 Subtask 32−34−00−840−001 C. D. Make sure that the LDG GEAR control handle is in the DN position. Make sure that the manual release handle is in the STOW position. **ON A/C 7033, 7041, 7052, 7138, 7149, 7180, 7189, 7193 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Pre SB601R−31−022 Subtask 32−34−00−980−003 E. To keep the landing gear horn from being heard during this procedure, move the throttle levers forward out of the IDLE position. Master EFFECTIVITY: See Pageblock 32−34−00 page 501 502 32−34−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7032, 7059, 7061, 7063, 7094, 7103, 7110, 7115, 7125, 7133, 7142, 7148, 7154, 7166−7167, 7170, 7205, 7272, 7365, 7371, 7384, 7390−7990, 8000−8064, 8066−8068 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Post SB601R−31−022 Subtask 32−34−00−980−004 F. To keep the landing gear horn from being heard during this procedure, and to make sure that the correct indication will be seen on the EICAS primary page, move the throttle levers forward out of the IDLE position. NOTE: If the throttle levers are in the IDLE position, the landing gear is not down and locked, and the logic state is satisfied for the landing gear horn to be heard for 10 seconds or more, one or more of the indications in the three GEAR boxes on the EICAS primary page will become amber and flash with a one second interval. This is a visual indication for additional landing safety and occurs even if the landing gear horn has been muted or disabled. **ON A/C ALL Subtask 32−34−00−861−001 G. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801). Subtask 32−34−00−866−001 H. Make sure that the flaps are fully retracted to zero degrees (Ref. TASK 27−54−00−866−802). Subtask 32−34−00−980−001 I. Make sure that the NLG forward doors are closed (Ref. TASK 32−22−01−980−802). Subtask 32−34−00−090−001 J. Remove the safety lockpins from the nose landing gear and from the main landing gear (Ref. TASK 10−11−00−000−801 and TASK 10−11−00−000−802). Master EFFECTIVITY: See Pageblock 32−34−00 page 501 503 32−34−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 3. Procedure NOTE: Unless it is specified in this procedure, ignore the three white−color UP indications in the GEAR boxes on the EICAS primary page. In this procedure, the three white−color UP indications will not go off after 30 seconds and is normal. When the aircraft is in the correct flight configuration, the three white−color UP indications go out of view after a maximum of 30 seconds after first being seen. This will only happen if: ± There is no message related to brakes, gear, flaps, antiskid, steering, WOW, or the proximity sensor system shown on the EICAS primary and status pages ± The flaps are at zero degrees ± There is no flap overspeed condition. **ON A/C 7003−7039, 7041−7052, 7054−7056, 7058−7060, 7062, 7064−7067, 7069−7098, 7100−7124, 7126−7141, 7143, 7145−7147, 7149−7156, 7158−7163, 7165−7166, 7168−7298, 7300−7328, 7330−7364, 7366−7369 Pre SB601R−32−077 Subtask 32−34−00−867−009 BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. Do the operational test of the manual release system for the landing gear as follows: (1) Pressurize hydraulic system No. 3A and No. 3B (Ref. TASK 12−00−06−863−803). (2) Make sure that the three green−color DN indications are shown in the three GEAR boxes on the EICAS primary page. (3) Put the LDG GEAR control handle to the UP position. (4) Make sure that: (a) The NLG forward doors open. (b) The three amber−color gear hash marks are shown in the three GEAR boxes on the EICAS primary page (the NLG and the MLG are in transit). (c) In 9 to 15 seconds, the three white−color UP indications are shown in the three GEAR boxes on the EICAS primary page (the NLG and the MLG are retracted and locked in the up position). (d) The NLG forward doors close. CAUTION: MAKE SURE THAT YOU DO NOT PULL THE MANUAL RELEASE HANDLE FOR THE LANDING GEAR MORE THAN 7.75 INCHES (19.7 CM). (5) Pull the landing gear manual−release−handle fully out until all of the NLG and MLG WARNING: A. Master EFFECTIVITY: See Pageblock 32−34−00 page 501 504 32−34−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL uplocks are released. NOTE: The uplock assemblies will be released when the handle has moved through its normal range of travel of approximately 6.5 inches (16.5 cm). NOTE: The operating mechanism for the NLG doors and the uplocks for the NLG and the MLG will release at different times when the manual release handle is pulled. The tension will increase at different positions along the handle travel as the uplocks release in sequence. (6) Make sure that: (a) The NLG forward doors open. (b) The three amber−color gear hash marks are shown on the EICAS primary page (the NLG and the MLG are in transit). (c) In less than 21 seconds, the three green−color DN indications are shown in the three GEAR boxes on the EICAS primary page (the NLG and the MLG are extended and locked in the down position). If a green−color DN indication does not come into view on the EICAS primary page, it is acceptable to use: ± a maximum force of five pounds (22.5 N) on the NLG as an acceptable alternative for aerodynamic forces to complete the down and locked sequence. ± slight hand pressure on the applicable MLG as an acceptable alternative to hydraulic system No. 2 ACMP (and the related MLG downlock assist actuator) to complete the down and locked sequence. WARNING: THE NOSE−LANDING−GEAR DOORS WILL CLOSE WHEN THE LANDING GEAR MANUAL−RELEASE−HANDLE IS PUT BACK TO THE STOWED POSITION. STAY AWAY FROM THE NOSE−LANDING−GEAR DOORS. WHEN THE DOORS CLOSE THEY CAN CAUSE INJURIES. CAUTION: PUT THE LDG GEAR SELECTOR HANDLE TO THE DOWN POSITION BEFORE THE MANUAL RELEASE HANDLE IS PUT BACK TO THE STOWED POSITION. IF YOU DO NOT DO THIS, THE NOSE LANDING GEAR WILL RETRACT INTO THE NOSE−LANDING−GEAR DOORS. THIS WILL CAUSE DAMAGE TO THE AIRCRAFT. (7) Put the LDG GEAR control handle to the DN position and then push the release button on top of the manual release handle and slowly return the manual release handle (under spring pressure) back to the STOW position. Make sure that the manual release handle unlocks and that the NLG forward doors close. (8) Release the release button on top of the manual release handle. Master EFFECTIVITY: See Pageblock 32−34−00 page 501 505 32−34−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7040, 7053, 7057, 7061, 7063, 7099, 7125, 7142, 7144, 7148, 7157, 7164, 7167, 7299, 7329, 7365, 7370−7990, 8000−8064, 8066−8068 and ON A/C 7003−7039, 7041−7052, 7054−7056, 7058−7060, 7062, 7064−7067, 7069−7098, 7100−7124, 7126−7141, 7143, 7145−7147, 7149−7156, 7158−7163, 7165−7166, 7168−7298, 7300−7328, 7330−7364, 7366−7369 Post SB601R−32−077 Subtask 32−34−00−867−002 BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. Do the operational test of the manual release system for the landing gear as follows: (1) Pressurize hydraulic system No. 3A and No. 3B (Ref. TASK 12−00−06−863−803). (2) Make sure that the three green−color DN indications are shown in the three GEAR boxes on the EICAS primary page. (3) Put the LDG GEAR control handle to the UP position. (4) Make sure that: (a) The NLG forward doors open. (b) The three amber−color gear hash marks are shown on the EICAS primary page (the NLG and the MLG are in transit). (c) In 9 to 15 seconds, the three white−color UP indications are shown in the three GEAR boxes on the EICAS primary page (the NLG and the MLG are retracted and locked in the up position). (d) The NLG forward doors close. CAUTION: MAKE SURE THAT YOU DO NOT PULL THE MANUAL RELEASE HANDLE FOR THE LANDING GEAR MORE THAN 10 INCHES (25.4 CM). (5) Pull the landing gear manual−release−handle fully out until all of the NLG and MLG uplocks are released. NOTE: The uplock assemblies will be released when the handle has moved through its normal range of travel of approximately 7.75 inches (19.7 cm). NOTE: The operating mechanism for the NLG doors and the uplocks for the NLG and the MLG will release at different times when the manual release handle is pulled. The tension will increase at different positions along the handle travel as the uplocks release in sequence. (6) Make sure that: (a) The NLG forward doors open. (b) The three amber−color gear hash marks are shown in the three GEAR boxes on the EICAS primary page (the NLG and the MLG are in transit). (c) In less than 21 seconds, the three green−color DN indications are shown in the three GEAR boxes on the EICAS primary page (the NLG and the MLG are extended and locked in the down position). If a green−color DN indication does not come into view on the EICAS primary WARNING: B. Master EFFECTIVITY: See Pageblock 32−34−00 page 501 506 32−34−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL page, it is acceptable to use: ± a maximum force of five pounds (22.5 N) on the NLG as an acceptable alternative for aerodynamic forces to complete the down and locked sequence. ± slight hand pressure on the applicable MLG as an acceptable alternative to hydraulic system No. 2 ACMP (and the related MLG downlock assist actuator) to complete the down and locked sequence. WARNING: THE NOSE−LANDING−GEAR DOORS WILL CLOSE WHEN THE LANDING GEAR MANUAL−RELEASE−HANDLE IS PUT BACK TO THE STOWED POSITION. STAY AWAY FROM THE NOSE−LANDING−GEAR DOORS. WHEN THE DOORS CLOSE THEY CAN CAUSE INJURIES. CAUTION: PUT THE LDG GEAR SELECTOR HANDLE TO THE DOWN POSITION BEFORE THE MANUAL RELEASE HANDLE IS PUT BACK TO THE STOWED POSITION. IF YOU DO NOT DO THIS, THE NOSE LANDING GEAR WILL RETRACT INTO THE NOSE−LANDING−GEAR DOORS. THIS WILL CAUSE DAMAGE TO THE AIRCRAFT. (7) Put the LDG GEAR control handle to the DN position and then push the release button on top of the manual release handle and slowly return the manual release handle (under spring pressure) back to the STOW position. Make sure that the manual release handle unlocks and that the NLG forward doors close. (8) Release the release button on top of the manual release handle. **ON A/C ALL 4. Close Out Subtask 32−34−00−980−005 A. Move the throttle levers aft to the IDLE position again. Subtask 32−34−00−863−001 B. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−34−00−490−001 C. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Subtask 32−34−00−861−006 D. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802). Subtask 32−34−00−586−001 E. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Master EFFECTIVITY: See Pageblock 32−34−00 page 501 507 32−34−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL TASK 32−34−00−720−801 Functional Test of the Landing Gear Manual−Release−System 1. Reason for the Job Refer to MRB 32−34−00−03. 2. Job Set−Up Information Subtask 32−34−00−943−004 A. Tools and Equipment REFERENCE G601R323002−1 None specified DESIGNATION Test hook, manual release−force (or equivalent) Force gauge, 0−100 pounds (0−445 N) Subtask 32−34−00−946−002 B. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 10−11−00−000−801 TASK 10−11−00−000−802 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−803 TASK 12−00−06−863−804 TASK 12−00−07−861−801 TASK 12−00−07−861−802 TASK 27−54−00−866−802 TASK 32−22−01−980−802 TASK 32−34−00−830−801 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Removal of the Nose Landing Gear Lockpin Removal of the Main Landing Gear Lockpins Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Pressurize Hydraulic System No. 3 Release Hydraulic Pressure − System No. 3 Connect External AC Power Remove External AC Power Electrical Retraction of the Flaps Close the Nose−Landing−Gear Forward Doors Rigging of the Manual Release System 3. Job Set−Up Subtask 32−34−00−582−002 A. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). Make sure that there is more than 4 inches (10 cm) between the landing gear tires and the ground. Subtask 32−34−00−865−002 B. Make sure that the circuit breakers that follow are closed: Master EFFECTIVITY: See Pageblock 32−34−00 page 501 508 32−34−00 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL CB PANEL CBP−1 CBP−1 CBP−1 CBP−1 CBP−2 CBP−2 CBP−2 CBP−2 CBP−2 CBP−4 CB NO. A2 F6 F7 G11 A2 F9 G15 P2 P3 B13 NAME HYD PUMP 3B PROX SENS LGC/D1 PROX SENS WOW 1 HYD SYST AC PUMP CONT 3B HYD PUMP 3A PROX SENS WOW 2 HYD SYST AC PUMP CONT 3A PROX SENS LGC/D1 PROX SENS LGC/D2 WOW 1 + 2 PROX SENS LGC/D2 ZONE 221 221 221 221 222 222 222 222 222 222 Subtask 32−34−00−840−002 C. D. Make sure that the LDG GEAR control handle is in the DN position. Make sure that the manual release handle is in the STOW position and then do the step that follows: (1) Measure and make a note of the vertical distance between the bottom of the manual release handle and the pedestal. This reference dimension will be used to determine the actual travel dimension of the manual release handle in this procedure. **ON A/C 7033, 7041, 7052, 7138, 7149, 7180, 7189, 7193 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Pre SB601R−31−022 Subtask 32−34−00−980−006 E. To keep the landing gear horn from being heard during this procedure, move the throttle levers forward of the IDLE position. Master EFFECTIVITY: See Pageblock 32−34−00 page 501 509 32−34−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL **ON A/C 7032, 7059, 7061, 7063, 7094, 7103, 7110, 7115, 7125, 7133, 7142, 7148, 7154, 7166−7167, 7170, 7205, 7272, 7365, 7371, 7384, 7390−7990, 8000−8064, 8066−8068 and ON A/C 7003−7031, 7034−7040, 7042−7051, 7053−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7137, 7139−7141, 7143−7147, 7150−7153, 7155−7165, 7168−7169, 7171−7179, 7181−7188, 7190−7192, 7194−7204, 7206−7271, 7273−7364, 7366−7370, 7372−7383, 7385−7389 Post SB601R−31−022 Subtask 32−34−00−980−007 F. To keep the landing gear horn from being heard during this procedure, and to make sure that the correct indication will be seen on the EICAS primary page, move the throttle levers forward of the IDLE position. NOTE: If the throttle levers are in the IDLE position, the landing gear is not down and locked, and the logic state is satisfied for the landing gear horn to be heard for 10 seconds or more, one or more of the indications in the three GEAR boxes on the EICAS primary page will become amber and flash with a one second interval. This is a visual indication for additional landing safety and occurs even if the landing gear horn has been muted or disabled. **ON A/C ALL Subtask 32−34−00−861−007 G. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801). Subtask 32−34−00−866−002 H. Make sure that the flaps are fully retracted to zero degrees (Ref. TASK 27−54−00−866−802). Subtask 32−34−00−980−002 I. Make sure that the NLG forward doors are closed (Ref. TASK 32−22−01−980−802). Subtask 32−34−00−090−002 J. Remove the safety lockpins from the nose landing gear and the main landing gear (Ref. TASK 10−11−00−000−801 and TASK 10−11−00−000−802). Subtask 32−34−00−840−013 K. Prepare the aircraft for the functional test of the manual release system as follows: (1) Pressurize hydraulic system No. 3A and No. 3B (Ref. TASK 12−00−06−863−803). (2) Make sure that the three green−color DN indications can be seen in the three GEAR boxes on the EICAS primary page. WARNING: BEFORE THE EXTENSION/RETRACTION OF THE LANDING GEAR, MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE GEAR MOVEMENT AREAS. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURIES. (3) Put the LDG GEAR control handle to the UP position. Master EFFECTIVITY: See Pageblock 32−34−00 page 501 510 32−34−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL (4) Make sure that: (a) The NLG forward doors open. (b) The three amber−color gear hash marks are shown in the three GEAR boxes on the EICAS primary page (the NLG and the MLG are in transit). (c) In 9 to 15 seconds, the three white−color UP indications are shown in the three GEAR boxes on the EICAS primary page (the NLG and the MLG are retracted and locked in the up position). (d) The NLG forward doors close. (5) Attach the test hook and the force gauge to the manual release handle. 4. Procedure NOTE: Unless it is specified in this procedure, ignore the three white−color UP indications in the GEAR boxes on the EICAS primary page. In this procedure, the three white−color UP indications will not go off after 30 seconds and is normal. When the aircraft is in the correct flight configuration, the three white−color UP indications go out of view after a maximum of 30 seconds after first being seen. This will only happen if: ± There is no message related to brakes, gear, flaps, antiskid, steering, WOW, or the proximity sensor system shown on the EICAS primary and status pages ± The flaps are at zero degrees ± There is no flap overspeed condition. **ON A/C 7003−7039, 7041−7052, 7054−7056, 7058−7060, 7062, 7064−7067, 7069−7098, 7100−7124, 7126−7141, 7143, 7145−7147, 7149−7156, 7158−7163, 7165−7166, 7168−7298, 7300−7328, 7330−7364, 7366−7369 Pre SB601R−32−077 Subtask 32−34−00−720−003 A. Do the functional test of the manual release system for the landing gear as follows: (1) Do the steps that follow to make a record of the actual travel of the manual release handle, the force that is required to release the landing gear, and also the NLG extension time. CAUTION: MAKE SURE THAT YOU DO NOT USE A FORCE OF MORE THAN 75 POUNDS−FORCE (334 N) OR A TRAVEL DIMENSION OF MORE THAN 7.75 INCHES (19.7 CM) WHEN YOU PULL THE MANUAL RELEASE HANDLE FOR THE LANDING GEAR. (a) Pull the landing gear manual−release−handle fully out with the force gauge and test hook at a constant slow speed until the operating mechanism for the NLG doors and the uplocks for the NLG and the MLG are released. NOTE: The operating mechanism for the NLG doors and the uplocks for the NLG and the MLG will release at different times when the manual release handle is pulled. The tension will increase at different positions along the handle travel as the uplocks release in sequence. (b) Make sure that: Master EFFECTIVITY: See Pageblock 32−34−00 page 501 511 32−34−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL 1 The NLG doors−uplock latch and the MLG uplock latches unlock (the order in which they unlatch is not important). NOTE: If the manual release handle is between two notches when all of the uplock latches unlock, let the manual release handle go back to the lower notch. 2 The NLG forward doors open. 3 The three amber−color gear hash marks are shown in the three GEAR boxes on the EICAS primary page (the NLG and the MLG are in transit). 4 After a maximum of 21 seconds, the three green−color DN indications are shown in the three GEAR boxes on the EICAS primary page (the NLG and the MLG are extended and locked in the down position). If a green−color DN indication does not come into view on the EICAS primary page, it is acceptable to use: ± a maximum force of five pounds (22.5 N) on the NLG as an acceptable alternative for aerodynamic forces to complete the down and locked sequence ± slight hand pressure on the applicable MLG as an acceptable alternative to hydraulic system No. 2 ACMP (and the related MLG downlock assist actuator) to complete the down and locked sequence. (c) With the shaft of the manual release handle held in position at a notch, measure the distance from the pedestal base to the bottom of the manual release handle. (d) To determine the actual travel dimension, subtract the reference dimension from the measured dimension that was obtained in the Job Set−Up part of this TASK. (e) Make sure that you recorded the measurements that follow: ± The force that was required to release the landing gear was between 45 and 62 pounds (200 and 276 N) ± The actual travel dimension of the manual release handle was a maximum of 6.5 inches (16.5 cm) ± The NLG extension time (to the fully extended and locked position) was a maximum of 14 seconds ± The MLG extension time (to the fully extended and locked position) was a maximum of 21 seconds. WARNING: THE NOSE−LANDING−GEAR DOORS WILL CLOSE WHEN THE LANDING GEAR MANUAL−RELEASE−HANDLE IS PUT BACK TO THE STOWED POSITION. STAY AWAY FROM THE NOSE−LANDING−GEAR DOORS. WHEN THE DOORS CLOSE THEY CAN CAUSE INJURIES. CAUTION: PUT THE LDG GEAR SELECTOR HANDLE TO THE DOWN POSITION BEFORE THE MANUAL RELEASE HANDLE IS PUT BACK TO THE STOWED POSITION. IF YOU DO NOT DO THIS, THE NOSE LANDING GEAR WILL RETRACT INTO THE NOSE−LANDING−GEAR DOORS. THIS WILL CAUSE DAMAGE TO THE AIRCRAFT. (2) Put the LDG GEAR control handle to the DN position and then push the release Master EFFECTIVITY: See Pageblock 32−34−00 page 501 512 32−34−00 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL button on top of the manual release handle and slowly return the manual release handle (under spring pressure) back to the STOW position. Make sure that the manual release handle unlocks and that the NLG forward doors close. (3) Release the release button on top of the manual release handle. Subtask 32−34−00−830−002 B. If you get any of the conditions that follow, do the rigging of the manual release system (Ref. TASK 32−34−00−830−801) : ± the force required to unlock the landing gear is more than 62 pounds (276 N) ± the actual travel dimension of the manual release handle is more than 6.5 inches (16.5 cm). **ON A/C 7040, 7053, 7057, 7061, 7063, 7099, 7125, 7142, 7144, 7148, 7157, 7164, 7167, 7299, 7329, 7365, 7370−7990, 8000−8064, 8066−8068 and ON A/C 7003−7039, 7041−7052, 7054−7056, 7058−7060, 7062, 7064−7067, 7069−7098, 7100−7124, 7126−7141, 7143, 7145−7147, 7149−7156, 7158−7163, 7165−7166, 7168−7298, 7300−7328, 7330−7364, 7366−7369 Post SB601R−32−077 Subtask 32−34−00−720−004 C. Do the functional test of the manual release system for the landing gear as follows: (1) Do the steps that follow to make a record of the actual travel of the manual release handle, the force that is required to release the landing gear, and also the NLG extension time. CAUTION: MAKE SURE THAT YOU DO NOT USE A FORCE OF MORE THAN 58 POUNDS (258 N) OR A TRAVEL DIMENSION OF MORE THAN 10 INCHES (25.4 CM) WHEN YOU PULL THE MANUAL RELEASE HANDLE FOR THE LANDING GEAR. (a) Pull the landing gear manual−release−handle fully out with the force gauge and test hook at a constant slow speed until the operating mechanism for the NLG doors and the uplocks for the NLG and the MLG are released. NOTE: The operating mechanism for the NLG doors and the uplocks for the NLG and the MLG will release at different times when the manual release handle is pulled. The tension will increase at different positions along the handle travel as the uplocks release in sequence. (b) Make sure that: 1 The NLG doors−uplock latch and the MLG uplock latches unlock (the order in which they unlatch is not important). NOTE: If the manual release handle is between two notches when all of the uplock latches unlock, let the manual release handle go back to the lower notch. 2 The NLG forward doors open. 3 The three amber−color gear hash marks are shown in the three GEAR boxes on the EICAS primary page (the NLG and the MLG are in transit). 4 After a maximum of 21 seconds, the three green−color DN indications are shown in the three GEAR boxes on the EICAS primary page (the NLG and the MLG are extended and locked in the down position). Master EFFECTIVITY: See Pageblock 32−34−00 page 501 513 32−34−00 DecPage 10/2005 C AIRCRAFT MAINTENANCE MANUAL If a green−color DN indication does not come into view on the EICAS primary page, it is acceptable to use: ± a maximum force of five pounds (22.5 N) on the NLG as an acceptable alternative for aerodynamic forces to complete the down and locked sequence ± slight hand pressure on the applicable MLG as an acceptable alternative to hydraulic system No. 2 ACMP (and the related MLG downlock assist actuator) to complete the down and locked sequence. (c) With the shaft of the manual release handle held in position at a notch, measure the distance from the pedestal base to the bottom of the manual release handle. (d) To determine the actual travel dimension, subtract the reference dimension from the measured dimension that was obtained in the Job Set−Up part of this TASK. (e) Make sure that you recorded the measurements that follow: ± The force that was required to release the landing gear was between 25 and 46 pounds (111 and 205 N) ± The actual travel dimension of the manual release handle was a maximum of 7.75 inches (19.7 cm) ± The NLG extension time (to the fully extended and locked position) was a maximum of 14 seconds ± The MLG extension time (to the fully extended and locked position) was a maximum of 21 seconds. WARNING: THE NOSE−LANDING−GEAR DOORS WILL CLOSE WHEN THE LANDING GEAR MANUAL−RELEASE−HANDLE IS PUT BACK TO THE STOWED POSITION. STAY AWAY FROM THE NOSE−LANDING−GEAR DOORS. WHEN THE DOORS CLOSE THEY CAN CAUSE INJURIES. CAUTION: PUT THE LDG GEAR SELECTOR HANDLE TO THE DOWN POSITION BEFORE THE MANUAL RELEASE HANDLE IS PUT BACK TO THE STOWED POSITION. IF YOU DO NOT DO THIS, THE NOSE LANDING GEAR WILL RETRACT INTO THE NOSE−LANDING−GEAR DOORS. THIS WILL CAUSE DAMAGE TO THE AIRCRAFT. (2) Put the LDG GEAR control handle to the DN position and then push the release button on top of the manual release handle and slowly return the manual release handle (under spring pressure) back to the STOW position. Make sure that the manual release handle unlocks and that the NLG forward doors close. (3) Release the release button on top of the manual release handle. Subtask 32−34−00−830−003 D. If you get any of the conditions that follow, do the rigging of the manual release system (Ref. TASK 32−34−00−820−801) : ± the force required to unlock the landing gear is more than 46 pounds (205 N) ± the actual travel dimension of the manual release handle is more than 7.75 inches (19.7 cm). Master EFFECTIVITY: See Pageblock 32−34−00 page 501 514 32−34−00 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL **ON A/C ALL 5. Close Out Subtask 32−34−00−980−008 A. Move the throttle levers aft to the SHUT OFF position again. Subtask 32−34−00−863−002 B. Release the hydraulic pressure from system No. 3 (Ref. TASK 12−00−06−863−804). Subtask 32−34−00−490−005 C. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Subtask 32−34−00−861−008 D. Remove the external AC power (Ref. TASK 12−00−07−861−802). Subtask 32−34−00−586−002 E. Lower the aircraft and remove the jacks (Ref. TASK 07−11−01−582−804). Master EFFECTIVITY: See Pageblock 32−34−00 page 501 515 32−34−00 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL TASK 32−34−00−830−801 Rigging of the Manual Release Mechanism 1. Job Set−Up Information Subtask 32−34−00−943−002 A. Tools and Equipment REFERENCE G601R270001−1 None specified None specified DESIGNATION Kit, rigging pin Torque wrench 0−200 pound−inches (0−25 N·m) Force gauge, 0−100 pounds (0−445 N) Subtask 32−34−00−944−001 B. Consumable Materials REFERENCE 05−004 DESIGNATION Lockwire Subtask 32−34−00−945−001 C. Parts REF 1 2 3 4 7 8 10 11 12 13 16 17 23 27 30 31 50 51 55 56 57 NAME OF PART Screw Cable ball seal Safety clip Turnbuckle Safety clip Turnbuckle Screw Cable ball seal Safety clip Turnbuckle Safety clip Turnbuckle Clevis pin Lock Cotter pin Washer Safety clip Turnbuckle Stop bolt Cotter pin Nut Master EFFECTIVITY: See Pageblock 32−34−00 page 501 QTY 1 2 2 1 2 1 2 2 4 2 2 1 1 1 1 1 2 1 1 1 1 IPC SEQUENCE NO. IPC 32−34−00−02−490 IPC 32−34−00−02−485 IPC 32−34−00−02−060 IPC 32−34−00−02−055 IPC 32−34−00−02−065 IPC 32−34−00−02−050 IPC 32−34−00−03−435 IPC 32−34−00−03−430 IPC 32−34−00−03−040 IPC 32−34−00−03−035 IPC 32−34−00−03−048 IPC 32−34−00−03−047 IPC 32−34−00−03−125 IPC 32−34−00−03−165 IPC 32−34−00−03−135 IPC 32−34−00−03−130 IPC 32−34−00−02−133 IPC 32−34−00−02−130 IPC 32−34−00−01−220 IPC 32−34−00−01−240 IPC 32−34−00−01−235 32−34−00 Page 516 Apr 20/2004 C AIRCRAFT MAINTENANCE MANUAL REF 58 59 NAME OF PART Washer Shim washer QTY A/R A/R IPC SEQUENCE NO. IPC 32−34−00−01−230 IPC 32−34−00−01−225 Subtask 32−34−00−946−003 D. Reference Information REFERENCE TASK 07−11−01−582−801 TASK 07−11−01−582−804 TASK 10−11−00−400−801 TASK 10−11−00−400−802 TASK 12−00−06−863−804 TASK 12−00−07−861−802 TASK 32−22−01−980−801 TASK 32−22−01−980−802 TASK 32−22−10−830−801 TASK 32−30−00−720−801 TASK 32−30−00−710−802 TASK 32−34−00−720−801 TASK 32−34−00−820−801 TASK 32−61−05−220−801 TASK 32−61−05−820−801 TASK 53−83−01−000−801 TASK 53−83−01−400−801 DESIGNATION Put the Aircraft on Jacks Removal of the Aircraft from Jacks Installation of the Nose Landing Gear Lockpin Installation of the Main Landing Gear Lockpins Release Hydraulic Pressure − System No. 3 Remove External AC Power Open and Isolate the Nose−Landing−Gear Forward Doors Close the Nose−Landing−Gear Forward Doors Adjustment of the NLG Door Actuator and Mechanism Functional Test of the Landing Gear Extension/Retraction System Landing Gear Extension and Retraction − Maintenance Practices Functional Test of the Landing Gear Manual Release System Adjustment of the NLG Manual Release System Clearance Check of the Landing Gear Proximity Sensors Adjustment of the Landing Gear Proximity Sensors Removal of the MLG Wheel Bins Installation of the MLG Wheel Bins 2. Job Set−Up Subtask 32−34−00−840−025 A. B. Make sure that the LDG GEAR control handle is in the DN position. Make sure that the manual release handle is in the STOW position. Master EFFECTIVITY: See Pageblock 32−34−00 page 501 517 32−34−00 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−34−00−490−011 C. Install the safety lockpins at the nose landing gear and at the main landing gear (Ref. TASK 10−11−00−400−801 and TASK 10−11−00−400−802). Subtask 32−34−00−582−012 D. Lift the aircraft on jacks (Ref. TASK 07−11−01−582−801). Make sure that there is more than 4 inches (10 cm) between the landing gear tires and the ground. Subtask 32−34−00−010−022 E. F. Remove the left and right MLG wheel bins (Ref. TASK 53−83−01−000−801). Remove the flight compartment floor panel 221 ALF or open the main avionics compartment door 811 to get access to the manual release components that are under the flight compartment floor. WARNING: IF THE NOSE DOOR MAINTENANCE SWITCH AT THE EXTERNAL SERVICES PANEL IS SET TO THE "FLT NORM" POSITION, THE NOSE−LANDING−GEAR (NLG) FORWARD DOORS WILL CLOSE WHEN HYDRAULIC SYSTEM NO. 3 IS PRESSURIZED. WHEN YOU DO MAINTENANCE ON OR NEAR THE NLG WITH THE FORWARD DOORS OPEN, MAKE SURE THAT YOU: ± ALWAYS SET THE NOSE DOOR MAINTENANCE SWITCH TO THE "OPEN" POSITION TO ISOLATE THE NLG FORWARD DOORS FROM HYDRAULIC SYSTEM NO. 3 ± RELEASE THE PRESSURE FROM HYDRAULIC SYSTEM NO. 3. FAILURE TO DO THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. G. Open and isolate the NLG forward doors (Ref. TASK 32−22−01−980−801). Subtask 32−34−00−863−016 H. Make sure that hydraulic system No. 3 is not pressurized (Ref. TASK 12−00−06−863−804). Subtask 32−34−00−840−026 Refer to Figure 501. I. If an adjustable component of the NLG door operating mechanism or related proximity sensor system was replaced before you started this TASK, make sure that the NLG door operating mechanism is correctly adjusted (Ref. TASK 32−22−10−830−801). J. If any of the manual release system components that follow were replaced or adjusted before you started this TASK, make sure that the manual release mechanism in the NLG bay is adjusted correctly (Ref. TASK 32−34−00−820−801). ± The NLG uplock assembly (37) ± The NLG bypass valve (48) ± The NLG−door bypass valve (47) ± The cross shaft (49). Master EFFECTIVITY: See Pageblock 32−34−00 page 501 518 32−34−00 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL Subtask 32−34−00−030−007 Refer to Figure 501. K. Do the steps that follow to prepare the manual release system for the rigging procedure: (1) Loosen the screws (1) that hold the cable ball seals (2) in position in the NLG bay at FS 202.75. (2) Remove the safety clips (3) from the turnbuckle (4) and loosen the turnbuckle (4) until the input cable (5) for the NLG release mechanism is disconnected from the input cable (6) for the MLG release mechanism. (3) Remove the safety clips (7) from the turnbuckle (8) and loosen the turnbuckle (8) until there is no load on the cable (9) to the manual release handle. (4) Loosen the screws (10) that hold the cable ball seals (11) in position in the MLG bay at LBL 12. (5) Remove the safety clips (12) from the two turnbuckles (13) and loosen both of the turnbuckles (13) until there is no load on the uplock release cable (14) and the uplock release cable (15) for the MLG. (6) Remove the safety clips (16) from the turnbuckle (17). (7) Loosen the turnbuckle (17) until the threads of the input cable (6) for the MLG release mechanism and the threads on the fork−end that is attached to the lever (18) can just be seen. Do not loosen the turnbuckle (17) any further. (8) Tighten the turnbuckle (17) five to six turns. If necessary, temporarily safety the turnbuckle (17) with the safety clips (16). Do not lock the safety clips (16) at this time. (9) Manually close the latches of the right and the left MLG uplock assemblies (20). (10) Operate the lever (18) by hand and make sure that the clevis pin (21) that attaches the spool for the runaround and bypass valve (19) does not catch on the bracket (22). Make sure that the clevis pin (21) points down. NOTE: The runaround and bypass valve (19) is internally spring loaded to stay in the fully retracted position. 3. Procedure Refer to Figure 501, sheet 3. Subtask 32−34−00−820−008 A. Do the initial adjustment of the manual release mechanism in the MLG bay as follows: (1) Install the rigging pin P1 through the bracket (22) and the lever (18) of the runaround and bypass valve (19). (2) Do a check to make sure that the clevis pin (23) that attaches the link assembly (24) to the downlock assist valve (25) can move freely. If the clevis clevis pin (23) cannot move freely (or the rigging pin P1 could not be installed easily) do the steps that follow: NOTE: It is possible that you will need to move the lever (18) slightly inboard or outboard by hand to compensate for the springs that are attached near forward end of the lever (18). NOTE: If the clevis clevis pin (23) can move freely go to the next step. Master EFFECTIVITY: See Pageblock 32−34−00 page 501 519 32−34−00 DecPage 15/2004 C AIRCRAFT MAINTENANCE MANUAL (3) (4) (5) (6) (a) Remove the lockwire that secures the nut (26) of the link assembly (24). (b) Loosen the nut (26) of the link assembly (24) sufficiently to disengage the lock (27) from the groove in the rod−fitting (28) and the related groove in the fork−end (29) of the link assembly (24). Remove and keep the lock (27). (c) Remove the cotter pin (30) and the washer (31) from t
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