BHT-206L1-MM-2

BHT-206L1-MM-2
,
MAINTENANCE
MANUAL
VOLUME
2
INSTRUMENTS-ELECTRICAL-AVIONICS
NOTICE
The instructions
set forth in this manual, as supplemented
or modified by Alert Service Bulletins
and other directions issued by Bell Helicopter Textron and Airworthiness
Directives issued by the
Federal Aviation Administration,
shall be strictly followed.
A Subsidiary of Textron Inc.
COPYRIGHT NOTICE
COPYRIGHT
1993
POST OFFICE BOX 482.
AND BELL HELICOPTER TEXTRON.
A DIVISION OF TEXTRON CANADA LTD.
ALL RIGHTS RESERVED
FORT WORTH. TEXAS 76101
3 DECEMBER
REISSUE
15 JANUARY
1977
1993
BHT-206L1-MM-2
Additional
copies of this publication may be obtained by contacting:
Commercial Publication
Distribution Center
Bell Helicopter Textron
P.O. Box 482
Fort Worth, Texas 78101-0482
BHT-206L1-MM-2
LIST OF EFFECTIVE
PAGES
,
On a revised page the portion
indicated by a vertical line.
Original ..............
Revision .............
of the text and illustration
0 .... .3 December
1 .. .14 September
Page
No.
1977
1978
Vol. Date/
Rev. No.
Cover ...................................
Title .....................................
PN ......................................
A/B ......................................
1-1/1-2 ..................................
1-3/1-4 ..................................
95-l - 95-2 .............................
95-3/95-4 ................................
95-5 - 95-12 ...........................
95-13/95-14..
...........................
95-15/95-18
.............................
95-17 - 95-20 ..........................
95-21/95-22
.............................
95-23 - 95-24 ..........................
0
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0
0
0
0
0
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0
0
0
0
0
0
affected
Revision .............
Revision .............
Reissue .............
by the latest
revision
is
2 .........
15 April 1980
3. ........
.15 July 1981
0 ..... .15 January 1993
Page
No.
96-1 - 96-20 ...........................
96-21/96-22 .............................
96-23 - 98-40 ..........................
96-41/96-42 .............................
98-43 - 96-48 ..........................
96-49/96-50..
...........................
96-51/96-52 .............................
96-53/98-54 .............................
97-1/97-2 ................................
97-3 - 97-30 ...........................
98-l - 98-50 ...........................
98-51/98-52 .............................
Index 1 - Index 6 ......................
Vol. Date/
Rev. No.
0
0
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NOTE
This complete
reissue of Volume 2 supersedes
original
Volume 2 dated 3 December 1977 and Revisions 1 through
3. Please discard original Volume 2 and revisions.
-
A/B
E
VALUATE
L
OGISTICS
P
L
UBLICATIONS
Have you found something
wrong with this manual - an
error,
an inconsistency,
unclear
instructions,
etc?
Although
we strive for accuracy
and clarity,
we may
make errors on occasion.
If we do and you discover
it,
we would appreciate
your telling us about it so that we
can change whatever
is incorrect
or unclear.
Please be
as specific as possible.
Your complaint
or suggestion
will be acknowledged
we will tell you what we intend to do.
You may use the enclosed
Customer
Feedback
applicable,
to inform us where we have erred.
Your
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and
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BHT-206L1-MM-2
CHAPTER
CONTENTS
Paragraph
Number
l-l
l-2
-
1 -
INTRODUCTION
MAINTENANCE
Title
.................................
Scope of manual
Use of manual ....................................
PROCEDURES
Chapter/Section
Number
1-00-00
1-00-00
Page
Number
3
3
1-00-00
Page 1/2
BHT-206L1-MM-2
INTRODUCTION
l-l.
SCOPE OF MANUAL.
This maintenance
manual (Volume II, Model
206L1, instruments,
Electrical, Avionics, and
Wiring Diagrams) includes the necessary data
to provide
helicopter
operators
with field
maintenance
procedures.
Table
l-1.
List
TITLE
CHAPTER
INTRODUCTION
INSTRUMENT
SYSTEM
ELECTRICAL SYSTEM
AVIONICS SYSTEM
WIRING DIAGRAMS
ALPHABETICAL
INDEX
1-2.
of chapters
1-00-00
95-00-00
96-00-00
97-00-00
98-00-00
INDEX 1
USE OF MANUAL.
Preceding
each Chapter
is a Table
of
Contents, List of Tables, and List of Figures
to enable the user to quickly determine where
the information
sought can be found. The
data in each chapter is divided into systems
(DC Power Systems,
Indicator
Systems,
Caution and Warning Systems, etc.). These
systems are further divided into subsystems.
As an example,
under DC Power Systems
would follow: Battery System, External Power
System,
Generator
System,
and StarterIgniter System. The wiring diagrams, also, are
provided as System Wiring Diagrams for ease
of troubleshooting
and circuit analysis. The
last chapter of this manual, the Alphabetical
Index, lists all primary headings with crossindexing.
NOTE
Model 206L1
series
maintenance
manuals
are
currently
being
reformatted and revolumized. Chapters
95 through 98 have been updated and
are in Bell Helicopter’s
Automated
Technical
Publications
(ATP) system.
To expedite this information to the field
for the benefit
of our customers,
existing Volume 2 is reissued using the
inprocess
format
for chapters
95
through 98.
1-00-00
Page 3/4
BHT-206L1
CHAPTER
CONTENTS
Paragraph
Number
95-l
95-2
95-3
95-4
95-5
95-6
95-7
95-8
95-9
95 -
MAINTENANCE
--
.................................
Pitot-static system.. ..............................
Removal - pitot tube and static ports .........
Cleaning - pitot-static system .................
Inspection - pitot-static system ...............
Installation - pitot tube and static ports .......
Testing - pitot-static system ..................
Airspeed indicator ................................
Altimeter ..........................................
Inclinometer
......................................
95-23
95-24
95-25
95-26
95-27
95-28
95-29
--
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
10
IO
10
IO
IO
10
10
13
13
13
95-00-00
95-00-00
95-00-00
15
15
15
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
17
17
17
17
17
17
95-00-00
18
INSTRUMENTS
Navigation instruments
...........................
Standby magnetic compass ......................
Calibration - standby magnetic compass ......
PROPULSION
Page
Number
INSTRUMENTS
instruments
NAVIGATION
95-20
95-21
95-22
Chapter/Section
Number
Instrument system ................................
Troubleshooting
instruments ......................
Instruments maintenance
practices ...............
Removal - instruments ........................
Inspection - instruments
......................
Installation - instruments ......................
Instrument panel maintenance
practices ..........
Removal - instrument panel ..................
Installation - instrument panel ................
Flight
SYSTEM
PROCEDURES
Title
FLIGHT
95-l 0
95-l 1
95-12
95-l 3
95-14
95-15
95-l 6
95-l 7
95-18
95-19
INSTRUMENT
-MM-10
INSTRUMENTS
Propulsion instruments
...........................
Dual tachometer ..................................
Operational check - dual tachometer .........
Gas producer tachometer .........................
Operational check - gas producer tachometer
Engine oil temperature/pressure
indicator ........
Operational check - engine oil temperature/
pressure indicator ..............................
95-00-00
Page
1
BHT-206L1-MM-10
CONTENTS
Paragraph
Number
95-30
95-31
95-32
95-33
95-34
95-35
95-36
95-37
95-38
95-39
95-40
95-41
95-42
-
MAINTENANCE
(Cont)
Chapter/Section
Number
Title
Bleeding pressure gage line - engine oil
temperature/pressure
indicator . . . . . . . . . . . . . . . . .
Transmission
oil temperature/pressure
indicator..
Operational check - transmission
oil
temperature/pressure
indicator . . . . . . . . . . . . . . . . .
Bleeding pressure gage line - transmission
oil temperature/pressure
indicator.. . . . . . . . . . . . .
Fuel quantity indicator..
..........................
Fuel pressure indicator . . . . . . . . . . . . . . . . . . . . . . . . . . .
Operational check - fuel pressure indicator..
.
Engine torquemeter..
. . . . . . . . . . . . . . . . . . . . . .. . . . . . .
Operational check - engine torquemeter..
....
Bleeding - engine torquemeter gage pressure
line.............................................
Turbine outlet temperature indicator.. . . . . . . . . . . . .
Maintenance - turbine outlet temperature
, indicator........................................
Operational check - turbine outlet
temperature
indicator and circuitry . . . . . . . . . . . . .
MISCELLANEOUS
95-43
95-44
95-45
95-46
95-47
95-48
95-49
PROCEDURES
Page
Number
95-00-00
95-00-00
18
18
95-00-00
18
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
18
19
19
19
19
95-00-00
95-00-00
19
19
95-00-00
20
95-00-00
20
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
95-00-00
23
23
23
23
23
23
23
19
INSTRUMENTS
Miscellaneous
instruments ........................
DC loadmeter .....................................
Engine hourmeter .................................
Operational check - engine hourmeter ........
Clock.. ...........................................
Free air temperature
indicator ....................
Maintenance - free air temperature indicator
FIGURES
Figure
Number
95-l
95-2
95-00-00
Page 2
Title
Instrument
Instrument
panel......................................~
......................
piping installation
................................................
Page
Number
8
12
BHT-206L1
-MM10
TABLES
Table
Number
95-1
Title
instruments
troubleshooting..
............................,...................
Page
Number
6
95-00-00
Page 3/4
BHT-206L1-MM-10
INSTRUMENT
95-1.
INSTRUMENT
b.
SYSTEM.
Instrument
system
is divided
into four
categories;
flight, navigation,
propulsion,
and
miscellaneous.
All indicators are installed in
hinged instrument
panel, figure 95-1, except
pilot standby compass, hourmeter,
and free
air temperature
indicator.
Pilot standby
compass is mounted in a support attached to
right side of cabin structure, slightly forward
of instrument panel. Hourmeter is mounted in
nose compartment
and free air temperature
indicator is mounted in windshield.
1. Flight instrument
system consists of pitotstatic system and following instruments
and
panels:
a.
Airspeed
Gas producer
C.
Engine
indicator.
oil
d. Transmission
indicator.
tachometer
temperature/pressure
oil temperature/pressure
e.
Fuel quantity
indicator.
f.
Fuel pressure
indicator.
g.
Engine torque
h.
Turbine
indicator.
meter.
outlet temperature
indicator.
indicator.
4. Miscellaneous
instrument
following instruments:
b.
Altimeter.
C.
Inclinometer.
d.
Airspeed
limitation
panel:
In mph (effective
45154 through 45238).
helicopter
S/N
(2) In knots (effective
45239 and subsequent).
helicopter
S/N
(1)
2. Navigation instrument system
pilot standby magnetic compass.
3. Propulsion
instrument
following instruments:
a.
SYSTEM
Dual tachometer
system
consists
includes
of
a.
Hourmeter.
b.
8-day clock.
C.
Free air temperature
d.
Loadmeter.
system includes
indicator.
95-2. TROUBLESHOOTING
INSTRUMENTS.
Malfunctions
pertaining
to basic aircraft
instruments
are typical.
Table
95-l
in
conjunction
with wiring diagrams in Chapter
98 are used as a guide in troubleshooting.
indicator.
95-00-00
Page 5
BHT-206L1-MM-10
Table
INDICATION
TROUBLE
95-l.
Instruments
OF
PROBABLE
Excessive
scale error.
moves backward.
Indication
Indicator
only half.
fails to operate.
reading
No reading
(TOT).
on indicator
in tachometer.
polarity.
Replace.
Interchange
leads.
Leads connected
to wrong
terminals on indicator.
Refer to wiring diagram.
Circuit breaker.
Replace
Faulty wiring.
Repair as necessary.
Defective
tachometer
Replace.
TURBINE
Incorrect
ACTION
TACHOMETER
Weak magneto
Reversed
CORRECTIVE
CAUSE
DUAL
Pointer
troubleshooting
Harness
transmitter/
generator.
OUTLET
circuit breaker.
TEMPERATURE
Calibrate
ohms.
not calibrated.
Open or defective
breaker.
circuit
harness
Check and replace
breaker.
Loose
co n n e c t i o n s o n
indicator,
terminal
block or
connector.
Clean and tighten
Open thermocouple
Check harness.
harness.
5 to
faulty
100
circuit
connections.
,
Inaccurate
readings.
TOT light inoperative.
95-00-00
Page 6
Shorts
or open in engine
thermocouple
harness.
Check harness.
Improper thermocouple
resistance.
Check harness.
Defective
TOT
circuit wiring.
loop
overtemp
Replace
or repair wiring.
Defective
TOT overtemp
circuitry in indicator.
Replace
indicator.
6
BHT-206L1-MM-10
Table
95-1.
Instruments
troubleshooting
(Cont)
!
INDICATION
TROUBLE
OF
PROBABLE
TOT light does not illuminate
at
appropriate
overtemperature
indication.
Defective
indicator.
Overtemp
needed.
CAUSE
overtemp
circuit
CORRECTIVE
circuit
in
adjustment
ACTION
Replace
indicator.
Replace
indicator.
ALTIMETER
Pointer indicates
(altimeter).
incorrectly
Leak in static line. Static vent
Defective
plugged.
instrument.
ENGINE
Low reading
Sluggish
on indicator.
OIL TEMPERATURE/PRESSURE
Obstructed
reading.
Inaccurate
indicator.
Sluggish
line and/or fitting.
Sludge in pressure
ENGINE
Low reading
on indicator.
Obstructed
or sticking
Defective
reading.
NOTE
-
Instruments
must be tested
and
repaired
at an authorized
repair
station.
Disassembly
of an
instrument
is not recommended,
or clean
line
and/or
or clean
line
and/or
TORQUEMETER
line and/or fitting.
Replace
fitting.
Replace
indicator.
indicator.
Bleed line.
line.
except
station.
MAINTENANCE
Replace
fitting.
Bleed line.
line.
Sludge in pressure
95-3.
INSTRUMENTS
PRACTICES.
Repair as necessary.
at an
authorized
repair
Removal,
cleaning,
inspection,
and
installation
procedures for all instruments
is
basically
the same. Therefore,
a single
removal and installation
procedure
will be
used for all instruments.
95-4.
1.
REMOVAL
-
INSTRUMENTS.
Ensure battery switch is OFF.
95-00-00
Page 7
BHT-206L1-MM-10
VIEW A
VIEW C
VIEW B
A2
A1
3
A
ENGINE
OVSP
TEST
VIEW
NOTES
A1
Effective helicopters
S/N 45154 thru 45728.
2
Effective helicopters
S/N 45729 and subsequent.
Effective helicopters
S/N 45154 thru 45790.
Figure
95-00-00
Page 8
95-l.
Instrument
panel
206L1-M-95-1
206-075-276R
BHT-206L1-MM-10
2. Disengage
glareshield
that
instrument panel.
three
attach
studs
forward
console
shroud
3.
Disengage
six studs
that
instrument panel to console structure.
of
to
attach
95-7.
INSTRUMENT
PANEL
MAINTENANCE
PRACTICES.
PROTECT
INSTRUMENTS
FROM
FRONTAL
DAMAGE
AND WIRES
AND
TUBES
FROM
BEING
TWISTED
AND STRAINED
WHEN
TILTING
INSTRUMENT
PANEL
AFT.
4.
Tilt instrument
panel aft.
6. Remove screws that attach instrument
instrument panel and remove instrument.
INSPECTION
1. Inspect
glass.
2.
95-6.
1.
-
Disconnect
glareshield
that
instrument panel.
three
attach
instrument
panel.
studs
forward
console
shroud
of
to
attach
3. Tilt instrument
panel aft and
instruments (paragraph 95-4).
remove
4. Disconnect
instrument panel.
electrical
harness
from
5. Remove hinge pin at bottom of instrument
panel and remove panel.
for loose or cracked
-
INSTRUMENT
of range markings.
is mounted
-
properly
in
1. Align hinge halves on instrument
panel
and console structure. Insert hinge pin.
2. Clamp
panel.
INSTRUMENTS.
electrical
harness
to instrument
battery switch is OFF.
3.
2. Position instrument
in instrument
and install mounting screws.
-
INSTRUMENT
2. Disconnect
six studs
that
instrument panel to console structure.
95-9.
INSTALLATION
PANEL.
INSTALLATION
Ensure
to
INSTRUMENTS.
instruments
Check legibility
3. Check
instrument
-
95-8.
REMOVAL
PANEL.
1.
5. Disconnect
electrical connector or tubes
from back of instrument.
Place protective
cover on connectors, tubes, and openings into
instrument.
95-5.
5. Tighten three studs forward of glareshield
that attach console
shroud to instrument
panel.
Install instruments
(paragraph
95-6).
panel
3. Remove protective
cover and connect
electrical connectors or tubes to instrument.
4. Close instrument
panel and tighten six
studs that attach instrument panel to console
structure.
4. Close instrument
panel and tighten six
studs that attach instrument panel to console
structure.
5. Tighten three studs forward of glareshield
that attach console
shroud to instrument
panel.
95-00-00
Page 9
BHT-206L1-MM-10
FLIGHT INSTRUMENTS
95-10.
FLIGHT
air to blow lines clear of any obstructions
or moisture.
INSTRUMENTS.
Flight instrument
system includes pitot-static
system
and airspeed,
altimeter,
and
inclinometer
indicators.
Refer to paragraph
95-3 for instrument
removal, inspection,
and
installation procedures.
95-11.
PITOT-STATIC
1.
REMOVAL
PORTS.
-
95-14.
INSPECTION
SYSTEM.
-
and
connect
PITOT-STATIC
SYSTEM.
Pitot tube (1, figure 95-2) is mounted on a
support located in most forward part of cabin
nose bubble just right of helicopter centerline.
This tube supplies
impact air to airspeed
indicator.
Static air pressure for instrument
operation
is obtained from two static ports.
Ports are located on aft edge of left and right
lower plastic panels of cabin nose bubble.
95-12.
STATIC
2. Reinstall
drain
plugs
pressure and static lines.
and/
PITOT
TUBE
AND
1.
Inspect all lines and fittings.
2. Visually check lines for chafing,
and damage.
3.
mounting,
Inspect pitot tube and static ports.
95-15.
INSTALLATION
AND STATIC
PORTS.
-
PITOT
TUBE
Position pitot head sleeve on pitot head.
Remove cover from wire ends, and connect
electrical wiring to pitot head.
1.
Ensure all electrical
power is OFF.
2. Remove
screws
and lockwashers
attaching pitot head sleeve to pitot head and
pitot tube support.
2. Remove caps or covers from openings in
pitot head and pressure
line and connect
pressure line to pitot head.
3. Hold pitot head and slide sleeve forward
until coupling
in pitot pressure
line is
exposed. Disconnect pressure line and cap or
cover opening in line and in pitot head.
3. Align holes in pitot head sleeve with holes
in pitot head and in pitot tube support and
install attaching lockwashers and screws.
electrical
wiring, if existing,
4. Disconnect
and cover wire ends. Remove pitot head and
sleeve from helicopter.
Disconnect
static
line
5.
Disconnect tee from static port.
from
6. Remove nut and washer from static
and remove static port and baffle.
tee.
port
4. Install
washer.
static port and baffle with nut and
5. Connect
to tee.
tee to static port and static
95-16.
TESTING
SYSTEM.
SPECIAL
95-13.
CLEANING
SYSTEM.
-
Page 10
PITOT-STATIC
TEST
EQUIPMENT
PITOT-STATIC
1. Remove drain plugs and allow moisture to
drain out. Disconnect pressure and static line
from instruments and use filtered compressed
95-00-00
-
TYPE
OR MODEL
MB-1 (Tactair)
equivalent
or
NOMENCLATURE
Static Field Tester
line
BHT-206L1-MM-10
NOTE
Altitude and airspeed indicators are
functionally
tested during following
procedures, in addition to pitot-static
system.
Refer to step 14 in this
paragraph if test set is not available.
airspeed
airspeed
VALVES
ON TEST
SET ARE
SENSITIVE
AND SHOULD
BE
OPERATED
SLOWLY AND WITH
CARE
TO AVOID
POSSIBLE
DAMAGE
TO INSTRUMENTS.
INSTRUMENTS
ARE
EASILY
DAMAGED
BY IMPROPER
MANIPULATION
OF VALVES ON
TEST SET.
Connect
Tactair
MB-l,
or equivalent,
pitot-static system field test set hoses to pitot
and static connections
on test set. Connect
appropriate hoses to pitot tube and one static
port on helicopter. Seal remaining static port
on helicopter
with tape. Check connections
for tightness.
1.
2. Open both vent valves
in lines to equalize. Close
test set.
to allow pressure
all five valves on
3. Set barometric
pressure
dials
on
helicopter and test set altimeter indicators to
barometric pressure at test site, if known, or
to 29.92
inches
Hg. Check
helicopter
altimeter
reads same as test set altimeter
within ±20 feet. If readings
do not agree,
perform one of the following adjustments:
.
.
indicators
and check helicopter
indicator reads 120 ± 4 knots.
6. Close
pressure
source
valve
with
helicopter airspeed indicator reading 120 f 4
knots.
After 5 minutes,
check airspeed
indication
has not dropped
more than 10
knots.
7. Slowly open pressure vent valve. Check
airspeed
indication
returns
to indicator’s
minimum limit.
a. When 29.92 inches Hg is set, adjust
helicopter altimeter to test set altimeter.
b. When ambient pressure is set, adjust
helicopter altimeter to actual test site altitude,
if known. If not known, set altimeter to agree
with test set.
4. Pressurize pressure tank on test set until
sufficient
pressure
for test is indicated
on
pressure dial (approximately
50 inches Hg or
I 170 kPa).
NOTE
Pressure in tank may be replenished
as required for test.
5. Open pressure vent valve approximately
1/4 turn. Slowly open pressure source valve.
Close pressure vent valve. Leave pressure
source valve open until airspeed indicator on
test set reads 120 knots, then close pressure
source
valve.
Maintain
this -pressure
by
manipulation
of pressure
source valve as
required. Gently tap on helicopter and test set
NEVER
BREAK
A LINE
OR
REMOVE
A FITTING
TO VENT
DAMAGE
TO
SYSTEM.
INSTRUMENTS
MAY OCCUR.
6. Pump vacuum side until approximately
20
inches Hg (68 kPa) is indicated on vacuum 1
dial.
9. Slowly open vacuum source valve. Check
both altimeter and airspeed indicator readings
increase.
Slowly bring airspeed to approximately
120 knots and close vacuum source valve
and pressure vent valve. Hold airspeed at 120
knots and increase
altitude
indications
by
manipulation
of cross bleed and vacuum
source valves. Tap gently on helicopter and
test set altimeter and check loss in altitude
does not exceed 100 feet in 1 minute.
10.
95-00-00
Page 11
BHT-206L1-MM-10
1.
2.
3.
4.
5.
6.
7.
6.
9.
10.
11.
12.
13.
14.
15.
16.
13
Altimeter
Airspeed indicator
Torque meter
Engine oil indicator
Transmission oil pressure disconnect
Engine oil pressure disconnect
Torque pressure disconnect
Transmission oil indicator
Static port tee
Static port
Switch - transmission oil
Tee
Pitot tube
Pitot tube disconnect
Static port
Static port tee
206Ll-M-95-2
Figure
95-00-00
Page 12
95-2.
Instrument
piping
installation
BHT-206Ll
-MM-l 0
11.
Slowly decrease vacuum until test set
altimeter
reads 1000 feet. Maintain
this
reading by manipulation
of vacuum source
valve as required. Gently tap on test set and
helicopter
altimeter
and check helicopter
indicator
reads within ± 20 feet of test set
indicator.
provides
an airspeed
reading in miles per
hour by measuring difference between impact
air pressure from pitot tube and static air
pressure from static ports. Refer to paragraph
95-11 for specific maintenance
and testing of
pitot-static system.
12. Slowly open vacuum vent valve and
observe
helicopter
and test set altimeter
return to approximate ground level readings.
Altimeter furnishes direct reading of helicopter
height in feet above sea level. This indicator
is connected
to static air system to sense
atmospheric pressure. An external adjustment
knob is provided
to make adjustments
for
variations
of prevailing
barometric
pressure.
Refer to paragraph
95-11
for specific
maintenance
and testing
of pitot-static
system.
13. Open pressure and vacuum vent valves.
After system pressures are equalized, remove
test set from helicopter. Remove seal placed
on static port.
95-18.
95-19.
14. An alternate
method
pressure line is as follows:
of checking
pitot
a. With the system
installed,
apply
regulated air pressure to pitot intake. When
airspeed
indicator
shows
a reading
of
between 50 and 100 mph, close off pressure
line.
ALTIMETER.
INCLINOMETER.
Inclinometer
consists of a curved glass tube,
ball, and dampening fluid. The ball indicates
when helicopter
is in directional
balance,
either in a turn or straight and level flight. If
helicopter is yawing or slipping, ball will move
off center.
Tap lightly
on panel near indicator
watching for a drop in reading which would
indicate leakage. If reading drops more than
5 mph in 1 minute, check line connections,
correct leakage, and repeat test.
b.
95-17.
AIRSPEED
Airspeed indicator
instrument.
This
INDICATOR.
is a standard
single
scale
pitot-static
indicator
95-00-00
Page 13/14
BHT-206L1-MM-10
NAVIGATION
95-20.
NAVIGATION
Navigation
standby
paragraph
inspection,
4. Start helicopter
standard procedures.
INSTRUMENTS.
instrument
consists
of the pilot
magnetic
compass.
Refer
to
95-3 for instrument
removal,
and installation procedures.
95-21. STANDBY
COMPASS.
MAGNETIC
Magnetic
compass
is a standard,
nonstabilized,
magnetic type instrument mounted
on a support attached to right side of forward
cabin. Compass is used in conjunction with a
compass
correction
card located
below
compass.
95-22.
CALIBRATION
MAGNETIC
COMPASS.
-
STANDBY
Check
compass
for excessive
card
oscillation,
card element
not level,
and
sluggish card before positioning helicopter on
compass rose.
1.
2. Position
helicopter
on compass
rose.
Observe the following
precautions
prior to
start
of compass
compensation
test
procedures.
a. Ensure
all magnetic
material
and
equipment in helicopter is secured in normal
flight position.
b.
Ensure
controls
normal flight position.
and
levers
INSTRUMENTS
are
in
C.
Ensure personnel near or in helicopter
have no magnetic material on their person.
d. Ensure all magnetic objects, such as
trucks,
automobiles,
or other aircraft,
are
moved from compass rose area.
3. Secure
helicopter
right-hand
skid to
compass rose holding fixture. Use helicopter
ground
handling
wheels
or equivalent
to
support helicopter when rotating to different
headings.
engine
according
to
5. Turn power on to all equipment,
except
landing lights. Allow approximately
3 minutes
for equipment to stabilize.
6. Set E-W and N-S adjustment screws on
standby
compass
to zero position.
Zero
position is when dot of screw is aligned with
dot of frame.
NOTE
Attempt
to place
helicopter
in
simulated
flight
condition
while
swinging compass.
7. Swing
helicopter
to magnetic
north
heading. Adjust N-S adjustment
screw until
compass reads exactly north.
6. Swing
helicopter
to magnetic
east
heading. Adjust E-W adjustment
screw until
compass reads exactly east.
to magnetic
south
9. Swing helicopter
heading and note resulting error. Adjust N-S
adjustment screw to remove one-half of error.
Swing helicopter
to magnetic
west
10.
heading and note resulting error. Adjust E-W
adjustment screw to remove one-half of error.
NOTE
Maximum
deviation
on cardinal
headings
shall
not exceed
f 2
degrees. Maximum deviation on 30degree headings shall not exceed +
5 degrees.
11. Swing helicopter in successive magnetic
30-degree headings and record all errors on
compass correction card.
95-00-00
Page 15/16
BHT-206L1-MM-10
PROPULSION
95-23.
PROPULSION
INSTRUMENTS.
Propulsion
instruments
installed
consist of
dual tachometer,
gas producer tachometer,
engine oil temperature/pressure,
transmission
oil temperature/pressure,
fuel quantity,
fuel
pressure
half of fuel pressure/loadmeter,
engine
torquemeter,
and turbine
outlet
temperature
indicators.
Refer to paragraph
removal,
inspection,
procedures.
95-24.
95-3 for instrument
and installation
3. Disconnect
electrical connector
(1G2P1)
from turbine
tachometer
generator
and
connect to matching receptacle on test set.
Check that the turbine rpm pointer on the
rotor and turbine rpm tachometer
indicator
reads upscale and at approximate
rpm of the
tachometer generator.
4. Disconnect
electrical connector
(1G2P1)
from the test set and reconnect
to turbine
tachometer generator.
95-26.
DUAL TACHOMETER.
Dual tachometer,
reading
in percent,
furnishes
both rotor rpm and power turbine
rpm information.
This instrument
is powered
by rotor tachometer
and power turbine
tachometer
generators.
Generators
are selfgenerating and are not connected to electrical
system.
Normal operation
of helicopter
is
when rotor rpm and power turbine
rpm
indicator
needles are synchronized
and in
green arc.
95-25.
OPERATIONAL
TACHOMETER.
INSTRUMENTS
CHECK
-
DUAL
I
TYPE
I
H337
OR MODEL
TEST
EQUIPMENT
NOMENCLATURE
Howell
Engine
Set or Alternate
Test
I.
Disconnect
electrical
connector
(1G3P1)
from rotor tachometer generator and connect
to matching receptacle on test set. Energize
test set tachometer
generator.
Check that
rotor rpm pointer and turbine rpm tachometer
indicator
read upscale at the approximate
speed that test set generator is turning.
2. Disconnect
electrical
connector
from test set and reconnect
tachometer generator.
(1G3P1)
to rotor
TACHOMETER.
Gas producer tachometer, reading in percent,
furnishes gas producer rpm information. This
instrument
is powered
by gas producer
tachometer
generator.
Generator
is selfgenerating and is not connected to electrical
system.
OPERATIONAL
CHECK
95-27.
PRODUCER
TACHOMETER.
SPECIAL
TYPE
H337
SPECIAL
GAS PRODUCER
OR MODEL
TEST
-
GAS
EQUIPMENT
NOMENCLATURE
Howell
Engine
Set or Alternate
Test
I.
Disconnect
electrical connector
(1G1P1)
from gas producer tachometer generator and
connect to matching receptacle on test set.
Check gas producer indicator reads upscale
and reads approximate
rpm of tachometer
generator.
2. Disconnect
electrical connector
(1G1P1)
from test set and reconnect to gas producer
tachometer generator.
95-28.
ENGINE OIL TEMPERATURE/
PRESSURE INDICATOR.
Engine oil temperature/pressure
indicator
dual instrument
providing
temperature
is a
and
95-00-00
Page I7
BHT-206L1-MM-10
pressure
indications.
Temperature
side of
instrument
is part of a bridge circuit with
resistor element of temperature
bulb located
in engine
oil tank. Indicates
engine
oil
temperature
in degrees centigrade.
Indicator
and temperature bulb are matched electrically
in bridge circuit and do not require calibration.
Pressure side of instrument is precalibrated
in
pounds per square inch and is included in a
piping installation
which provides direct (wet
line) readings
to indicator.
Calibration
of
system
is not required
on installation.
Bleeding of pressure gage lines is required if
air is allowed to enter the pressure lines.
96-29.
OPERATIONAL
CHECK
OIL TEMPERATURE/PRESSURE
INDICATOR.
-
1. Close
breaker.
IND
ENG/XMSN
2. Check
indicator
ambient temperature.
TEMP
reads
95-30.
BLEEDING
PRESSURE
- ENGINE
OIL TEMPERATURE/
PRESSURE
INDICATOR.
ENGINE
circuit
approximate
GAGE
LINE
Disconnect
pressure gage line at engine
inlet and place end of line in a receptacle so
end will be covered by accumulated fluid in
receptacle. Station an observer at receptacle
to observe when a bubble free flow has been
established.
1.
2. Remove mounting
screws; carefully
tilt
instrument panel aft. Protect instruments from
frontal damage, and wiring and tubes behind
panel
from being
twisted:
or strained.
Disconnect
pressure gage line at instrument
and connect a low pressure filler gun, filled
with engine oil (Chapter
12), to gage line.
Apply pressure slowly to displace fluid in line.
Continue to force engine oil into line until a
steady flow is established at aft end.
3. When bleeding
has been satisfactorily
completed,
remove filler gun arid-. connect
gage line to instrument.
Take precaution to
hold fluid loss to a minimum while connecting
line. Carefully close instrument panel, taking
care that wiring and tubes behind panel stow
95-00-00
Page 16
without twisting or interference. Secure panel.
Connect aft end of gage line at engine.
95-31.
TRANSMlSSlON
OIL
TEMPERATURE/PRESSURE
INDICATOR.
The transmission
oil temperature/pressure
indicator
is a. dual instrument
providing
temperature
and pressure
indications.
The
temperature side of the instrument
is part of a
bridge
circuit
with resistor
element
of
temperature bulb located in oil filter head and
indicates
transmission
oil temperature
in
degrees
centigrade.
Indicator
and
temperature
bulbs are matched electrically
in
bridge circuit and do not require calibration.
Pressure side of instrument is precalibrated
in
pounds per square inch and is included in a
piping installation
which provides direct -(wet
line) readings
to indicator.
Calibration
of
system
is not required
with installation.
Bleeding of pressure gage
lines is required if
air is allowed to enter pressure lines.
95-32.
OPERATlONAL
CHECK TRANSMISSION
OIL TEMPERATURE/
PRESSURE
INDICATOR.
1. Close
breaker.
ENG/XMSN
2. Check
indicator
ambient temperature.
TEMP IND
reads
circuit
approximate
95-33.
BLEEDING
PRESSURE
GAGE
- TRANSMISSION
OIL TEMPERATURE/
PRESSURE
INDICATOR.
LINE
1.
Disconnect
pressure
gage
line at
transmission
and place end of line in a
receptacle
so that end will be covered by
accumulated
fluid in receptacle.
Station an
observer at the receptacle to observe when a
bubble free -flow has been established.
2. Remove mounting
screws; carefully
tilt
instrument
panel aft as necessary.
Protect
instruments
from frontal damage, and wiring
and tubes behind panel from being twisted or
strained. Disconnect pressure gage line at the
instrument and connect a low pressure filler
gun, filled with-transmission
oil (Chapter 12),
to gage line. Apply
pressure
slowly
to
-
BHT-206L1-MM-10
.
,
displace fluid in line. Continue to force oil into
line until a steady flow is established
at the
aft end.
3. When bleeding
has been satisfactorily
completed,
remove filler gun and connect
gage line to instrument.
Take precaution
to
hold fluid loss to a minimum while connecting
line. Carefully close instrument panel, taking
care that wiring and tubes behind panel stow
without twisting or interference.
Secure panel.
Connect aft end of gage line at transmission.
95-34.
Fuel
fuel
part
units
FUEL QUANTITY
INDICATOR.
quantity indicator provides readings of
supply quantity
in pounds. Indicator
is
of a bridge circuit which includes tank
and three float elements.
95-35.
FUEL PRESSURE
Fuel pressure indicator, located in instrument
panel is a dual indicator
with loadmeter
indicator. Electrical circuitry is provided from
fuel pressure transmitter to indicator. Indicator
is precalibrated
in pounds per square inch
and requires no calibration when installed.
95-36.
OPERATIONAL
PRESSURE
INDICATOR.
CHECK
Fuel pressure transducer
passenger door.
is located aft of right
1. Remove fuel
fuel compartment.
pressure
FUEL
transducer
95-38.
OPERATIONAL
TORQUEMETER.
CHECK
-
from
2. Connect
transducer
to regulated
air
pressure
source
and reinstall
electrical
connector on transducer.
3. With electrical power turned on (28 Vdc
from battery or APU), slowly increase
air
pressure to a maximum of 30 psi (207 kPa).
Fuel pressure indicator should indicate same
as source pressure ± 3 psi (20.7 kPa).
95-37.
ENGINE TORQUEMETER.
Engine
panel,
torquemeter,
located in instrument
is precalibrated
in percent.
This
ENGINE
1.
Disconnect
torque pressure
line from
engine,
and attach pressure
hand gun to
torque pressure line.
2. Apply 57 to 59 psig (393 to 407 kPa)
pressure. Check torquemeter
reads 100 ± 2
percent.
95-39.
BLEEDING
- ENGINE
TORQUEMETER
GAGE PRESSURE
INDICATOR.
-
instrument
is included
in piping circuit to
lower firewall disconnect
which continues to
engine accessory drive gearbox (forward side
of engine). No calibration
of torquemeter
is
required when installed.
See paragraph
95-30 for bleeding
95-40.
TURBINE
INDICATOR.
OUTLET
LINE.
procedure.
TEMPERATURE
Turbine outlet temperature
(TOT) indicator is
a part of turbine outlet temperature
system
which includes indicator, related wiring, and
engine associated
components.
Indicator
receives
temperature
indications
from
bayonet
type thermocouples
mounted
in
turbine exhaust outlet. Indicator is graduated
in degrees Celsius and electrical
power is
supplied from 28 Vdc bus through TOT circuit
breaker.
Effective
on helicopters
S/N 45729 and
subsequent,
and helicopters
incorporating
Technical Bulletin 206L-86-133,
a red warning I
light is incorporated on face of TOT indicator.
Light will illuminate
if red line temperature
(810 degrees)
is exceeded
for more than
10(+2, -0) seconds. It will remain illuminated
until power is removed
from indicator
or
circuit is reset with TOT OVERTEMP LIGHT
reset switch. If circuit is not reset, light will
illuminate
any time power is applied
to
indicator.
95-00-00
Page 19
BHT-206L1-MM-10
95-41.
OUTLET
MAINTENANCE
TEMPERATURE
-
TURBINE
INDICATOR.
SPECIAL
TYPE
Refer to paragraph 95-3 for maintenance
turbine outlet temperature
indicator.
of
95-42.
OPERATIONAL
CHECK TURBINE
OUTLET
TEMPERATURE
INDICATOR
AND CIRCUITRY.
If electrical power is removed from
TOT indicator, OFF flag will appear
and pointer will remain at its last
reading. For example: if last reading
was 500°C when electrical
power
was removed, pointer will continue
to read 500°C until electrical power
is reapplied.
If temperature
has
dropped to 30°C, pointer will motor
down to read 30°C when power is
reapplied.
This is not sticking,
but
normal
indicator
operation.
If
thermocouple
leads are opened
while electrical
power is applied
indicator pointer will spin or motor.
This,
also,
is normal
indicator
operation.
thermocouple
loop
resistance
Disconnect
electrical
connector
(1M4P1)
from back of TURB OUT TEMP
(TOT) indicator.
Measure resistance
across
terminals
on thermocouple
terminal
board
(1TB1) located in engine compartment.
Check
resistance of engine thermocouple
loop is 1.0
± 0.50 ohms.
b.
Measure
resistance
between
pins D
and E of connector
(1M4P1).
Resistance
readings shall be between 5 and 20 ohms.
Reconnect
(1M4P1).
2.
TOT
TOT system functional
95-00-00
Page 20
electrical
check:
OR MODEL
Barfield
Type 2312G
EQUIPMENT
NOMENCLATURE
Turbine
Temperature
Test Set
a. Set FUNCTION switch on tester to IND
mode. Adjust test set meter for ambient
temperature variations, if required.
NOTE
1.
Engine
check:
TEST
connector
b.
Remove wire (E7A-AL) from terminal
board (1TB1). Connect black lead from test
set to terminal of wire (E7A-AL). Connect red
wire from test set to wire (ESA-CR)
on
terminal board (1TB1).
c. Close TOT IND circuit breaker (1CB10).
Press and hold TEST switch on test set while
positioning
CAL/ADJUST
knob to 738
degrees on the dial. Pointer on TOT indicator
should indicate 738 ± 5 degrees (low end of
yellow range mark).
NOTE
On helicopters
S/N 45729
and
subsequent
and helicopters
incorporating
Technical
Bulletin
206L-88-133,
if TOT indicator
pointer indicates above red line (810
degrees) for more than 10(+2, -0)
seconds, red TOT overtemperature
warning light on face of indicator will
illuminate.
I
d.
Press and hold TEST switch while
positioning
CAL ADJUST
knob to 810
degrees on dial. TOT indicator
pointer will
indicate 810 ± 5 degrees (high end of yellow
range mark and leading edge of red line).
e. On helicopters
S/N 45729
and
subsequent
and helicopters
incorporating
Technical
Bulletin
206L-86-133,
perform
following check of TOT warning light circuit:
(1)
If red over-temperature
warning light
did not illuminate in preceding step, press and
hold TEST switch on test set; and adjust CAL/
ADJUST knob to a setting slightly above 810
degrees (approximately
812 to 815 degrees).
I
I
BHT-206Ll
Red warning
illuminated.
light shall illuminate
and remain
(2) Press and hold TEST switch and
position
CAL/ADJUST
knob below
810
degrees (800 degrees for example). Red TOT
warning light shall remain illuminated.
(3)
warning
Reset TOT circuit
breaker.
Red
light should go out when power is
removed
restored.
but illuminate
again
when
-MM-l 0
power
is
(4) Reset TOT warning light circuit by
positioning
TOT LT TEST switch to RESET.
Red TOT warning light shall go out.
f.
Open
TOT IND circuit
breaker.
Disconnect test set leads and reconnect wire
(E7A-AL) to terminal board (1TB1).
95-00-00
Page 21122
BHT-206L1-MM-10
MISCELLANEOUS
95-43.
MISCELLANEOUS
INSTRUMENTS.
Miscellaneous
instruments installed consist of
DC loadmeter, engine hourmeter, 8-day clock,
and free air temperature
indicator.
Refer to
paragraph
95-3 for instruments
removal,
inspection and installation procedure.
95-44.
DC LOADMETER.
DC loadmeter measures and indicates output
of generator in percentage. Indicator is a dual
instrument
providing
loadmeter
and fuel
pressure indications.
95-45.
ENGINE
HOURMETER.
Engine
hourmeter
is mounted
in
compartment
aft bulkhead.
Hourmeter
mechanism
is calibrated
in hours
registers engine operating hours.
95-46.
OPERATIONAL
HOURMETER.
CHECK -
nose
clock
and
one hour. A control
knob on case starts
pointers when pressed, stops both pointers
when pressed a second time, and returns
both pointers when pressed a third time. A
second control knob winds and sets the clock.
95-48.
FREE AIR TEMPERATURE
INDICATOR.
Free air temperature
indicator is windshield
mounted at top of right windshield just to right
of center post. The probe portion is exposed
to outside temperatures
through windshield
and is protected by a sunshield. The indicator
provides
a direct
reading
of outside
air
temperature
in degrees
Fahrenheit
and
Celsius.
95-49.
MAINTENANCE
- FREE
TEMPERATURE
INDICATOR.
1. Remove
follows:
free air temperature
AIR
indicator
as
ENGINE
1. Close
HOURMETER
circuit
breaker.
Check “power on” indicator on hourmeter is
not moving.
2. Close CAUTION LIGHTS circuit breaker.
Check “power on” indicator on hourmeter is
not moving.
3. Temporarily,
disconnect
electrical
connector
(4S1P1) from engine out sensor.
Check that “power on” indicator is moving.
4. Reconnect
electrical
connector
(4S1P1)
to the engine out sensor. Check that “power
on” indicator is not moving.
95-47.
INSTRUMENTS
CLOCK.
The clock is an 8-day, wind-up clock with
added stop-watch feature for elapsed time. It
has a sweep-second
pointer and a minute
totalizer hand to indicate elapsed time up to
a. Unscrew and remove sunshield, dished
washer, and one case washer from outside of
windshield.
Remove
indicator
and
b.
washer from inside of windshield.
other
2. Inspect
follows:
indicator
a.
leaking
free air temperature
Inspect
seals,
indicator
case
for discoloration
as
and
b. Check mounting
and that reading
agrees with a standard indicator known to be
correct.
3. Install
follows:
free air temperature
indicator
as
Place case washer
over probe of
a.
thermometer
with flat side of washer next to
indicator case. Insert probe through mounting
hole from inside windshield.
95-00-00
Page 23
BHT-206L1-MM-10
b. Place other case washer, flat side out,
on probe outside windshield.
Seat washer
shoulders
in mounting
hole. Install dished
washer, with outside edge curving toward
windshield.
Position indicator scale correctly
before tightening.
95-00-00
Page 24
C.
Place sunshield
securely.
over probe and tighten
BHT-206L1-MM-10
CHAPTER
CONTENTS
Paragraph
Number
96-1
96-2
96-3
96-4
96-5
96-6
96-7
96-8
96-9
96-10
96-11
--
96-12
96-13
96-14
96-15
96-16
96-17
96-18
96-19
96 -
ELECTRICAL
MAINTENANCE
SYSTEM
PROCEDURES
Title
Electrical systems ................................
Equipment list ....................................
Starter/generator/igniter
systems troubleshooting
...................................
Lighting system - troubleshooting
...............
Electrical power loading ..........................
Electrical power - DC ...........................
External electrical power .........................
Wiring ............................................
Miscellaneous
electrical components .............
Removal - miscellaneous
electrical
components ....................................
Installation - miscellaneous
electrical
components..
..................................
Inspection - miscellaneous
electrical
components..
..................................
Control panels - electrical .......................
Removal - control panels .....................
Inspection - control panels ....................
Installation - control panels ...................
Circuit breakers ...................................
Removal - circuit breakers ....................
Installation - circuit breakers ..................
Chapter/Section
Number
Page
Number
96-00-00
96-00-00
7
7
96-00-00
96-00-00
96-00-00
96-00-00
9600-00
96-00-00
96-00-00
15
16
17
18
18
18
18
96-00-00
19
96-00-00
19
96-00-00
96-00-00
96-00-00
96-00-00
9600-00
96-00-00
96-00-00
96-00-00
19
19
19
20
20
20
20
20
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
23
23
23
23
23
24
24
24
24
24
24
24
24
24
25
DC POWER SYSTEMS
96-20
96-21
96-22
96-23
96-24
96-25
96-26
96-27
96-28
96-29
96-30
96-31
96-32
96-33
96-34
DC power systems ...............................
Battery system ....................................
Maintenance - battery ........................
Removal -battery
.............................
Installation - battery ..........................
Battery relay ......................................
Removal - battery relay .......................
Installation - battery relay .....................
External power system ...........................
External power receptacle ........................
Removal - external power receptacle .........
Installation - external power receptacle .. . ...
External power relay ..............................
Removal - external power relay ...............
Installation - external power relay ............
96-00-00
Page 1
BHT-206L1-MM-10
CONTENTS
Paragraph
Number
96-35
96-36
96-37,
96-36
96-39
96-40
96-41
96-42
96-43
96-44
96-45
96-46
96-47
96-46
96-49
96-50
96-51
96-52
96-53
96-54
96-55
96-56
96-57
96-56
96-59
96-60
96-61
96-62
96-63
96-64
-
MAINTENANCE
96-00-00
Page 2
(Cont)
Chapter/Section
Number
Title
Generator system .................................
Generator .........................................
Inspection - generator ........................
Voltage regulator..
...............................
Removal - voltage regulator ..................
Inspection and repair - voltage regulator .....
Installation - voltage regulator ................
Adjusting - voltage regulator ..................
Line control relay .................................
Removal - line control relay ..................
Installation - line control relay ................
Generator reset switch ...........................
Removal - generator reset switch .............
Installation - generator reset switch ...........
Generator shunt ..................................
Removal - generator shunt ...................
Installation - generator shunt .................
Starter-igniter
system .............................
Operational check - starter system circuitry . .
Starter ............................................
Starter relay ......................................
Removal - starter relay .......................
Installation - starter relay .....................
Field-igniter
relay .................................
Removal - field-igniter
relay ..................
Installation - field-igniter
relay ................
Igniter ............................................
Starter switch .....................................
Removal - starter switch ......................
Installation - starter switch ....................
DC INDICATOR
96-65
96-66
96-67
96-66
96-69
96-70
96-71
96-72
96-73
96-74
PROCEDURES
Page
Number
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
25
25
25
26
27
27
27
27
27
27
27
27
27
26
26
26
26
26
26
26
29
29
29
29
29
29
29
29
29
30
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
31
31
31
31
31
31
31
SYSTEMS
DC indicator systems .............................
Temperature
bulbs ...............................
Removal - temperature bulbs .................
Installation - temperature bulbs ................
Tachometer generators ...........................
Removal - tachometer generators ............
Installation - tachometer generators ..........
Fuel quantity system .............................
Description - fuel quantity system ............
Calibration procedure - fuel ‘quantity system . .
32
32
32
BHT-206L1-MM-10
CONTENTS
Paragraph
Number
-
MAINTENANCE
96-87
96-88
96-89
96-90
96-91
96-92
96-93
96-94
96-95
96-96
96-97
96-98
96-99
96-100
96-101
96-102
96-103
96-104
96-105
96-106
96-107
96-l 08
96-109
96-110
(Cont)
Chapter/Section
Number
Title
CAUTION
96-75
96-76
96-77
96-78
96-79
96-80
96-81
96-82
96-83
96-84
96-85
96-86
PROCEDURES
AND
WARNING
Page
Number
SYSTEM
Caution and warning system .....................
Caution light panel ...............................
Removal - caution light panel .................
Installation - caution light panel ...............
Operational test - caution light panel .........
Engine out warning system .......................
Operational test - engine out warning system
Engine rpm sensor ...............................
Removal - engine rpm sensor ................
Installation - engine rpm sensor ..............
Low rotor rpm caution system ....................
Operational test - low rotor rpm caution
system .........................................
Rotor rpm sensor .................................
Removal - rotor rpm sensor ..................
Installation - rotor rpm sensor ................
Transmission
oil pressure caution system ........
Operational test - transmission
oil pressure
caution system .................................
Transmission
oil pressure switch .................
Removal - transmission
oil pressure switch ...
Installation - transmission
oil pressure switch
Transmission
oil temperature caution system .....
Operational test - transmission
oil
temperature caution system ....................
Transmission
oil temperature switch ..............
Removal - transmission
oil temperature
switch.. ........................................
Installation - transmission
oil temperature
switch.. ........................................
Battery hot warning system .......................
Operational test - battery hot warning system
Battery relay caution system .....................
Operational test - battery relay caution
system .........................................
Engine chip detector caution system .............
Operational test - engine chip detector
caution system .................................
Transmission
chip detector caution system .......
Operational test - transmission
chip detector
caution system .................................
Tail rotor gearbox chip detector caution system . .
Operational test - tail rotor gearbox chip
detector caution system ........................
Fuel filter caution system .........................
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
35
35
35
35
35
36
36
36
36
36
36
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
37
37
37
37
37
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
38
38
38
38
38
96-00-00
96-00-00
38
38
96-00-00
39
96-00-00
96-00-00
96-00-00
96-00-00
39
39
39
39
96-00-00
96-00-00
39
39
96-00-00
96-00-00
39
40
96-00-00
96-00-00
40
40
96-00-00
96-00-00
40
40
96-00-00
Page 3
BHT-206L1-MM-10
CONTENTS
Paragraph
Number
96-111
96-112
96-113
96-114
96-115
96-116
-
MAINTENANCE
96-124
96-125
96-126
96-127
96-128
96-129
96-130
96-131
96-132
96-133
96-134
96-135
96-136
96-137
96-138
96-139
96-140
96-141
96-142
96-143
96-144
96-145
96-146
96-147
Operational test - fuel filter caution system ...
Fuel pump caution system ........................
Operational test - fuel pump caution system . .
Fuel flow switch ..................................
Fuel low caution system ..........................
Generator failure caution system .................
96-00-00
Page 4
CONTROL
AND
Page
Number
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
SYSTEMS
Lighting Systems .................................
Interior lighting system ...........................
Cockpit light ......................................
Removal - cockpit light and base .............
Installation - cockpit light .....................
Instrument and control panel lighting .............
Operational check - instrument and control
panel lighting ...................................
Cabin lighting .....................................
Exterior lighting system ...........................
Position lights ....................................
Removal - position light .......................
Installation - position light ....................
Removal - tail light ............................
Installation - tail light .........................
Operational check - position lights ............
Anticollision
light ..................................
light ...................
Removal - anticollision
Installation - anticollision
light .................
Operational check - anticollision
light .........
HS strobe power supply (flasher unit) ............
Removal - HS strobe power supply ...........
Installation - HS strobe power supply .........
Landing lights .....................................
Replacement - landing lights ...................
Operational check - landing lights ............
Landing light relays ...............................
Removal - landing light relays ................
Installation - landing light relays ..............
Landing light switch ..............................
Removal - landing light switch ................
Installation - landing light switch ..............
ENGINE
96-148
96-149
(Cont)
Chapter/Section
Number
Title
LIGHTING
96-117
96-118
96-119
96-120
96-121
96-122
96-123
PROCEDURES
ACCESSORIES
Engine control and accessories systems
Fuel boost pumps ................................
.........
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
43
43
44
44
44
44
44
44
44
44
44
44
45
45
45
45
45
45
45
45
45
45
46
46
46
96-00-00
96-00-00
47
47
SYSTEMS
BHT-206L1-MM-10
CONTENTS
Paragraph
Number
96-l 50
96-l 51
96-l 52
96-153
96-154
96-155
96-156
96-157
96-158
96-159
96-160
96-161
96-162
96-163
96-164
96-165
96-166
96-167
96-168
96-169
96-170
96-171
-
MAINTENANCE
Operational check - fuel boost pumps ........
Fuel valve ........................................
Operational check - fuel valve ................
Fuel dump valve ..................................
Operational check - fuel dump valve ..........
Fuel dump switch .................................
Removal - fuel dump switch ..................
Installation - fuel dump switch ................
Fuel valve switch .................................
Removal - fuel valve switch ...................
Installation - fuel valve switch ................
Engine deicing/anti-icing
system ..................
Operational check - engine deicing/anti-icing
system .........................................
Engine deicing/anti-icing
switch ..................
Removal - engine deicing/anti-icing
switch ...
Installation - engine deicing/anti-icing
switch
Governor actuator ................................
Operational check - governor actuator ........
Governor rpm switch .............................
Removal - governor control switch ............
Installation - governor control switch ..........
Particle separator .................................
CONTROL
-
Page
Number
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
47
47
47
48
48
48
48
48
48
48
48
48
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
48
49
49
49
49
49
49
49
49
49
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
96-00-00
51
51
51
51
51
51
96-00-00
96-00-00
96-00-00
53
53
53
SYSTEM
Flight controls system ............................
Operational check - flight controls system ....
Hydraulic bypass solenoid ........................
Removal - hydraulic bypass solenoid .........
Installation - hydraulic bypass solenoid .......
Control boost/hydraulic
system switch ............
MISCELLANEOUS
96-178
96-179
96-180
(Cont)
Chapter/Section
Number
Title
FLIGHT
96-172
96-173
96-174
96-175
96-176
96-177
PROCEDURES
ELECTRICAL
Miscellaneous
electrical system ..................
Defogging blowers ................................
Operational check - defogging blower ........
SYSTEM
96-00-00
Page 5
BHT-206L1-MM-10
FIGURES
Figure
Number
96-1
96-2
96-3
96-4
Title
Equipment location - electrical .............................................
Overhead console panel (typical) ............................................
Starter-generator
brush wear ................................................
.........................................
Transmitter and test set connection
Page
Number
11
21
26
34
TABLES
Table
Number
96-1
96-2
96-3
96-00-00
Page 6
Title
Equipment list - electrical ..................................................
Starter/generator/igniter
systems troubleshooting
chart ......................
............................................
Lighting systems troubleshooting
Page
Number
7
15
16
BHT-206L1-MM-10
ELECTRICAL
96-l.
ELECTRICAL
SYSTEM
Table
SYSTEMS.
Controls
for the electrical
systems are located
on the overhead
console
and instrument
panel. Control,
regulating,
power transfer,
and
malfunction
monitoring
equipment
is located
throughout
the helicopter.
An equipment
list
(table 96-l) is provided
to assist in equipment
identification
and troubleshooting
tables
to
assist with maintenance.
See figure 96-1 for
equipment
location
and Chapter
98 for
individual
systems
wiring diagrams.
EQUIPMENT
LIST.
Table
96-1.
Equipment
list -
NOMENCLATURE
1B1
1B2
1B3
1B4
1B5
1B5P1
1B6
1B8P1
1CB1
1CB2
1CB3
ACTUATOR,
GOV RPM
ACTUATOR,
ENG DEICE
FUEL PUMP, RIGHT
FUEL PUMP, LEFT
FUEL SHUTOFF
VALVE
CONN, FUEL SHUTOFF
VALVE
FUEL PRESS XMTR
CONN, FUEL PRESS XMTR
CIRCUIT
BREAKER,
STARTER
CIRCUIT
BREAKER,
IGNITER
CIRCUIT
BREAKER,
GOV
CONT
CIRCUIT
BREAKER,
ENG
DEICE/ANTI-ICING
CIRCUIT
BREAKER,
FUEL
BOOST RIGHT
CIRCUIT
BREAKER,
FUEL
BOOST LEFT
CIRCUIT
BREAKER,
FUEL
VALVE
1CB4
1CB5
1CB6
1CB7
electrical
1CB8
CIRCUIT
BREAKER,
FUEL
CITY/PRESS
IND
CIRCUIT
BREAKER,
ENG/
XMSN TEMP IND
CIRCUIT
BREAKER,
TURB
OUTLET
TEMP IND
CIRCUIT
BREAKER,
HOURMETER
CIRCUIT
BREAKER,
FUEL
BOOST LEFT EMER
CIRCUIT
BREAKER,
ENGINE
OVERSPEED
CIRCUIT
BREAKER,
ENGINE
PAR SEP PRG
DIODE, STARTER
RELAY
DIODE, HOURMETER
CHIP DETECTOR,
UPPER ENG
CONN
CHIP DETECTOR,
LOWER
ENG
CONN
CHIP DETECTOR,
XMSN
CHIP DETECTOR,
TAIL
ROTOR
CHIP DETECTOR,
XMSN
CHIP DETECTOR,
FREEWHEELING
TACH GEN, GAS PRODUCER
CONN, GAS PRODUCER
TACH
GEN
TACH GEN, PWR TURB
CONN, PWR TURB TACH GEN
TACH GEN, ROTOR
CONN, ROTOR TACH GEN
CONN, ENG FW DISC. NO. 1
CONN, ENG FW DISC. NO. 2
CONN, XMSN DISC
CONN, ENGINE
CONN, ENGINE OVSP SW
RELAY, STARTER
RELAY, HOURMETER
RELAY, W/A LOW FLUID
VALVE, FLUID DUMP
VALVE, W/A SOLENOID
CONN, W/A SOLENOID
VALVE
1CB9
1CB10
1CB13
1CB14
1CR1
1CR4
1E1
1E1P1
1E2
electrical
REF DES
list -
NOMENCLATURE
1CB12
The purpose
of table
98-l
is to provide
maintenance
personnel
with the necessary
information
to correlate
equipment
designator,
equipment
location,
system
wiring diagrams,
and text. Reference
Designators
(Ref Des)
are assigned
to each piece of equipment
and
is common
on system
wiring
diagrams
and
text.
Equipment
(Cont)
REF DES
1CB11
96-2.
96-1.
1E2P1
1E3
1E4
1E5
1E6
1G1
1G1P1
1G2
1G2P1
1G3
1G3P1
1J1
1J2
1J3
1J4
1J5
1K1
1K2
1K5
1L1
1L2
1L2P1
96-00-00
Page 7
BHT-206L1-MM-10
Table
96-1.
Equipment
(Cont)
list -
electrical
Table
96-l.
Equipment
(Cont)
list -
electrical
REF DES
NOMENCLATURE
REF DES
NOMENCLATURE
1M1
1M1P1
1M2
INDICATOR,
FLUID QTY
CONN, FUEL QTY IND
INDICATOR,
ENG OIL PRESS/
TEMP
CONN, ENG OIL PRESS/TEMP
IND
INDICATOR,
XMSN OIL
PRESS/TEMP
CONN, XMSN OIL PRESS/
TEMP IND
INDICATOR,
TURB OUTLET
TEMP
CONN, TURB OUTLET
TEMP
IND
INDICATOR
GAS PRODUCER
TACH
CONN, GAS PRODUCER
TACH
IND
INDICATOR,
DUAL TACH
CONN, DUAL TACH-PWR
TURB
CONN, DUAL TACH-ROTOR
HOURMETER
CONN, ENG FW DISC NO. 1
CONN, ENG FW DISC NO. 2
CONN, XMSN DISC
CONN, ENGINE
CONN, ENGINE
OVSP SW
TEMP BULB, ENG OIL
CONN, ENG OIL TEMP BULB
TEMP BULB, XMSN OIL
CONN, XMSN OIL TEMP BULB
SWITCH,
FUEL DUMP
SWITCH,
XMSN OIL TEMP
SWITCH,
XMSN OIL PRESS
CONN, XMSN OIL PRESS
SWITCH
SWITCH,
FUEL FILTER PRESS
CONN, FUEL FILTER PRESS
SWITCH
SWITCH,
LEFT FUEL FLOW
CONN, LEFT FUEL FLOW
SWITCH
SWITCH,
RIGHT‘ FUEL FLOW
CONN, RIGHT FUEL FLOW
SWITCH
SWITCH,
TEST ENGINE OVSP
1S11
1S12
1S13
1S14
1S14P1
SWITCH,
W/A SYSTEM
SWITCH,
W/A INJECT
SWITCH,
FLOAT
SWITCH,
W/A PRESSURE
CONN, W/A PRESSURE
SWITCH
SWITCH,
DIFF PRESSURE
CONN, DlFF PRESSURE
SWITCH
SWITCH,
FUEL LOW LEVEL
SWITCH,
TOT LIGHT TEST
SWITCH,
TOT OVERTEMP
LIGHT RESET
TERM. BD, TURB OUTLET
TEMP
THERMOCOUPLE,
ENG
IGNITER
XMTR, UPPER FUEL QTY
CONN, UPPER FUEL QTY
XMTR
XMTR, LOWER AFT FUEL QTY
XMTR, LOWER FWD FUEL
QTY
BATTERY
CIRCUIT
BREAKER,
LOADMETER
CIRCUIT
BREAKER,
LOADMETER
CIRCUIT
BREAKER,
GEN
FIELD
CIRCUIT
BREAKER,
GEN
RESET
CIRCUIT
BREAKER,
AUX
RECEPTACLE
DIODE, BATT RLY
DIODE,
BATT RLY
DIODE, EXT PWR
DIODE, LINE CONT
DIODE, LINE CONT
CONN, START-GEN
FW DISC
CONN, EXTERNAL
PWR
RELAY, BATTERY
RELAY, EXTERNAL
PWR
RELAY, LINE CONT
RELAY, FIELD/IGNITER
INDICATOR,
LOADMETER/
FUEL PRESS
1M2P1
1M3
1M3P1
1M4
1M4P1
1M5
1M5P1
1M6
1M6P1
1M6P2
1M7
1P1
1P2
1P3
1P4
1P5
1RT1
1RT1P1
1RT2
1RT2P1
1S2
1S3
1S4
1S4P1
1S5
1S5P1
1S7
1S7P1
1S6
1S6P1
1S10
96-00-00
Page 6
1S15
1S15P1
1S16
1S18
1S19
1TB1
1TC1
1Z1
1Z2
1Z2P1
1Z3
1Z4
2BT1
2CB1
2CB2
2CB3
2CB4
2CB5
2CR1
2CR1
2CR2
2CR3
2CR3
2J1
2J2
2K1
2K2
2K3
2K4
2M1
BHT-206L1-MM-10
Table
96-1.
Equipment
(Cont)
list -
electrical
Table
96-1.
Equipment
(Cont)
list -
electrical
REF DES
NOMENCLATURE
REF DES
NOMENCLATURE
2M1P1
CONN, LOADMETER/FUEL
PRESS IND
STARTER-GENERATOR
CONN, STARTER-GENERATOR
FW
RESISTOR,
LOADMETER
SHUNT
SWITCH,
BATTERY
SWITCH,
GENERATOR
RESET
TERMINAL
BOARD,
PWR DIST
SENSOR
MODULE,
BATTERY
OVERTEMP
CONN, MODULE,
BATTERY
OVERTEMP
SENSOR
MODULE
SWITCH,
BATT. OVRTMP
SENS. MODULE
SWITCH,
BATT. OVRTMP
SENS. MODULE
VOLTAGE
REGULATOR
CONN, VOLTAGE
REGULATOR
SWITCH
BOX, PILOT COLL
SWITCH,
GOV RPM
SWITCH,
LANDING
LIGHT
SWITCH,
STARTER
PANEL, PILOT MISC
LIGHT, PILOT MISC PANEL
LIGHT, PILOT MISC PANEL
SWITCH,
ENG. DEICE/ANTIICING
SWITCH,
CONT BOOST
SWITCH,
CAUTION
LIGHT DIM
SWITCH
ENG PARTICLE
SEPARATOR
PURGE
PANEL, PILOT FUEL CONT.
LIGHT, PILOT FUEL CONT
PANEL
SWITCH,
FUEL VALVE
PANEL, OVERHEAD
CONSOLE
CONN, OVERHEAD
CONSOLE
PANEL
CYCLIC
STICK, PILOT
SWITCH,
PILOT CYCLIC
STICK
BUTTON
SWITCH,
PILOT CYCLIC STICK
TRIGGER
AIRSPEED
LIMITATIONS
PANEL
4A6J1
CONN, AIRSPEED
LIMITATIONS
PANEL
CIRCUIT
BREAKER,
CAUTION
LIGHTS
CIRCUIT
BREAKER,
PITOT
HEATER
CIRCUIT
BREAKER,
DIRECT
GYRO AND ATTITUDE
IND
PANEL, CAUTION
CONN, CAUTION
PANEL
CONN, CAUTION
PANEL
PITOT HEATER
CONN, PITOT HEATER
DISC
RELAY, LOW ROTOR HORN
MUTE
RELAY, ENGINE OUT HORN
MUTE
ALARM,
ENG OUT WARNING
ALARM,
LOW ROTOR RPM
COMPASS,
PILOT
LIGHT, PILOT COMPASS
INCLINOMETER,
PILOT
LIGHT, PILOT INCLINOMETER
INDICATOR,
ATTITUDE
CONN, ATTITUDE
INDICATOR
INDICATOR,
DIRECTION
CONN, DIRECTION
INDICATOR
INDICATOR,
TURN AND SLIP
CONN, TURN AND SLIP
SWITCH,
ENG OUT SENSOR
CONN, ENG OUT SENSOR
SWITCH
SWITCH,
LOW ROTOR RPM
SENSOR
CONN, LOW ROTOR RPM
SENSOR
SWITCH
SWITCH,
LOW RPM COLL
CUTOFF
SWITCH,
CAUTION
LIGHT
TEST
2MG1
2P1
2R1
2S1
2S2
2TB1
2U1
2U1P1
2U1S1
2U1s2
2VR1
2VR1P1
4A1
4A1S1
4A1S2
4A1S3
4A2
4A2DS1
4A2DS2
4A2S1
4A2S2
4A2S3
4A2S4
4A3
4A3DS1
4A3S1
4A4
4A4J1
4A5
4A5S1
4A5S2
4A6
4CB1
4CB2
4CB3
4DS1
4DS1J1
4DS1P1
4HR1
4HR1P1
4K1
4K2
4LS1
4LS2
4M1
4M1DS1
4M2
4M2DS1
4M3
4M3P1
4M4
4M4P1
4M5
4M5P1
4S1
4S1P1
4S2
4S2P1
4s3
4s4
4s5
4TB1
SWITCH,
WARNING
TERMINAL
BOARD,
COLL/CYCLlC
MUTE
PILOT
4TB2
TERMINAL
INST PNL
PILOT
BOARD,
96-00-00
Page 9
BHT-206L1-MM-10
Table
96-l.
Equipment
(Cont)
list -
electrical
Table 96-1.
Equipment
(Cont)
list -
electrical
REF DES
NOMENCLATURE
REF DES
NOMENCLATURE
5A1
5A1S1
CYCLIC
STICK, COPILOT
SWITCH,
COPILOT
CYCLIC
STICK BUTTON
SWITCH,
COPILOT
CYCLIC
STICK TRIGGER
CIRCUIT
BREAKER,
INST
LIGHTS
CIRCUIT
BREAKER,
LANDING
LIGHTS
CIRCUIT
BREAKER,
ANTICOLLISION
LIGHT
CIRCUIT
BREAKER,
POSITION
LIGHTS
CIRCUIT
BREAKER,
COCKPIT
LIGHT
VOLTAGE
REGULATOR,
LIGHT
5V)
LIGHT, FWD SHINING
LANDING
LIGHT, DOWN SHINING
LANDING
LIGHT, ANTICOLLISION
STROBE
CONN, ANTICOLLISION
STROBE
LIGHT
CONN, ANTICOLLISION
STROBE
LIGHT
LIGHT, TAIL POSITION
LIGHT, LEFT POSITION
LIGHT, RIGHT POSITION
LIGHT, COCKPIT
LIGHT, LOWER LH POSITION
LIGHT, LOWER RH POSITION
LIGHT, CABIN
LIGHT, CABIN
LIGHT, CABIN
LIGHT, CABIN
CONN, TAIL FIN DISC
CONN, TAILBOOM
DISC
CONN, TAIL LIGHT DISC
CONN, INSTRUMENT
LIGHT
CONN, CABIN LTS
RELAY, FWD SHINING
LDG LT
RELAY, DOWN SHINING
LDG
LT
RELAY, LIGHT DIMMING
CONN, TAIL FIN DISC
CONN, TAILBOOM
DISC
8P3
8P4
8P5
8PS1
8PS1P1
CONN, TAIL LIGHT DISC
CONN, INSTRUMENT
LIGHT
CONN, CABIN LTS
POWER SUPPLY,
HS STROBE
CONN, HS STROBE
POWER
SUPPLY
TRANSISTOR,
LIGHT DIMMING
TRANSISTOR,
LIGHT DIMMING
RESISTOR,
LIGHT DIMMING
RESISTOR,
LIGHT DIMMING
RESISTOR,
LIGHT DIMMING
SWITCH,
CABIN LT
SWITCH,
CABIN LT
SWITCH,
CABIN LT
SWITCH,
CABIN LT
SWITCH,
PILOTS PASS LT
TERMINAL
BOARD,
INSTRUMENT
LIGHT
TERMINAL
BOARD,
POSITION
LIGHTS
CONTROL,
INSTRUMENT
LIGHT
POTENTIOMETER,
INSTRUMENT
LIGHT
POTENTIOMETER,
INSTRUMENT
LIGHT
SWITCH,
INSTRUMENT
LIGHT
CIRCUIT
BREAKER,
HYDRAULIC
BOOST
SOLENOID,
HYDRAULIC
BYPASS
CONN, HYDRAULIC
BYPASS
SOLENOID
-BLOWER,
LH DEFOG
BLOWER,
RH DEFOG
CIRCUIT
BREAKER,
DEFOG
BLOWER
CIRCUIT
BREAKER,
HEATER
POWER
FILTER,
LH DEFOG BLOWER
FILTER,
RH DEFOG BLOWER
SWITCH,
VENTILATOR
HEAT
SWITCH,
HEATER-START
SWITCH,
UPPER LOCK PIN
SWITCH,
LOWER LOCK PIN
5A1S2
8CB1
8CB2
8CB3
8CB4
8CB5
8CR1
8DS1
8DS2
8DS3
8DS3J1
8DS3P1
8DS4
8DS5
8DS8
8DS7
8DS10
8DS11
8DS13
8DS14
8DS15
8DS16
8J1
8J2
8J3
8J4
8J5
8K1
8K2
8K3
8P1
8P2
96-00-00
Page 10
8Q1
8Q2
8R1
8R2
8R3
8S2
8S3
8S4
8S5
8S6
8TB1
8TB2
8U1
8U1R1
8U1R2
8U1S1
9CB1
9L1
9L1P1
10B1
1082
10CB1
1OCB2
1OFL1
1OFL2
1 OS1
1 OS2
2483
2486
Figure
96-l.
Equipment
location
-
electrical
(Sheet
206L1-M-96-1-1
BHT-206L1-MM-10
1 of 4)
96-00-00
Page 11
SHT-206L1-MM-10
96-00-00
Page 12
Figure
96-1.
Equipment
location
-
electrical
(Sheet
2)
206L1-M-96-1-2
BHT-206L1-MM-10
206L1-M-96-1-3
Figure
96-1.
Equipment
location
-
electrical
(Sheet
3)
96-00-00
Page 13
BHT-206L1-MM-10
VIEW B
206L1-M-96-1-4
Figure
66-00-00
Page 14
96-l.
Equipment
location
-
electrical
(Sheet
4)
BHT-206L1-MM-10
includes typical malfunctions
that may occur
in a helicopter and can be used as a guide.
96-3.
STARTER/GENERATOR/IGNITER
SYSTEMS - TROUBLESHOOTING.
When troubleshooting
starter/generator/igniter
systems,
refer to table 96-2. This table
Table
INDICATION
TROUBLE
96-2.
Starter/generator/igniter
systems
troubleshooting
chart
OF
Starter fails to operate when
start switch is depressed.
PROBABLE
CAUSE
Battery.
Circuit
breaker.
Replace
battery.
Replace
circuit breaker.
Repair as necessary.
Starter relay.
Replace
relay.
External
power relay.
Replace
relay.
Starter
worn.
brushes
Repair as necessary.
excessively
Replace
starter.
Adjust
power.
output
Igniter circuit breaker.
Replace
circuit breaker.
Field/igniter
Replace field/igniter
burned out.
Voltage from
too low.
external
power
relay.
Igniter exciter
No generator output indicated
with electrical
equipment
turned on.
ACTION
Faulty wiring.
Armature
Igniter fails to operate when
starter switch is depressed.
CORRECTIVE
box.
Replace
exciter
Faulty wiring.
Repair wiring.
Voltage
Replace
regulator.
Open generator
Line control
field circuit.
relay.
from
external
relay.
box.
regulator.
Repair as necessary.
Replace
relay.
96-00-00
Page 15
BHT-206L1-MM-10
Table
INDICATION
TROUBLE
96-2.
Starter/generator/igniter
systems
PROBABLE
Defective
CAUSE
CORRECTIVE
circuit breaker.
(Cont)
ACTION
Replace
starter/generator.
Replace
loadmeter.
Replace as necessary.
of
lighting systems, refer
table’ includes
typical
Table
96-3.
Lighting
systems
troubleshooting
OF
PROBABLE
Lights fail to illuminate.
Defective
CAUSE
breaker trip.
CORRECTIVE
wiring.
ACTION
Repair as necessary.
Circuit breaker.
Replace circuit breaker.
Defective
Replace
switch.,
Wires improperly
structure.
bonded
to
Shorted wiring.
switch.
Bond as necessary
to provide
good electrical connection.
Repair as necessary.
Anticollision
light fails to flash
when
circuit
breaker
is
energized.
Defective
supply
Both indicator
and control
panel lights fail to illuminate
when instrument
light control
is rotated clockwise.
8Q1, 8Q2, 8R3, 8U1, circuit
breaker.
Repair as necessary.
Only control
illuminate.
Defective
Replace transistor.
96-00-00
Page 16
-
malfunctions applicable to lighting systems
helicopter and can be used as a guide.
96-4.
LIGHTING SYSTEM TROUBLESHOOTING.
While troubleshooting
to table 96-3. This
winding
loadmeter.
Loadmeter
Circuit
chart
OF
Armature
or field
short circuited.
INDICATION
TROUBLE
troubleshooting
panel
fails
to
H.S. strobe
transistor
power
(8Q2).
Replace
supply-
H.S.
strobe
power
BHT-206L1-MM-10
Table
INDICATION
TROUBLE
96-3.
Lighting
systems
troubleshooting
OF
PROBABLE
CORRECTIVE
CAUSE
8U1 defective.
B rig ht n e s s Ie v e I o f
instrument/light
and/or control
panel lights are inoperative.
Only indicator
illuminate.
lights
fail
to
Instrument/light
control.
-
1.
ELECTRICAL
DC Generator
transistor
Defective
resistor
Defective
transistor
Capacity:
200 Ampere Generator
137 amperes (continuous)
300 amperes (2 minutes)
400 amperes (5 seconds)
2. Basic Helicopter
Operating
battery charging load).
Loads
(8Q1).
(8R3).
(8Q2).
zener
POWER LOADING.
Output-Load
(rheostat)
Defective
Defective
(8CR1).
96-5.
(Cont)
(less
diode
Replace
unit.
Replace
unit.
Replace transistor.
Replace
32.63 amperes
31.27 amperes
31.15 amperes
Take-Off
5 seconds
2 minutes
15 minutes
32.15 amperes
31.26 amperes
31 .I 1 amperes
Cruise
5 seconds
2 minutes
15 minutes
32.15 amperes
31.25 amperes
31 .1 1 amperes
resistor.
Replace transistor.
Replace
diode.
Landing
5 seconds
2 minutes
15 minutes
50.85 amperes
49.95 amperes
37.35 amperes
Emergency
5 seconds
2 minutes
15 minutes
22.65 amperes
21.75 amperes
21.62 amperes
3.
Battery Charging
17 AH Battery
Start and Warm-Up
5 seconds
2 minutes
15 minutes
ACTION
Load:
57.80 to 3.70 amperes
4. Auxiliary
Kits Operating
added equipment).
Heater kit
ECU
Flight instruments*
Auto relight**
Cargo hook**
VHF receiver
VHF transmitter
ADF
Voltage converter
OMNI/ILS Indicator
Loads
(optional
16.70 amperes
39.50 amperes
5.90 amperes
0.50 amperes
14.00 amperes
1.02 amperes
3.10 amperes
1.00 amperes
0.10 amperes
0.20 amperes
96-00-00
Page 17
BHT-206L1-MM-10
Audio panel
Transponder
Pop-out floats**
Rotor brake
1.33
1.30
4.00
0.40
amperes
amperes
amperes
amperes
Avionics kits:***
VHF receiver
VHF transmitter
ADF receiver
Voltage converter
OMNI/ILS indicator
Audio panel
Transponder
1.02
3.10
1.00
0.10
0.20
1.33
1.30
amperes
amperes
amperes
amperes
amperes
amperes
amperes
Avionics kits:****
VHF NAV/COMM
receiver
VHF NAV/COMM
xmtr
OMNI/ILS indicator
Audio panel
Isolation Amp
ADF receiver
Transponder
0.56 amperes
0.20
1.84
1.10
0.59
1.11
amperes
amperes
amperes
amperes
amperes
ELECTRICAL
POWER -
DC.
Helicopter
is equipped with a 28 volt direct
current
electrical
system.
Power for this
system is obtained from a nickel-cadmium,
vented, 24 volt 17 ampere-hour battery and a
200 ampere (derated to 137 amp&es), 30 volt
combination
starter-generator.
Major
components
of dc power system
include
battery, starter-generator,
voltage regulator,
relays, and circuit breaker&
All circuits in
electrical
system
are single
wire with a
common ground return. Negative terminals- of
starter-generator
and battery are grounded to
helicopter structure.
96-7.
EXTERNAL
ELECTRICAL
Page 16
letters
(Example)(E17B20N)
E
Circuit
17
Wire Number
B
Wire Segment
20
Wire Size
N
Ground
WIRING
Function
IDENTIFICATION
C
Control
D
Instrument
Circuits
flight instrument)
E
Engine
H
Heating,
J
Ignition
K
Engine Control
L
Lighting
N
Ground
P
DC Power
Q
Fuel and Oil Circuit
R
Radio-Navigation
W
Warning
CODE
Surface
lnstrument
Ventilating
(Other
than
Circuits
and De-icing
Circuit
Circuit
Circuit
and Emergency
96-9. MISCELLANEOUS
COMPONENTS.
ELECTRICAL
POWER.
External power may be supplied to helicopter
by a receptacle located on lower front section
of helicopter fuselage.
96-00-00
WIRING.
All wires are marked with identification
and numbers:
2.75 amperes
*Includes pitot tube heater.
**Momentary
load only.
***S/N $5154 through 45600
****S/N 45801 and subsequent
96-6.
96-8.
In this category
are relays,
solenoids,
rheostats,
switches, circuit
breakers,
plugs,
leads,
connectors, wiring,
receptacles,
shunts, shock mounts, capacitors,
diodes,
BHT-206L1-MM-10
transistors,
lights.
resistors,
inductors
and
panel
96-l 0. REMOVAL
- MISCELLANEOUS
ELECTRICAL
COMPONENTS.
5.
Inspect
leads
and wiring
for loose
corrosion
damaged
terminals,
chafing,
insulation,
excessive
mechanical
stress,
broken strands, damaged shielding,
shorted
shielding, routing and mounting conditions.
6. Inspect
shunts
for corrosion,
proper
mounting,
scratches,
physical damage and
discoloration
(indicating
excessive
overloading).
BEFORE
ATTEMPTING
TO
REMOVE
ANY
ELECTRICAL
COMPONENT,
DISCONNECT
BATTERY.
1.
Remove attaching
2.
Identify
3.
Remove
7. Inspect
shock mounts
for retention,
proper mounting, cracks, distortion, corrosion
and bonding.
6. Inspect relays and solenoids
for loose
connections,
broken contact pins, damage to
case,
insulation
between
contact
pins,
evidence of corrosion, pits, or discoloration.
hardware.
wires.
component.
9.
Visually
check
diodes
for loose
connections
and broken
leads.
Check
suspected
faulty
diode
front
to back
conductivity
ratio with standard ohmmeter.
96-l 1. INSTALLATION
MISCELLANEOUS
ELECTRICAL
COMPONENTS.
1.
Install
component
and
attaching hardware or clamps.
2. Attach
connectors.
identified
secure
terminals
with
and/or
96-l 2. INSPECTION
- MISCELLANEOUS
ELECTRICAL
COMPONENTS.
Inspect rheostats
for proper mounting,
corrosion,
burned element, damaged wiper,
cracks and correct resistance.
I.
2. Inspect switches
mounting, corrosion,
OFF position.
10. Visually check panel lights for corrosion
and burned elements.
96-13.
CONTROL
ELECTRICAL.
Controls and control panels are mounted
overhead console and instrument panel.
96-14.
REMOVAL
PANELS.
4. Inspect plugs, connectors and receptacles
for proper
mounting,
contact
corrosion,
damaged
contacts,
broken
wires,
faulty
contacts, insert cracks and faulty insulation.
-
in
CONTROL
NOTE
Removal procedure for all panels is
basically the same. A single removal
procedure
may be used for any
panel.
for weak detents, proper
and continuity in ON and
3. Inspect
circuit
breakers
for proper
mounting,
corrosion,
actuation
for circuit
power on and power off and reset retentions.
PANELS -
I.
Disconnect
2.
Ensure all electrical
battery.
power is OFF.
3. Disengage
fasteners
holding
panel
mounting.
Lift panel
from mount
and
disconnect electrical connector.
96-00-00
Page 19
BHT-206L1-MM-10
96-15.
INSPECTION
PANELS.
-
96-16.
REMOVAL
BREAKERS.
CONTROL
1. Visually
inspect for scratched,
broken edge lit panels.
chipped
or
1.
Disconnect
2.
Ensure
INSTALLATION
96-16.
PANELS.
1.
Connect
electrical
2.
Position
panel
3.
Engage
fasteners.
96-17.
CIRCUIT
-
CONTROL
all electrical
4. Disconnect
and cover wire
power
is OFF.
fasteners
assembly.
wiring
ends.
and
to appropriate
5.
Remove
mounting
from panel assembly.
nut
and
96-19.
INSTALLATION
BREAKERS.
-
1. Position
breaker
install mounting
nut.
in panel
Remove
cover
2.
connect to breaker.
from
open
breaker
lift
breaker
CIRCUIT
assembly
and
connector.
in mount.
BREAKERS.
Circuit
breakers
are mounted
on overhead
console.
Circuits can be separated
and closed
by operating
these trip-free,
push-pull
circuit
breakers
(figure
96-2).
See miscellaneous
electrical
components
for additional
maintenance
information.
96-00-00
Page 20
CIRCUIT
battery.
Disengage
3.
appropriate
panel
Visually
inspect
for
loose
wiring
2.
connections,
damaged
or faulty
switches,
damaged
connectors,
and broken or missing
mounting
fasteners.
-
3.
Close
fasteners.
panel
assembly
wire
ends
and
and
engage
BHT-206L1-MM-10
206L1-M-96-2
206-075-013F
Figure
96-2.
Overhead
console
panel
(typical)
96-00-00
Page 21/22
BHT-206L1-MM-10
DC POWER SYSTEMS
96-20.
DC POWER SYSTEMS.
DC power systems consist of battery, external
power, starter/generator,
and starter-igniter
systems. Refer to Chapter 98 for individual
system wiring diagrams.
96-21.
BATTERY
SYSTEM.
Battery system consists of battery, battery
relay, battery switch, and related wiring.
MATERIALS
REQUIRED
NUMBER
NOMENCLATURE
C-237
Varnish,
Resistant,
b. Check battery compartment
is clean
and free from alkaline deposits. If corrosion is
present,
remove
with diluted
boric acid
solution.
Retouch
varnished
surfaces,
if
necessary,
with alkali-resistant
varnish,
(C237).
2. Ensure battery is charged. A fully charged
battery can be determined by moving battery
switch from BAT to OFF and observing effect
on generator
loadmeter.
If change
in
indication is less than 5 amperes, battery is
fully
charged.
No other
maintenance,
servicing,
or inspection
of battery
is
authorized.
NOTE
Alkaline
TT-V-119
Do not service
nickel-cadmium
batteries
while
installed
in the
helicopter.
Remove
battery
and
service, as required, by authorized
battery shop personnel only.
NOTE
For more information on consumable
materials,
refer to BHT-ALL-SPM
manual.
96-22.
MAINTENANCE
-
96-23.
1.
BATTERY.
Clean battery and battery compartment
follows:
1.
as
REMOVAL
Unlatch
-
BATTERY.
and raise nose access door.
2. Loosen clamps
from battery.
and remove
3. Remove connectors
and protect ends.
Remove
battery
remove battery.
4.
holddown
96-24.
DO NOT USE EQUIPMENT
THAT
HAS BEEN USED ON LEAD ACID
BATTERIES.
2.
Connect
3.
Install vent tube and tighten
4.
Secure nose access door.
Clean battery
with
brush or wash with water.
a.
from battery
DO NOT USE WIRE
BRUSH.
ENSURE
VENT
PLUGS
ARE
CLOSED BEFORE CLEANING AND
BATTERY
EXTERIOR
I‘S
COMPLETELY
DRY
BEFORE
RETURNING TO USE.
a dry,
stiff
INSTALLATION
vent
-
terminal
bolts
and
BATTERY.,
1. Position battery in helicopter
in place with two holddown bolts.
connectors
tubes
and secure
to battery.
clamps.
fiber
96-00-00
Page 23
BHT-296L1-MM-10
96-26.
BATTERY
RELAY.
96-29.
EXTERNAL
RECEPTACLE.
Battery relay, located in nose section forward
of battery, is an electrically
operated switch
controlling battery current to main bus bar. It
is actuated
by a battery switch, located in
overhead
console, which opens and closes
circuit to relay energizing coil.
96-26.
1.
REMOVAL
Disconnect
2. Retract
terminals.
BATTERY
1.
protective
nipples
wires
from
attachment
relay
relay
relay
screws
3. Position
terminals.
protective
4.
battery.
EXTERNAL
-
and
2. Remove protective
wire to relay.
POWER
Set battery switch to OFF.
2. Remove attachment
screws and extract
receptacle enough to gain access to power
cables.
and protect
and lift relay
BATTERY
install
covers
1. Remove
and connect
attaching
receptacle
2. Position
install attachment screws.
MAXIMUM
EXTERNAL
SHOULD
AMPERES.
EXTERNAL
in helicopter
and
and connect
96-32.
nipples
-
protective cover from wire ends
cables to receptacle.
to cover
relay
POWER SYSTEM.
EXTERNAL
POWER RELAY.
External power relay, located in nose below
battery in landing light compartment,
is an
electrically
operated switch between external
power receptacle
and main bus bar. It is
controlled
through
small positive
pin from
external power source which energizes circuit
to activating coil of relay.
96-33.
REMOVAL
RELAY.
CURRENT
LIMIT OF
POWER
SOURCE
NOT EXCEED
1000
External power system consists of external
power receptacle,
external power relay, and
related wiring.
96-00-00
Page 24
EXTERNAL
96-31.
INSTALLATION
POWER -RECEPTACLE.
1. Position
screws.
96-28.
to expose
-
power
cables;
protect
3. Disconnect
terminals and tag wires for identification.
96-27.
INSTALLATION
RELAY.
Connect
External
power receptacle
located in front
center
at nose section
is a polarized
receptacle
used as a contact
point for
external power plug in.
96-30.
REMOVAL
RECEPTACLE.
RELAY.
battery.
3. Disconnect
ends.
4. Remove
free.
-
POWER
1. Set battery
external power.
2. Remove
access panel.
-
EXTERNAL
switch
landing
3. Retract protective
terminals.
to OFF.
light
nipples
POWER
Remove
compartment
to expose
relay
BHT-206L1-MM-10
4. Disconnect
ends.
5. Remove
free.
96-34.
POWER
wires
from
attachment
screws
INSTALLATION
RELAY.
Position
screws.
1.
2. Remove
relay wires.
relay
relay
-
and protect
and lift relay
MATERIALS
NUMBER
NOMENCLATURE
c-304
Solvent,
Type
Insignificant
4. Install
panel.
NOTE
and
protective
96-35.
protective
landing
light
GENERATOR
install
covers
For more information on consumable
materials,
refer to BHT-ALL-SPM
manual.
mounting
and connect
96-37.
nipple
to cover
compartment
relay
INSPECTION
Check for terminal
-
GENERATOR.
board damage.
2. Check brush cover for dents, loose or
bent pins,
broken
spring,
or damaged
insulation.
access
SYSTEM.
3. Clean exterior of unit with a clean cloth
moistened with cleaning solvent (C-304). With
a clean, dry cloth, wipe unit dry and clean
splines of driveshaft.
Generator
system
consists
of generator
portion
of the starter-generator,
voltage
regulator,
line control relay, generator reset
switch, and generator shunt.
Generator furnishes regulated voltage for all
dc electrical
components
on helicopter.
It
switches
onto main bus when generated
voltage exceeds bus voltage by 0.30 to 0.42
volts. Line control relay connects generator
power to bus and voltage regulator operates
line control relay, regulates generator voltage,
and provides protection against over-voltage
and low voltage.
96-36.
P-D-660,
II,
pH
EXTERNAL
1.
3. Position
terminals.
REQUIRED
GENERATOR.
Starter-generator
is located on underside of
engine to right of helicopter center line. Refer
to Chapter 71 for removal and installation
procedures.
DO NOT USE COMPRESSED
FOR INTERNAL
CLEANING
STARTER-GENERATOR.
AIR
OF
4. Remove brush band cover and inspect for
foreign material that has entered the unit.
Remove material with a vacuum cleaner only.
5. Rotate splined shaft to check for fan rub
and bearing condition.
6. Inspect
appearance
7.
commutator
for a smooth
with a light filming.
bright
Inspect brushes.
a. Brush leads must be flexible
a bright appearance.
and have
b. Brushes must have more than
remaining (figure 96-3).
1/4 life
96-00-00
Page 25
BHT-206L1-MM-10
VIEW I
VIEW II
NOTE
Starter - generator brushes
shoud be replaced at or near the
time brush wear indicates 1/4
life remaining.
VIEW III
Figure
96-3.
Starter-generator
Brushes must be properly seated. (A
100% seat in direction
of rotation
and
minimum 75% axially is mandatory.)
C.
ENSURE
BRUSH
LEADS
ARE
SECURED.
DO NOT RUB HAND
ON BRUSH HOLDER.
NOTE
If brushes pass inspection they must
be returned to their exact original
position in starter-generator.
6. Reinstall brush band cover and lockwire
attaching
screws.
If any of the brushes
require replacement
before next scheduled
overhaul
or inspection,
tag unit with
appropriate
comment and send to overhaul
shop.
96-00-00
Page 26
96-36.
brush
wear
VOLTAGE REGULATOR
A static type voltage regulator is located on
equipment
shelf
above
baggage
compartment.
It is adjustable from a 26.0 to
29.0 volt generator output by an adjustment
screw located on end of regulator adjacent to
connector. Regulator is a component of basic
dc power system and functions in conjunction
with. other components
of system to prevent
generator from being connected to line until
operating
voltage
is attained.
Voltage
regulator prevents reverse current flow, opens
generator
field and line contactor
relays in
over-voltage
‘condition,
and. holds generator
connected to line unless voltage drops to a
point where continued
operation
would be
detrimental
to electrical
equipment.
It also
provides increased resistance
in shunt field
circuit
to weaken
shunt field of startergenerator
during
start
operation,
and
maintains
approximately
1.0 volt positive
applied to generator terminal A, during start
operation,
to maintain
generator
residual
magnetism.
BHT-206L1-MM-10
96-36.
REMOVAL
REGULATOR.
Set battery
OFF position.
and
1.
2. Disconnect
protect with cap.
3. Remove
washers.
4.
-
Lift regulator
generator
electrical
four
96-43.
VOLTAGE
switches
connector
mounting
screws
to
and
and
96-40.
INSPECTION
AND
VOLTAGE
REGULATOR.
REPAIR
1.
-
Visually
inspect
regulator
case for
1.
physical
damage that could impair normal
efficient
operation
of unit. (Cracked
case,
damaged
contact
pins.) Check for secure
mounting of regulator.
2.
Replace
requirements
regulator
are not met.
96-41.
INSTALLATION
REGULATOR.
-
if
inspection
Position
regulator
and
mounting screws and washers.
install
1.
four
2. Remove
assembly.
Connect
electrical
96-42.
ADJUSTING
REGULATOR.
connector
-
LINE
CONTROL
power is OFF.
cover
from
electrical
panel
4. Remove mounting
screws
and lift relay from shelf.
INSTALLATION
-
wires.
and washers
LINE
CONTROL
relay on equipment
shelf and
1. Position
install with mounting screws and washers.
Connect
wires.
to regulator.
VOLTAGE
3. Install bus bars from generator
starter relay.
4.
Set multimeter
to appropriate
scale to
measure 28 Vdc. Connect positive lead to dc
bus located adjacent to voltage regulator and
negative
lead to airframe
ground.
Adjust
voltage regulator by turning adjustment screw
on face of regulator
clockwise
to increase
voltage
and counterclockwise
to decrease
voltage. Set regulator as follows:
CONDITION
-
3. Remove bus bars and disconnect
Protect wire ends.
2.
2.
REMOVAL
Ensure electrical
96-45.
RELAY.
VOLTAGE
RELAY.
Line control relay is installed
on electrical
panel assembly located on equipment
shelf
above baggage compartment.
Its function is
to open or close power circuit between dc bus
and generator. It is controlled by presence or
absence
of a proper output voltage
from
voltage regulator.
96-44.
RELAY.
from shelf.
LINE CONTROL
REGULATOR
SETTING
Below 59°F.
28 V.
Above 59°F.
28.5 V.
Install cover on electrical
96-46.
GENERATOR
RESET
shunt and
panel assembly.
SWITCH.
Generator reset switch is located on overhead
console. This switch is a double pole, double
throw,
spring
loaded
switch
with only
momentary
contact
in RESET position.
It
completes
generator
field circuit
in GEN
position
and supplies
voltage
to reset
generator field in RESET position.
96-47.
REMOVAL
SWITCH.
1.
Ensure electrical
-
GENERATOR
RESET
power is OFF.
96-00-00
Page 27
BHT-206L1-MM-10
2.
Open overhead
3.
Disconnect
4.
Remove
96-46.
RESET
Install
lockwasher
5.
and protect wire ends.
nut, lockwasher
INSTALLATION
SWITCH.
1.
-
Connect
electrical
3.
Close overhead
GENERATOR
console
with
1.
REMOVAL
console.
SHUNT.
-
GENERATOR
Ensure all electrical
2. Remove
assembly.
cover
3. Retract
terminals.
rubber
electrical
nipples
5.
Remove
96-51.
SHUNT.
mounting
INSTALLATION
1.
Position
hardware.
shunt
expose
electrical
screws and washers.
-
and
GENERATOR
install
2. Disconnect
igniter wire from
and isolate wire from ground.
igniter
unit
3. Connect
external
power
external power receptacle.
source
at
4. Energize external
power source. Close
ENGINE START circuit
breaker.
Depress
starter switch on pilot collective stick. Check
for approximately
28 Vdc at end of wire
(K4A2) while starter switch is depressed.
Connect
3.
Install bus bar.
4.
Position
96-00-00
Page 26
for zero
mounting
6. Close ENGINE IGNTR circuit breaker.
Depress starter switch on pilot collective stick.
Check for external power source voltage at
open end of igniter wire.
7. Release starter switch. Check
voltage at open end of igniter wire.
6. Open ENGINE
START
IGNTR circuit breakers.
and
for zero
ENGINE
9. Deenergize
external
power source
connect wire (K4A2) to starter-generator
wire to ignition unit.
96-54.
2.
-
panel
to
4. Remove bus bar and disconnect
wiring. Protect wire terminals.
96-53.
OPERATIONAL
CHECK
STARTER
SYSTEM
CIRCUITRY.
5. Release starter switch. Check
voltage at open end of wire (K4A2).
power is OFF.
from
SYSTEM.
1. Disconnect
wire (K4A2) from terminal C
on starter-generator
and isolate wire from
ground.
Generator
shunt is installed
on electrical
panel assembly
on equipment
shelf above
baggage compartment and provides a voltage
drop proportional
to current,
to operate
loadmeter.
96-50.
SHUNT.
STARTER-IGNITER
panel assembly.
Starter-igniter
system includes starter portion
of starter-generator,
starter relay, field-igniter
relay, igniter and starter switch.
wires to switch.
GENERATOR
Install cover on electrical
96-52.
and switch.
switch in overhead
and nut.
2.
96-49.
console.
and
and
STARTER.
wires.
nipples to cover terminals.
Starter-generator,
located on underside
of
engine, is energized by starter relay to start
engine. Refer to Chapter 71 for removal and
installation procedures.
BHT-206L1-MM-10
96-55.
STARTER
3.
RELAY.
Starter relay is installed on electrical panel
assembly
located on electrical
equipment
shelf above
baggage
compartment
and
supplies direct current to starter when starter
switch is depressed.
96-56.
1.
REMOVAL
-
Ensure electrical
2. Remove
assembly.
STARTER
RELAY.
power is OFF.
cover
from
electrical
panel
Disconnect
4. Remove
washers.
5.
Remove
96-60.
RELAY.
and protect wire ends.
four
mounting
INSTALLATION
1.
Position
relay
assembly and install
screws.
-
bus bar from relay.
2.
Connect
4.
Disconnect
and protect wire ends.
3.
Install cover on electrical
5.
Remove
mounting
6.
Remove
relay.
96-57.
RELAY.
INSTALLATION
1.
Position
relay
install with washers
-
on electrical
and mounting
2.
Connect
3.
Install bus bar.
4.
Install cover on electrical
96-58.
STARTER
panel and
screws.
FIELD-IGNITER
on electrical
panel
with four washers and
Disconnect
96-61.
and
relay.
3.
screws and washers.
screws
wires.
panel assembly.
IGNITER.
Igniter,
furnished
with power turbine,
is
located below tachometer generator on lower
left section of engine and consists of a low
tension capacitor discharge ignition exciter. It
provides
a continuous
ignition
arc during
engine start cycle. For additional information,
refer to engine manufacturers
maintenance
manual.
wires.
96-62.
FIELD-IGNITER
panel assembly.
RELAY.
STARTER
SWITCH.
Starter switch,
located
in collective
stick
switch box, is a double pole, single throw,
push button type switch.
When switch is
pressed to START position a ground potential
is furnished
to energize
starter and fieldigniter relays.
Field-igniter
relay is installed
on electrical
panel assembly
located on electrical
shelf
above baggage compartment.
It is actuated
when start switch is depressed and supplies
direct
current
to igniter
and start field
suppress section of voltage regulator.
96-63.
96-59.
RELAY.
2. Remove switch plate mounting
screws
and lift plate sufficiently
to gain access to
switch wires.
1.
REMOVAL
Ensure electrical
2. Remove
assembly.
cover
-
FIELD-IGNITER
power is OFF.
from
electrical
1.
REMOVAL
Ensure electrical
-
STARTER
SWITCH.
power is OFF.
3.
Disconnect
switch wires.
4.
Remove switch from switch plate.
panel
96-00-00
Page 29
BHT-206L1-MM-10
96-64.
INSTALLATION
SWITCH.
1. Align with indexing
in switch plate.
96-00-00
Page 30
-
STARTER
key and install
2.
switch
Connect
wires to switch.
3. Position plate
mounting screws.
on switch
box and install
BHT-206L1-MM-10
DC INDICATOR
96-65.
DC INDICATOR
2.
SYSTEMS.
I
lockwire
and temperature
bulb.
1. Screw temperature
bulb into well or line
fitting, tighten, and lockwire (C-405).
96-66.
96-69.
TEMPERATURE
BULBS.
MATERIALS
NUMBER
NOMENCLATURE
c-405
Lockwire,
MS20995
C32 (0.032 Inch Dia)
REMOVAL
1.
Disconnect
connector.
protect
-
TEMPERATURE
TACHOMETER
connector
electrical
to
GENERATORS.
Tachometer
generators
are three-phase
alternating current generators and provide ac
power
to drive
dual and gas producer
tachometer
indicators.
Rotor tachometer
generator
is located on forward left side of
transmission.
Power turbine
tachometer
generator is mounted on forward left side and
gas producer
tachometer
generator
is
mounted on forward right side of power and
accessory gearbox.
1.
Disconnect
connector.
2. Remove
studs.
-
TACHOMETER
and
protect
nuts and washers
Remove generator
electrical
from mounting
and gasket.
96-71.
INSTALLATION
GENERATORS.
-
TACHOMETER
1.
Position
gasket
and generator
mounting studs and install with washers
nuts.
-TEMPERATURE
and
INSTALLATION
2. Connect
electrical
temperature bulb.
3.
For more information on consumable
materials,
refer to BHT-ALL-SPM
manual.
96-67.
BULBS.
96-68.
BULBS.
96-70.
REMOVAL
GENERATORS.
REQUIRED
NOTE
I
Remove
DC indicator systems consist of engine and
transmission
temperature
indicator,
turbine
outlet temperature
indicator,
fuel quantity
indicator,
turbine power indicator
(N2), gas
producer
indication
(N1), and engine and
rotor (dual tachometer)
rpm indicator,
and
their respective
sensing
units.
Refer to
Chapter 98 for wiring diagrams.
Electrical resistance type bulbs are used in
engine oil and transmission
oil temperature
circuits.
Each bulb is connected
to an
electrical resistance temperature
indicator on
instrument
panel, and indicates an increase
by rise of temperature
in bulb
core.
Resistance elements of bulbs are hermetically
sealed
in metal wells.
Transmission
oil
temperature
bulb is located on left side of
transmission
and engine oil temperature
bulb
is mounted in a line near engine oil reservoir.
I
SYSTEMS
2. Connect
electrical
tachometer generator.
connector
on
and
to
96-00-00
Page 31
BHT-206L1-MM-10
96-72.
FUEL QUANTITY
96-73.
DESCRIPTION
SYSTEM.
-
SYSTEM.
positioned below empty mark and above white
dot on face of indicator.
FUEL
b. Set battery switch to BAT or apply
external
power to helicopter.
Close FUEL
QTY PRESS circuit breaker.
Fuel quantity
indicator pointer shall indicate “0” pounds. If
screw,
necessary
adjust “E” adjustment
located on fuel quantity transmitter protruding
above upper fuel cell, until pointer indicates
“0” pounds.
QUANTITY
Fuel quantity system is composed
of three
fuel quantity
probes,
a fuel quantity
transmitter,
a harness, and a fuel quantity
indicator. Two probes and a transmitter
are
installed in aft fuel cell and the other probe is
installed in forward left fuel cell. The probes,
which vary in capacitance
as fuel quantity
changes,
form one leg of a bridge. Bridge
output drives indicator located on instrument
panel. Refer to Chapter 28 for removal and
installation
of fuel quantity
probes
and
transmitter.
96-74.
FUEL
CALIBRATION
PROCEDURE
QUANTITY
SYSTEM.
SPECIAL
Type
TEST
Gull P/N
001
(GTF-1)
Repeat
steps
b. and
c.
d.
adjustments are no longer necessary.
-
e.
EQUIPMENT
361-016-
Fuel Quantity Gage,
Capacitance Type,
Test Set
until
Remove jumper.
2. Perform following
not empty:
NOMENCLATURE
OR MODEL
Connect a jumper wire between test
C.
points T, located
near top of transmitter.
Pointer
on fuel quantity
indicator
should
indicate 600 pounds. If necessary, adjust F
adjustment screw located beneath jumper on
transmitter until pointer indicates 600 pounds.
test when fuel cells are
a. Remove- main fuel cell quantity probe
located on upper section of aft fuel cell.
,
Fluke Model 8600A
(DVM)
Digital Voltmeter
or Equivalent
General Radio
GR1434P
Decade Resistor
Equivalent
NOTE
or
NOTE
Calibration
performed
components
with fuel empty can beonly with all system
installed.
1. Perform following
empty:
test when fuel cells are
NOTE
Refer to fuel quantity and pressure
wiring diagram in Volume 12.
a. With electrical
power OFF, observe
pointer on fuel quantity indicator. It should be
96-00-00
Page 32
Fuel quantity probe must be isolated
from helicopter
structure
before
following tests are accomplished.
b. Remove wires from terminals G, H, and
L on fuel quantity
probe. Attach a 44.95 pf
capacitor
across terminals
H and L on fuel
quantity probe.
With electrical
power turned
OFF,
C.
observe pointer on fuel quantity indicator. It
shall be positioned above white dot on face of
indicator.
d.
Place battery switch to
external
power to helicopter.
QTY PRESS circuit breaker.
indicator pointer shall indicate
necessary, adjust E adjustment
on’ fuel quantity probe housing
indicates 0 pounds.
BAT or apply
Close FUEL
Fuel quantity
0 pounds. If
screw located
until pointer
I
I
BHT-206L1-MM-10
e. Connect
a jumper wire between test
points T, located near top of fuel quantity
probe housing.
Pointer
on fuel quantity
indicator
shall
indicate
600 pounds.
If
necessary, adjust F adjustment screw located
beneath
jumper
on fuel quantity
probe
housing until pointer indicates 600 pounds.
Repeat
steps
d. and
e.
adjustments are no longer necessary.
f.
g.
Remove jumper.
h.
Disconnect
capacitor
wires to main fuel cell probe.
i.
until
Install
3. If empty
accomplished
as follows:
and
reconnect
main fuel cell probe in fuel cell.
and full calibration
cannot be
with fuel cells empty, proceed
206-063-656-l
transmitter
e. Disconnect
housing
assembly
connector
and connect
GTF-1 test set as shown in figure 96-4.
f. Set GTF-1 test set display select switch
to RES (MEG), resistance function switch to
A-B and resistance range switch to 100-l K.
GTF-1 test set should indicate a minimum of
100 megohms. If indication is lower than 100
megohms, insulation resistance between high
and low transmitter
tubes is too low and
transmitter should be replaced. If indication is
good proceed to step g.
g. Set test set
to A-GND.
Test
minimum of 100
lower
than
100
resistance between
ground is too low
replaced.
resistance function switch
set should
indicate
a
megohms.
If indication
is
megohms,
insulation
high transmitter tubes and
and transmitter
should be
h. Set test set resistance function switch
to B-GND. The test set should indicate
a
minimum of 100 megohms.
If indication
is
less than 100 megohms, insulation resistance
between low transmitter tubes and ground is
too low and transmitter should be replaced.
i. Check harness by removing
and probes from aircraft.
Place jumper across test points on fuel
cell probe housing assembly and observe fuel
quantity indicator.
a.
b.
pounds,
C.
pounds,
d.
pounds,
If indication
is between
replace 206-063-658-I
436 and 500
probe.
If indication
is between
replace 206-064-618-I
375 and 435
probe.
If indication
is between
replace 206-063-656-l
200 and 300
transmitter.
(1)
terminals
Check
continuity
on harness.
transmitter
between
H
(2)
Check
continuity
between
L
terminals on harness. If continuity is not found
in either test, replace harness.
NOTE
If indication
is other than stated in
steps b., c., or d., check fuel cell and
wiring as follows.
96-00-00
Page 33
BHT-206L1-MM-10
TANK
Figure
96-00-00
Page 34
96-4.
UNIT
Transmitter
and test set connection
BHT-206L1-MM-10
’
CAUTION AND WARNING SYSTEM
96-75.
CAUTION
SYSTEM.
AND WARNING
CAUTION
The caution and warning system consists of
caution light panel, engine rpm sensor and
warning
horn, low rotor rpm sensor and
warning horn, associated
components,
and
interconnecting
wiring. Refer to Caution and
Warning System wiring diagram in Volume 12.
External or battery power may be used for all
following operational tests.
96-76.
CAUTION
LIGHT PANEL.
Caution light panel is energized
by 28 Vdc
bus and protected by 5 amp CAUTION LTS
circuit breaker. Each capsule indicator light is
in series with its respective caution system.
96-77.
PANEL.
REMOVAL
-
CAUTION
1.
Disconnect
electrical
caution light panel.
connector
2. Remove four screws
light panel to instrument
and remove panel.
96-76.
PANEL.
INSTALLATION
LIGHT
from
that attach caution
panel glare shield
-
CAUTION
LIGHT
1. Install caution light panel on instrument
panel glare shield with four attaching screws.
2. Connect
light panel.
96-79.
LIGHT
electrical
OPERATIONAL
PANEL.
connector
TEST
-
Set battery
switch
to BAT
external power to helicopter.
1.
to caution
CAUTION
or apply
2. Close CAUTION LTS circuit breaker and
ensure that each segment is illuminated
as
listed below:
LIGHT
ENG OUT
LOW ROTOR RPM
TRANS OIL PRESS
TRANS OIL TEMP
BATTERY HOT
BATTERY RELAY
ENG CHIP
TRANS CHIP
FUEL FILTER
T/R CHIP
R FUEL PUMP
L FUEL PUMP
GEN FAIL
ENGINE OVERSPEED
LITTER DOOR OPEN
FUEL LOW
ALL SPARES
ON/OFF
CONDITION
ON
ON
ON
OFF
OFF
OFF
OFF
OFF
OFF
OFF
ON
ON
ON
OFF
OFF
OFF
OFF
3. Set DIM/BRT switch in middle position.
Check each segment as indicated in step 2.
4. Press DIM/BRT switch momentarily
DIM. Check caution lights do not dim.
5. Close INSTR LT circuit breaker.
instrument lights control clockwise until
closes. Press DIM/BRT switch to DIM.
caution lights, which are listed as ON
2, are dimly illuminated.
to
Rotate
switch
Check
in step
6. Press DIM/BRT switch to BRT. Check
caution
light segments
are again brightly
illuminated
(as indicated
in step 2) and
remain brightly illuminated after the DIM/BRT
switch is released.
7. Press DIM/BRT switch to DIM. Check
lights remain dimly illuminated after the switch
is released.
8. Depress PRESS TO TEST switch. Check
all caution
lights,
including
spares,
are
illuminated dimly.
96-00-00
Page 35
BHT-206L1-MM-10
9. Release PRESS TO TEST switch. Check
caution lights are illuminated as listed in step
2.
96-80.
ENGINE
SYSTEM.
OUT WARNING
Engine out warning system provides a visual
and audible
indication
of an engine
out
condition.
The system includes
ENG OUT
warning
light, located
on caution
panel,
engine
out warning
alarm
located
on
overhead
console,
and engine rpm sensor
located
on equipment
shelf forward
of
instrument
panel.
Engine
rpm sensor
is
connected
to gas producer
tachometer
generator circuit and when gas producer rpm
drops below 55 ±3 percent,
engine
rpm
sensor
provides
an electrical
ground
to
complete ENG OUT warning light and engine
out warning alarm circuit.
OPERATIONAL
TEST
96-81.
OUT WARNING
SYSTEM.
SPECIAL
TYPE
OR MODEL
H337
TEST
-
5. Decrease test
rpm to 50 percent
light is illuminated
alarm is audible.
set tachometer
generator
Check ENG OUT warning
and engine out warning
6. Reconnect
electrical
connector
to gas
producer tachometer generator on the engine.
7. Reconnect
rpm sensor.
96-62.
electrical
ENGINE
1.
Disconnect
sensor.
-
to rotor
RPM
connector
from
EQUIPMENT
2. Remove
washers.
NOMENCLATURE
Test
NOTE
Engine out warning system may be
tested
in conjunction
with gas
producer tachometer
indicator
test
procedure (Chapter 95).
1. Disconnect
electrical connector from rotor
rpm sensor and protect with cap or cover.
2. Disconnect electrical connector from gas
producer tachometer
generator and connect
plug to appropriate receptacle on test set.
3. Close CAUTION LTS circuit breaker, on
overhead console. Check ENG OUT warning
light is illuminated
and engine out warning
alarm is audible.
Page 36
ENGINE
electrical
3.
four
Remove engine
96-84.
INSTALLATION
SENSOR.
96-00-00
connector
RPM SENSOR.
96-83.
REMOVAL
SENSOR.
ENGINE
Howell
Engine
Set or Alternate
I
4. Increase test set tachometer
generator
rpm until
ENG OUT warning
light
is
extinguished.
Check gas producer tachometer
indicator reads 55 ±3 percent and engine out
warning alarm is not audible. Test set and
gas producer
tachometer
indicator
should
read approximately
the same.
attaching
screws
and
rpm sensor.
-
ENGINE
RPM
1. Position engine rpm sensor on equipment
shelf forward of instrument
panel and install
with four washers and four screws.
2.
Connect
electrical
connector
to sensor.
96-85.
LOW ROTOR RPM CAUTION
SYSTEM.
Low rotor rpm caution system provides visual
and audible
indication
of low rotor rpm
condition. This system includes ROTOR RPM
caution
light located on instrument
panel,
rotor rpm warning alarm installed on right side
plastic
headliner,
and rotor rpm sensor
located
on equipment
shelf forward
of
instrument
panel.
Rotor
rpm sensor
is
BHT-206L1-MM-10
connected
to rotor tachometer
generator
circuit and when rotor rpm drops below 90 ±3
percent,
rotor
rpm sensor
provides
an
electrical
ground to complete ROTOR RPM
caution
light and rotor rpm warning
alarm
circuits. A rotor rpm warning alarm disable
switch is installed under copilot seat slightly
forward
of collective
jackshaft.
When
collective stick is in extreme down position, a
lever on jackshaft
contacts
switch
and
deactivates rotor rpm warning alarm.
96-66.
ROTOR
TYPE
OPERATIONAL
RPM CAUTION
TEST SYSTEM.
SPECIAL
EQUIPMENT
TEST
OR MODEL
H337
LOW
Test
rpm caution system may
in conjunction
with dual
indicator (Chapter 95).
Disconnect
electrical
connector
from
engine rpm sensor and protect with cap or
cover.
1.
2. Disconnect electrical connector from rotor
tachometer generator and connect plug to the
appropriate receptacle on test set.
collective
stick
6. Move collective
stick towards its lowest
extreme. Check rotor rpm warning alarm is
deactivated when collective stick is moved to
within 1 ± 0.2 inch (25 ± 5 mm) from its
extreme
down position,
measured
at grip
adjacent to switch box. If switch is not in
tolerance,
adjust tab on jackshaft
under
copilot seat.
10.
Reconnect
rpm sensor.
96-87.
NOTE
3. Move
extreme.
7. Decrease test set tachometer
generator
rpm to 85 percent.
Check ROTOR
RPM
caution
light is illuminated
and rotor rpm
warning alarm is audible.
9. Reconnect
electrical
connector
tachometer generator on the engine.
NOMENCLATURE
Howell
Engine
Set or Alternate
Low rotor
be tested
tachometer
tachometer
indicator is 90 ±3 percent. Test
set and indicator should read approximately
the same.
to
its
lowest
4. Close CAUTION LTS circuit breaker on
overhead
console.
Check
ROTOR
RPM
caution
light is illuminated
and rotor rpm
warning alarm is not audible.
5. Raise collective stick and check ROTOR
RPM caution light remains illuminated
and
rotor rpm warning alarm is now audible.
6. Increase test set tachometer
generator
rpm until ROTOR
RPM caution
light is
extinguished
and rotor rpm warning alarm is
not audible. Check rotor indication
on dual
electrical
to engine
ROTOR RPM SENSOR.
96-66.
REMOVAL
SENSOR.
1. Disconnect
sensor.
2. Remove
washers.
3.
connector
to rotor
Remove
-
ROTOR
electrical
four
RPM
connector
attaching
from
screws
and
rotor rpm sensor.
96-69.
INSTALLATION
SENSOR.
-
ROTOR
RPM
1. Position rotor rpm sensor on equipment
shelf forward of instrument panel and install
with four washers and four screws.
2.
Connect
electrical
96-90.
TRANSMISSION
CAUTION SYSTEM.
connector
to sensor.
OIL PRESSURE
Transmission
oil pressure
caution
system
includes TRANS OIL PRESS caution light and
transmission
oil pressure switch.
96-00-00
Page 37
--
BHT-206L1-MM-10
96-91.
OPERATIONAL
TRANSMISSION
OIL
SYSTEM.
1.
Close CAUTION
4.
TEST PRESSURE
LTS circuit
light is
3. Disconnect transmission
oil pressure line
at engine firewall. Connect a hand pressure
gun to line leading to indicator.
Gradually
increase pressure until TRANS OIL PRESS
caution light is extinguished.
Check caution
light extinguishes
at a maximum increasing
pressure of 36 psig (246 kPa).
4. Decrease pressure on the transducer until
TRANS OIL PRESS caution light illuminates.
Check that caution
light illuminates
at a
decreasing
pressure of 30 ± 2 psig (207 ±
I 13.8 kPa).
5. Reduce pressure
to zero. Disconnect
hand pressure
gun and reconnect
aircraft
transmission
lines at the firewall.
Check
TRANS
OIL PRESS
caution
light
is
illuminated.
1.
Remove
pedestal
TRANSMISSION
3.
Disconnect
96-00-00
Page 36
OIL
access doors.
2. Disconnect
electrical
connector
switch and protect with cap or cover.
and cap pressure
line.
Position switch
mounting hardware.
hardware
and switch.
from
TRANSMISSION
in helicopter
1.
2. Uncap
switch.
pressure
3.
Connect
electrical
4.
Install pedestal
line
and install
and
connect
connector
to
to switch.
access doors.
96-95.
TRANSMISSION
OIL
TEMPERATURE
CAUTION SYSTEM.
Transmission
oil temperature
caution system
includes TRANS OIL TEMP caution light and
transmission
oil temperature switch.
96-96.
OPERATIONAL
TEST TRANSMISSION
OIL TEMPERATURE
CAUTION
SYSTEM.
1.
OIL PRESSURE
Transmission
oil pressure switch, located in
forward cabin section below instrument panel,
is a pressure
operated
switch installed
in
transmission
oil pressure indicator line and
serves to energize a transmission
oil pressure
caution light on instrument
panel, warning
pilot of low oil pressure.
96-93.
REMOVAL
PRESSURE
SWITCH.
mounting
96-94.
INSTALLATION
OIL PRESSURE
SWITCH.
breaker.
2. Check TRANS OIL PRESS caution
illuminated.
96-92.
TRANSMISSION
SWITCH.
Remove
CAUTION
Close CAUTION
LTS circuit
breaker.
2. Connect a temporary short between stud
on transmission
oil temperature
switch and
helicopter structure. Check TRANS OIL TEMP
caution light illuminates.
3. ‘Remove short and check TRANS
TEMP caution light is extinguished.
OIL
96-97. ‘TRANSMISSION
OIL
TEMPERATURE
SWITCH.
Transmission
oil- temperature
switch, located
adjacent
to temperature
bulb left side of
transmission,
is hermetically
sealed,
temperature operated, single-pole switch, that
closes when. temperature
of transmission
oil
rises above- safe operating
range.
This
energizes a transmission
temperature caution
light on instrument panel.
BHT-206L1-MM-10
MATERIALS
REQUIRED
96-l 02.
BATTERY
RELAY
CAUTION
SYSTEM.
NUMBER
NOMENCLATURE
c-405
Lockwire,
MS20995C32 (0.032 Inch Dia)
Battery
relay
caution
system
includes
BATTERY
RLY caution
light and related
circuitry for battery relay and battery switch. If
battery relay remains energized when battery
switch is set to OFF, BATTERY RLY caution
light will illuminate.
NOTE
For more information on consumable
materials,
refer to BHT-ALL-SPM
manual.
96-103.
BATTERY
I.
96-96.
REMOVAL
- TRANSMISSION
TEMPERATURE
SWITCH.
OIL
1.
Disconnect
switch.
from
electrical
96-99.
INSTALLATION
OIL TEMPERATURE
electrical
96-100.
BATTERY
SYSTEM.
and
unscrew
switch
4. Connect jumper wire between terminals
11 and 12 of battery
relay (2K1). Check
BATTERY RLY caution light illuminates.
- TRANSMISSION
SWITCH.
5. Remove jumper. Check
caution light extinguishes.
tighten
96-104.
CAUTION
connector.
HOT WARNING
Battery
hot warning
system
consists
of
BATTERY
HOT warning
light and internal
battery
over-temp
sensor switches.
Both
switches
in the battery are actuated
when
battery temperature
reaches 145 ± 5°F (62.7
± 2.5°C), which illuminates
BATTERY HOT
warning light. When BATTERY HOT warning
light illuminates,
battery charging circuit must
be disengaged to allow battery temperature to
drop.
--
OPERATIONAL
TEST HOT WARNING
SYSTEM.
All testing
accordance
instructions.
shall
with
be accomplished
battery
manufacturers
in
ENGINE
CHIP
SYSTEM.
BATTERY
RLY
DETECTOR
Engine chip detector caution system includes
ENG CHIP caution light, two engine furnished
magnetic
drain plug/chip
detectors,
and
related wiring. In event of metal particles in
oil, magnet
will attract
particles.
When
sufficient metal is attracted to complete circuit
between pole and ground, ENG CHIP caution
light will illuminate. For additional information
on the magnetic drain plugs/chip
detectors,
refer to manufacturers
engine manual.
96-105.
OPERATIONAL
TEST - ENGINE
CHIP DETECTOR
CAUTION
SYSTEM.
1.
96-101.
BATTERY
LTS circuit breaker.
switch
to BAT. Check
2. Set battery
BATTERY RLY caution light is extinguished.
connector
1. Screw switch into transmission,
and lockwire (C-405).
Connect
Close CAUTION
3. Set battery
switch
to OFF. Check
BATTERY RLY caution light is extinguished.
2. Remove lockwire
from transmission.
2.
OPERATIONAL
TEST RELAY CAUTION
SYSTEM.
Close CAUTION
LTS circuit breaker.
2. Remove electrical
connector
from one
engine chip detector.
Connect a temporary
short between pin of connector and aircraft
structure. Check ENG CHIP caution light is
illuminated.
96-00-00
Page 39
BHT-206L1-MM-10
3. Remove short. Check
light is extinguished.
ENG CHIP caution
4. Reconnect electrical connector to engine
chip detector. Check ENG CHIP caution light
remains extinguished.
5. Remove electrical
engine chip detector.
short between pin of
structure. Check ENG
illuminated.
connector
from other
Connect a temporary
connector and aircraft
CHIP caution light is
6. Remove short. Check
light is extinguished.
1.
Close CAUTION
CHIP DETECTOR
1.
related
Close CAUTION
LTS circuit
breaker.
2. Remove tail rotor gearbox chip detector
and ground probe to helicopter
structure.
Check T/R CHIP caution light is illuminated.
LTS circuit
96-110.
FUEL FILTER
SYSTEM.
breaker.
4. Complete steps 1 through 3 for remaining
transmission
chip detector and freewheeling
unit chip detector.
Tail rotor gearbox
chip detector
system consists of T/R CHIP caution
T/R CHIP
CAUTION
OPERATIONAL
TEST
CAUTION
SYSTEM.
Close CAUTION
LTS circuit
-
FUEL
breaker.
2. Disconnect
electrical
connector
(1S5P1)
from fuel filter differential
pressure switch.
Connect a temporary
short between pins A
and B on connector
(1S5P1). Check FUEL
FILTER caution. light is illuminated.
short.
Reconnect
electrical
3. Remove
connector
(1S5P1) to fuel filter differential
pressure switch. Check FUEL FILTER caution
light is extinguished.
96-112.
96-108.
TAIL ROTOR GEARBOX
DETECTOR CAUTION SYSTEM.
Check
Fuel filter caution system consists of FUEL
FILTER caution
light, fuel filter pressure
switch,
and related
wiring.
Should
fuel
pressure drop below safe operating limit, fuel
filter pressure switch closes and energizes
FUEL FILTER caution light alerting pilot of
clogged fuel filter. Fuel bypasses filter at this
time.
1.
3. Reinstall chip detector and check TRANS
CHIP caution light is extinguished.
Page 40
and
96-109.
OPERATIONAL
TEST - TAIL
ROTOR GEARBOX
CHIP DETECTOR
CAUTION
SYSTEM.
96-111.
FILTER
TEST DETECTOR
2. Remove one transmission
chip detector
and ground probe to helicopter
structure.
Check TRANS CHIP caution is illuminated.
96-00-00
detector,
3. Reinstall chip detector.
caution light is extinguished.
Transmission
chip detector caution system
consists of TRANS CHIP caution light, two
transmission
chip detectors,
a freewheeling
unit chip detector,
and related wiring. For
maintenance
instructions
on chip detectors,
refer to Chapter 63.
96-107.
OPERATIONAL
TRANSMISSION
CHIP
CAUTION
SYSTEM.
chip
ENG CHIP caution
7. Reconnect electrical connector to engine
chip detector. Check ENG CHIP caution light
remains extinguished.
96-106.
TRANSMISSION
CAUTION SYSTEM.
rotor gearbox
wiring.
FUEL PUMP CAUTION
SYSTEM.
CHIP
caution
light, tail
Fuel pump caution system consists of R/FUEL
PUMP caution light, L/FUEL PUMP caution
light, right side fuel flow switch, left side fuel
flow switch, and related wiring.
BHT-206L1-MM-10
96-113.
OPERATIONAL
TEST PUMP CAUTION SYSTEM.
1.
FUEL
Close CAUTION LTS circuit breaker.
2. Disconnect
electrical
connector
(1S8P1)
from right side fuel flow switch. Check R/
FUEL PUMP caution light extinguishes.
3. Reconnect
electrical
connector
side fuel flow switch and check
PUMP caution light illuminates.
to right
R/FUEL
4. Disconnect
electrical connector from left
side fuel flow switch. Check L/FUEL PUMP
caution light extinguishes.
fuel tanks. To gain access to flow switches
and for removal and installation
procedures,
refer to Chapter 28.
96-115.
FUEL LOW CAUTION
SYSTEM.
Fuel low system, which is independent of fuel
quantity
system,
illuminates
FUEL LOW
caution light when there is approximately
9.5
I
gallons (35.91 liters) of usable fuel remaining.
96-116.
GENERATOR
SYSTEM.
FAILURE
CAUTION
Generator failure caution system consists of
GEN FAIL caution light, line control relay,
starter relay, and related wiring. When line
control is deenergized,
GEN FAIL caution
light circuit is completed to ground through
line control
relay. When starter
relay is
energized,
GEN FAIL caution light circuit is
completed to ground through the starter relay.
5. Reconnect electrical connector to left side
fuel flow switch and check L/FUEL PUMP
caution light illuminates.
96-114.
FUEL FLOW SWITCH.
Right and left side fuel flow switches
are
located in fuel pressure lines between forward
96-00-00
Page 41/42
BHT-206L1-MM-10
LIGHTING SYSTEMS
96-117.
LIGHTING
SYSTEMS.
Lighting
systems
consist
of interior
and
exterior
lighting.
Interior
lighting
system
includes cockpit light, instrument and control
panel lighting,
and cabin lighting.
Exterior
lighting system includes position, anticollision,
and landing lights. Refer to Chapter 98 for
individual system wiring diagrams.
96-118.
INTERIOR
LIGHTING
SYSTEM.
Interior lighting system consists of cockpit,
instrument
and control panel lighting, cabin
lighting, and related wiring and components.
96-119.
COCKPIT
LIGHT.
Cockpit light is a multipurpose
utility light
designed to provide white illumination
utilizing
a narrow spotlight
or wide floodlight
beam.
Light is protected by a 5 ampere COCKPIT LT
circuit breaker. Controls for ON/OFF, DIM/
BRIGHT, and SPOT/FLOOD
are par-l of the
cockpit light body.
96-120.
REMOVAL
AND BASE.
I.
Ensure
-
electrical
2. Disconnect
(4TB1).
COCKPIT
2. Insert light wire through
install black wire on terminal
Install ground wire.
96-122.
PANEL
LIGHT
Instrument and control panel lighting circuits
are protected by a 5 ampere INSTR LT circuit
breaker.
Clockwise
rotation
of INSTR LT
control closes attached switch and supplies
28 Vdc through INSTR LT circuit breaker to
collector of transistor (8Q2), 100 ohm section
of INSTR LT control (8U1) and light dimming
resistor (8R1). At the opposite end of resistor
(8R1), 5.2 Vdc is controlled
by zener diode
(8CR1) and is applied to transistor (8Q1) and
150 ohm section of INSTR LT control. The
transistor
base voltage is controlled
by the
INSTR LT control which controls brightness
level of the indicators,
control
panels,
compass, and inclinometer post lights.
96-123.
OPERATIONAL
CHECK INSTRUMENT
AND CONTROL
PANEL
LIGHTING.
power is OFF.
board
remove
4. Remove mounting nuts, washers,
and spacer holding light base.
screws,
COCKPIT
1. Place light and spacer in position
install screws, washers, and nuts.
and
and
until
and
3. Rotate INSTR LT control clockwise and
check lights increase in brightness
and are
brightest at maximum clockwise.
4. Rotate
control
counterclockwise
and
check lights decrease in brightness
and are
extinguished
at maximum counterclockwise.
96-124.
-
to OFF
2. Rotate INSTR LT control clockwise
switch just closes.
Check instrument
control panel lights are dimly illuminated.
black wire from terminal
INSTALLATION
AND CONTROL
Rotate INSTR LT control
I.
close INSTR LT circuit breaker.
3. Disconnect
ground
wire and
cockpit light wire from grommet.
96-I 21.
LIGHT.
INSTRUMENT
LIGHTING.
grommet and
board (4TB1).
CABIN
LIGHTING.
Four individual
white cabin lights provide
passenger
area
illumination
at pilots
discretion.
These lights are protected
by 5
ampere COCKPIT LTS circuit breaker. They
are controlled by pilot CABIN LTS switch and
96-00-00
Page 43
BHT-206L1-MM-10
individual
switches located near each light.
When pilot CABIN LTS switch is placed in
CABIN LTS position,
all four cabin lights
illuminate.
When switch is placed in PASS
position,
each light can be individually
controlled by associated passenger switch.
96-125.
EXTERIOR
LIGHTING
POSITION
LIGHTS.
Position
lights consist of upper horizontal
stabilizer left and right side and lower cabin
left and right side position lights and tail light.
Position light lens or lamps may be replaced
by removing
one light fairing
attachment
screw
and removing
lens or lamp as
necessary.
96-127.
1.
REMOVAL
-
Check all electrical
POSITION
Remove
Place insert
nut.
I.
LIGHT.
1. Thread
wire
connect to light.
-
2. Tighten coupling
install three attaching
96-129.
1.
REMOVAL
Ensure electrical
-
POSITION
96-l 33.
REMOVAL
Page 44
and
-
-
LIGHT.
ANTICOLLISION
NOTE
When replacing
flash tube in anticollision
beacon,
avoid touching
glass portion of tube with fingers. Oil
from finger will shorten life of tube.
1.
Check all electrical
nut; position
screws.
light
and
3.
retainer
power is OFF.
ring clamp
power is OFF.
and
and remove
Pull flash tube from socket.
96-l 34.
INSTALLATION
ANTICOLLISION
LIGHT.
LIGHT.
3. Disconnect
coupling
nut that attaches
wiring insert to light and protect insert.
96-00-00
and install
CHECK
ANTICOLLISION
2. Release
lens.
screws
on mount
-screws.
96-132.
and
2. Remove
two attaching
remove light from mounting.
from wiring insert.
and tighten coupling
2. Set POS LT switch
breaker
to OFF.
Check side position lights and tail light are
extinguished.
nut
TAIL
LIGHT.
I.
Set POS LT switch breaker to POS LT.
Check right and left side position lights and
the tail light are illuminated.
coupling
through
protection
in position
TAIL
LIGHT.
power is OFF.
INSTALLATION
-
96-131.
OPERATIONAL
POSITION
LIGHTS.
2. To remove position lights, remove-three
attaching
screws
and remove
light’ from
mounting.
Back
off coupling
nut and
disconnect electrical wiring from light. Protect
wire end.
96-l 26.
LIGHT.
INSTALLATION
2. Position light
tighten attachment
SYSTEM.
Exterior lighting system consists of position,
anticollision,
landing lights and related wiring
and components.
96-126.
96-l 30.
-
1.
Insert flash tube into socket.
2.
Reassemble
retainer
ring clamp and lens.
3. Position
lamp support
plate in base;
install lens; install and secure retainer ring.
BHT-206L1-MM-10
96-135.
OPERATIONAL
ANTICOLLISION
LIGHT.
CHECK
2.
-
Install landing
Connect
a.
Set ANTI COLL LT switch breaker
to
ANTI COLL LT. Check anticollision
light
illuminates
and flashes at a rate of 42 to 45
flashes per minute.
I.
2. Set ANTI
OFF.
Check
extinguishes.
COLL
the
LT switch
anticollision
96-136.
HS STROBE
(FLASHER UNIT).
96-137.
POWER
REMOVAL
SUPPLY.
b.
install
nuts.
96-136.
POWER
screws,
INSTALLATION
SUPPLY.
Connect
electrical
-
LANDING
96-140.
LIGHTS.
REPLACEMENT
Remove
1.
landing
and
attaching
and wiring.
LIGHTS.
-
LANDING
b.
Open or remove light access window.
d.
OPERATIONAL
LIGHTS.
CHECK
power is OFF.
nuts, spacers,
landing lights.
washers
-
1. Close LDG LIGHTS circuit breaker. Set
LDG LT switch
to FWD. Check forward
landing light illuminates.
3. Set LDG LT switch
landing lights extinguish.
96-142.
LANDING
96-143.
RELAYS.
REMOVAL
to OFF. Check
and
Disconnect
electrical
wiring
from
lights and protect wire ends. Remove
both
LIGHT RELAYS.
-
Check all electrical
LANDING
wiring
3. Remove screws and washers
relay and remove relay.
96-144.
INSTALLATION
LIGHT RELAYS.
LIGHT
power is OFF.
2. Disconnect
all electrical
relay and protect wire ends.
lights.
Check all electrical
landing
lights.
I
Install or close light access window.
96-l 41.
LANDING
1.
a.
Remove
C.
bolts attaching
m
2. Set LDG LT switch to BOTH. Check both
landing lights illuminate.
HS STROBE
connector
96-139.
and
and
Position
forward
light so lower
forward edge of light is 6.00 inches
(152.4 mm) forward of station 18. Aft
light should be positioned so lower
forward edge of light is 2.00 inches
(50.8 mm) forward of station 18.
and black
washers,
I.
Position unit; install and tighten
screws, washers, and nuts.
2.
bracket
spacers
power is OFF.
2. Disconnect electrical connector
and white wire. Protect wire ends.
attaching
to landing
NOTE
C.
3. Remove
nuts.
wiring
Position light on mounting
attaching bolts, washers,
breaker
to
light
HS STROBE
Check all electrical
1.
electrical
lights.
POWER SUPPLY
-
lights.
-
from the
attaching
LANDING
I.
Position landing light relay beneath base
of instrument
pedestal and install attaching
washers and screws.
96-00-00
Page 45
BHT-206L1-MM-10
2.
Connect
all electrical
96-145.
LANDING
96-146.
SWITCH.
REMOVAL
1.
Ensure electrical
wiring.
LIGHT
-
4.
SWITCH.
LANDING
96-147.
INSTALLATION
LIGHT SWITCH.
Disconnect
power is OFF.
96-00-00
Page 46
switch wires.
-
LANDING
LIGHT
2. Remove
collective
stick switch
plate
mounting screws and lift plate sufficiently
to
gain access to switch wires.
3.
Remove switch from switch plate.
1. Position
index
switch plate.
2.
Connect
key and install
switch
in
wires to switch.
3. Position
plate on switch
mounting screws.
boss and install
BHT-206L1-MM-10
ENGINE CONTROL AND ACCESSORIES
,
96-148.
ENGINE CONTROL
ACCESSORIES
SYSTEMS.
2. Open FUEL BOOST
RIGHT
circuit
breaker. Check right fuel boost pump ceases
operation.
AND
Engine
control
and accessories
systems
consist
of fuel boost pumps, fuel shutoff
valve, fuel dump switch, fuel dump solenoid,
fuel valve switch, engine anti-ice solenoid,
and engine anti-icing switch. Refer to Chapter
98 for individual systems wiring diagrams.
96-149.
FUEL BOOST
SYSTEMS
PUMPS.
3. Close FUEL BOOST LEFT circuit breaker.
Set battery switch to BAT. Check left fuel
boost pump (located aft on sump) operates.
4. Set battery switch to OFF. Check left fuel
boost pump ceases operation.
5. Close LH FUEL BOOST circuit breaker.
Ensure FUEL VALVE circuit breaker is open.
Set FUEL VALVE switch to ON. Check left
fuel boost pump operates.
Two electrically
operated fuel boost pumps
submerged
in fuel cell are accessible
from
bottom
of fuselage.
Both
pumps
are
connected to a common fuel line and either
will furnish
sufficient
flow for engine
operation.
Pumps
are energized
from
separate circuit breakers in overhead console
and may be operated separately or together.
Refer
to Chapter
28 for removal
and
installation of fuel boost pumps.
7. Open LH FUEL BOOST circuit breaker.
Check
left fuel
boost
pump
remains
inoperative.
NOTE
NOTE
Left fuel boost pump will continue to
operate if both FUEL BOOST LEFT
(located
in OVHD CSL) and LH
FUEL BOOST (located adjacent to
battery) circuit breakers are pushed
in, fuel valve switch is ON, and
battery switch is OFF.
When operating on external power
or aircraft
generator
power, with
battery removed, battery switch must
be set to BAT to activate left fuel
boost pump.
6. Set FUEL VALVE switch to OFF. Check
left fuel boost pump ceases operation.
96-151.
96-150.
BOOST
OPERATIONAL
PUMPS.
CHECK
-
FUEL
NOTE
Battery
test.
must
be installed
for this
Sufficient fuel shall be added to fuel
cell to ensure fuel inlet of pump is
submerged by at least 1 inch.
1. Close
FUEL BOOST
RIGHT
circuit
breaker. Check right fuel boost pump (located
forward on sump) operates.
FUEL VALVE.
Fuel shutoff valve, located above aft fuel cell
on right side of helicopter,
is an electrically
operated motor driven valve and provides a
means of shutting off fuel to engine. Valve is
controlled
by FUEL VALVE
switch
on
instrument
panel. Refer to Chapter 28 for
maintenance procedures.
96-152.
VALVE.
OPERATIONAL
CHECK
-
FUEL
1. Set FUEL VALVE switch
to OFF and
close FUEL VALVE circuit breaker. Set FUEL
VALVE switch to ON. Check fuel valve opens.
96-00-00
Page 47
2. Set FUEL VALVE
fuel valve closes.
96-153.
switch
to OFF. Check
FUEL DUMP VALVE.
Fuel dump valve, located on fuel sump, is an
electrically
operated
solenoid
valve and
provides
a means of draining-fuel
tanks..
Valve ‘is controlled
by FUEL DUMP switch
located on RH lower aft side of fuel cell. Refer
to Chapter 28 for maintenance procedures.
96-154.
OPERATIONAL
DUMP VALVE.
CHECK -
2.
Set FUEL VALVE switch to OFF.
3. Press FUEL DUMP
dump valve opens.
switch.
Check
4. Release FUEL DUMP switch.
dump valve closes.
Check fuel
96-156.
REMOVAL
SWITCH.
-
FUEL DUMP
1.
power is OFF.
96-157.
INSTALLATION
SWITCH.
Connect
96-00-00
Page 48
electrical
1.
power is OFF.
Ensure electrical
2. Disconnect
wire ends.
.
3. Remove
switch.
FUEL VALVE
electrical
attaching
1. Position
hardware,
switch
2.
electrical
Connect
hardware
and remove
1. Close ENGINE
breaker.
FUEL DUMP
wires to switch.
and protect
hardware
and remove
-
FUEL VALVE
and install
with attaching
wires to switch.
Hot air solenoid valve is powered from 28 Vdc
essential bus through ENGINE DEICE/ANTIICING circuit breaker and ENGINE DEICING/
ANTI-ICING.
switch. When hot air solenoid
valve is deenergized
(valve open), hot air
passes from compressor
diffuser through
valve
to inlet housing.
Hot air aids in
preventing ice formation on hollow inlet guide
vanes.
.
96-162.
ENGINE
-
wires
96-161.
ENGINE DEICING/ANTI-ICING
SYSTEM.
and protect
1. Position fuel dump switch and install with
attaching hardware.
2.
-
wires
electrical
3. Remove attaching
fuel dump switch.
REMOVAL
96-159.
SWITCH.
fuel
FUEL DUMP SWITCH.
2. Disconnect
wire ends.
SWITCH.
96-160.
INSTALLATION
SWITCH.
Close FUEL VALVE circuit breaker.
Ensure electrical
FUEL VALVE
FUEL
1.
96-155.
96-156.
OPERATIONAL
CHECK DEICING/ANTI-CING
SYSTEM.
DEICE/ANTI-ICING
2. Set ENGINE DEICING/ANTI-ICING
on engine
control
to ON. Verify
solenoid deenergizes.
circuit
switch
hot air
3. Set ENGINE DEICING/ANTI-ICING
switch
to OFF. Verify hot air solenoid energizes.
4. Open ENGINE
breaker.
DEICE/ANTI-ICING
circuit
BHT-206L1-MM-10
96-163.
ENGINE
SWITCH.
DEICING/ANTI-ICING
96-164.
REMOVAL ANTI-ICING
SWITCH.
1.
Ensure electrical
2.
Remove
ENGINE
DEICING/
power is OFF.
electrical
96-169.
REMOVAL
SWITCH.
CONTROL
wires from switch.
3. Remove attaching
from edgelit panel.
hardware
and
switch
1. Install
switch
attaching hardware.
Install electrical
96-166.
in edgelit
panel
Ensure electrical
with
3.
Disconnect
switch wires.
4.
Remove switch from panel.
ACTUATOR.
Governor actuator is located on forward left
side of engine and is a reversible motor that
provides
increase
or decrease
of governor
setting. Actuator is controlled
by GOV RPM
switch on collective stick. Refer to Chapter 76
for maintenance
procedures.
UTILIZE
CAUTION
IN SWITCH
REMOVAL TO PREVENT CHAFING
OR DAMAGE TO WIRES.
96-170.
CONTROL
96-167.
OPERATIONAL
GOVERNOR ACTUATOR.
INSTALLATION
SWITCH.
-
GOVERNOR
CHECK 1. Install switch to plate observing
indexing key is in proper position.
1. Close GOV CONT circuit breaker. Press
GOV RPM switch to INCR. Check governor
control actuator retracts.
2.
2. Press GOV RPM switch to DECR. Check
governor control actuator extends.
3. Position plate
mounting screws.
96-166.
96-171.
GOVERNOR
power is OFF.
Remove switch plate mounting
screws
and lift plate sufficiently
to gain access to
switch wires.
wires on switch.
GOVERNOR
1.
GOVERNOR
2.
96-165.
INSTALLATION
- ENGINE
DEICING/ANTI-ICING
SWITCH.
2.
With switch
in INCR position,
circuit
to
actuator motor is completed and allows motor
to move arm in one given direction.
With
switch in DECR position polarity to actuator
motor is reversed, allowing actuator arm to
move in opposite direction. When switch is in
rest position, circuit is deenergized.
RPM SWITCH.
Governor
control
switch,
located
in pilot
collective
switch
box, is a double
pole,
double-throw,
spring
loaded,
momentary
contact switch that enables pilot to increase
or decrease
governor
rpm actuator setting.
Connect
that
wires to switch.
PARTICLE
on switch
box and install
SEPARATOR.
Particle separator is an integral part of 250C28 engine. For operation and maintenance
procedures,
refer
to operation
and
maintenance
manuals
provided
by Detroit
Diesel Allison on 250-C28 engine.
96-00-00
Page 49/50
BHT-206L1-MM-10
96-172.
FLIGHT
CONTROLS
FLIGHT
CONTROL
SYSTEM.
2.
Flight controls system consists of hydraulic
bypass
solenoid,
CONTROL
BOOST/
HYDRAULIC
SYSTEM
switch and related
components and wiring.
Remove
body.
96-176.
BYPASS
CONTROLS
OPERATIONAL
-
Connect
96-177.
SYSTEM
Connect
hydraulic
helicopter
and adjust
system pressure.
external
for normal
INSTALLATION
SOLENOID.
and
-
screw
electrical
valve
off
HYDRAULIC
and secure
connector.
FLIGHT
SYSTEM.
1.
2. Close
CONTROL
switch to
required
stick, and
CHECK
lockwire
1. Screw valve on body; tighten
with lockwire.
2.
96-173.
SYSTEM
power to
hydraulic
CONTROL
SWITCH.
BOOST/HYDRAULIC
CONTROL
BOOST/HYDRAULIC
SYSTEM
switch, located in edgelit panel on pedestal,
controls
operation
of hydraulic
bypass
solenoid. Refer to paragraph 96-9 and 96-13
for maintenance procedures.
HYDR SYSTEM circuit breaker. Set
BOOST/HYDRAULIC
SYSTEM
ON. Check only normal force is
to operate cyclic stick, collective
pedal controls.
Set CONTROL
BOOST/HYDRAULIC
SYSTEM
switch
to OFF. Check
cyclic,
collective and pedal controls are much harder
to move than in step 2.
3.
96-174.
HYDRAULIC
SOLENOID.
96-175.
BYPASS
REMOVAL
SOLENOID.
1.
Disconnect
connector.
BYPASS
-
and
HYDRAULIC
protect
electrical
96-00-00
Page 51/52
BHT-206L1-MM-10
MISCELLANEOUS
96-178. MISCELLANEOUS
SYSTEM.
Miscellaneous
electrical
defogging blowers.
96-179.
DEFOGGING
-
consists
SYSTEM
overhead
console.
Refer to Chapter 21 for
removal and installation of defogging blowers.
ELECTRICAL
system
ELECTRICAL
of
BLOWERS.
A right and left defogging blower is provided
in forward end of right and left side ram air/
defogging nozzles. Blowers are energized by
DEFOG
BLOWER
switch
breaker
on
96-180.
OPERATIONAL
DEFOGGING
BLOWER.
CHECK
-
1. Close DEFOG BLOWER switch
Check defogging blowers operate.
breaker.
2. Open DEFOG BLOWER switch
Check blowers stop operating.
breaker.
--
96-00-00
Page 53/54
BHT-206L1-MM-11
CHAPTER
CONTENTS
Paragraph
Number
97-1
-
97 -
MAINTENANCE
AVIONICS
PROCEDURES
Chapter/Section
Number
Title
Avionics
system
..................................
97-00-00
Page
Number
3
FIGURES
Figure
Number
97-l
97-2
97-3
97-4
97-5
97-6
97-7
97-8
97-9
97-l 0
97-I 1
97-l 2
97-l 3
97-14
97-I 5
97-l 6
97-17
97-18
97-l 9
97-20
97-21
97-22
97-23
Title
Audio system (AUD-251H) (S/N 45154 through 45600). ......................
VHF COMM/NAV system (KX-170B) (S/N 45154 through 45600). ...........
VHF COMM/NAV system (KX-170B) with audio system (AUD-251H) (S/N
45154 through 45600) .......................................................
Transponder
(KT-76) (S/N 45154 through 45600) ...........................
Transponder
(KT-76A) (S/N 45154 through 45600) ..........................
ADF (KR-85) with separate loop and sense antennas(S/N
45154 through
45600) .......................................................................
ADF (KR-85) with combined loop and sense antennas(S/N
45154 through
45600) .......................................................................
ADF-IFR
. . ................................................................
Transponder - IFR ..........................................................
Dual VHF transponders - IFR ..............................................
NAV 1 - IFR ................................................................
NAV 2 - IFR ................................................................
Glideslope - IFR ............................................................
.......................................................
Marker beacon-IFR
.........................................................
Audio system-IFR
Caution light system - IFR ..................................................
....................................................
DC power system -lFR
.....................................................
Compass system -lFR
.....................
Auxiliary speaker system (S/N 45601 and subsequent).
........
KMA-24H Intercommunication
system (S/N 45601 and subsequent).
KT-76A Transponder
(S/N 45601 and subsequent) ..........................
...................................
KR-87 ADF (S/N 45601 and subsequent).
KX-155 NAV/COMM system (S/N 45601 and subsequent). ..................
Page
Number
4
6
7
8
9
10
11
I2
13
14
I5
16
17
18
19
20
21
25
26
27
28
29
30
97-00-00
Page 1/2
BHT-206L1-MM-11
AVIONICS
97-1.
AVIONICS
SYSTEM.
Customer
requirements
vary so extensively
that a basic avionics
system is not provided.
Various
systems
are available
in Bell installed
kits, and will be installed
when ordered
by the
customer.
Manual
coverage
of these systems
is limited
to wiring
diagrams
of each
configuration.
Operational
and maintenance
procedures
are available
from equipment
manufacturers.
Listed below are the different
configurations
that can be installed.
1.
2.
AUD-251H
KX-170B
audio
VHF
system.
COMM/NAV
5.
KT-76
KT-76A
6. KR-85
antennas.
transponder.
with
7.
KR-85
ADF with
sense antenna.
*
VHF transponders
11.
NAV
1-
IFR.
12.
NAV 2 -
IFR.
13.
Glideslope
-
14.
Marker
15.
Audio
16.
Caution
17.
DC power
system
18.
Compass
system
19.
Auxiliary
speaker
20.
KMA-24H
21.
KT-76A
22.
KR-87
23.
KX-155
system.
ADF -
9.
Transponder
-
IFR.
-
IFR.
light
system
-
IFR.
*
system
-
IFR.
with
*
separate
loop
a combined
and sense
loop
and
*S/N 45154
8.
IFR.
IFR.
beacon
system
-
-
IFR.
l
transponder.
ADF
*
Dual
l
3. KX-170B
VHF COMM/NAV
AUD-251H
audio system. *
4.
10.
system.
Intercomm
Transponder.
ADF.
*
system.
l
l
*
*
**
NAV/COMM.
through
l
**
45600
IFR.
“S/N
-
45601
and subsequent
IFR.
97-00-00
Page 3
BHT-206L1-MM-11
ANTENNA
TRANSPONDER
206L1-M-97-4
206-077-050R
Figure
97-4.
Transponder
(KT-76)
97-00-00
Page 8
,
(S/N 45154 through
45600)
BHT-206L1-MM-11
WINDSHIELD
CENTER POST
Figure
97-5.
Transponder
(KT-76A)
(S/N 45154 through
45600)
97-00-00
Page 9
BHT-206L1-MM-11
/
MATCHING
Figure 97-7.
ADF (KR-85) with combined
loop and sense
(S/N 45154 through
45600)
antennas
97-00-00
Page 11
BHT-206L1-MM-11
MARKER RECEIVER
206L1-M-97-14
Figure 97-14.
97-00-00
Page 16
Marker
beacon
-
IFR
BHT-206L1-MM-11
411
206Ll-M-97-21
Figure
97-00-00
Page 26
97-21.
KT-76A Transponder
(S/N 45601 and subsequent)
BHT-206L1-MM-12
CHAPTER
CONTENTS
Paragraph
Number
98-I
98-2
98 -
WIRING
MAINTENANCE
DIAGRAMS
PROCEDURES
Chapter/Section
Number
Title
Wiring diagrams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Wire identification
................................
98-00-00
98-00-00
Page
Number
3
3
FIGURES
Figure
Number
98-I
98-2
98-3
98-4
98-5
98-8
98-7
98-8
98-9
98-10
98-II
98-12
98-13
98-14
98-15
98-16
98-17
98-18
98-19
98-20
98-21
98-22
98-23
98-24
98-25
98-26
98-27
98-28
98-29
98-30
98-31
Title
DC power system simplified wiring diagram .................................
External power circuit ........................................................
Generator power circuit ......................................................
Battery power circuit .........................................................
Auxiliary power circuit .......................................................
Starter and igniter circuits ...................................................
Fuel quantity and fuel pressure indicator systems ...........................
Engine and transmission
temperature indicating system .....................
Tachometer indicating system ...............................................
Caution and warning system .................................................
RPM warning system ........................................................
Interior lighting system .......................................................
Position and anticollision
lights ..............................................
Landing light system .........................................................
Fuel control system ..........................................................
Engine deicing/anti-icing
system .............................................
Governor rpm system ........................................................
Hydraulic control system .....................................................
................................
Defogging blowers...........................~
Turbine outlet temperature indicator system .................................
Hourmeter system ...........................................................
Particle separator purge system .............................................
............................................................
Flight instruments
Engine overspeed ............................................................
Pitot tube heater .............................................................
Component replacement chart ...............................................
ECS system .................................................................
Combustion heater ...........................................................
Bleed air heater ..............................................................
Cargo hook.. ................................................................
................................................................
Pop-out floats
Page
Number
4
5
7
8
IO
II
I3
14
15
I6
I7
18
20
21
22
23
24
25
26
27
28
29
30
31
32
33
46
47
48
49
50
98-00-00
Page 1
BHT-206L1-MM-12
FIGURES
(Cont)
Page
Number
Figure
Number
98-32
96-00-00
Page‘ 2
Engine auto-reignition.....................................................,..
51
I
BHT-206L1-MM-12
WIRING
98-1.
WIRING
DIAGRAMS.
This section contains wiring diagrams for all
basic electrical
circuits
in the helicopter.
Individual
system
wiring
diagrams
are
provided to assist maintenance
personnel in
understanding
the circuits and components
installed
in the
helicopter
and
in
troubleshooting
and tracing of inoperative and
malfunctioning
circuits.
Standard
symbols
have been used where possible.
DIAGRAMS
98-2.
WIRE IDENTIFICATION.
All wires on the systems wiring diagrams are
identified
by codes exactly
as they are
marked in the helicopter.
The code or wire
number indicates
the circuit function,
wire
number,
wire segment
number,
and wire
conductor
size. Wire identification
may be
accomplished
by using the identification
code
listed in Chapter 96.
96-00-00
Page 3
BHT-206L1-MM-12
04
EFFECTIVITY
0
0
3
Helicopters
S/N 45 194 through
4
Helicopters
S/N 45601
45600
and subsequent
206L1-M-98-5
206-075-295T
Figure
98-00-00
Page 10
98-5.
Auxiliary
power
circuit
LOADMETER
FUEL PRESS
206-075-295T
206-064-617
Figure
98-7.
Fuel quantity
and fuel pressure
indicator
systems
98-00-00
Page 13
Figure
98-00-00
Page 14
98-8.
Engine
and transmission
temperature
indicating
system
Figure 98-9.
Figure 98-14.
Figure 98-15.
BHT-206L1-MM-12
Figure
96-16.
Engine
deicing/anti-icing
system
96-00-00
Page 23
BHT-206L1-MM-12
Figure
98-00-00
Page 24
96-17.
Governor
rpm system
BHT-206L1-MM-12
Figure
98-18.
Hydraulic
control
system
98-00-00
Page 25
BHT-206L1-MM-12
DEFOGGING
Figure 98-19.
BLOWER
3
and subsequent.
4
TEMPERATURE
Figure
98-20.
THERMOCOUPLE
Turbine
LOOP
outlet
temperature
RESET
indicator
0
system
98-00-00
Page 27
Figure 98-21.
I
BHT-206L1-MM-12
ON
OFF
SEPARATOR
PURGE SWITCH
206L1-M-98-22
206-075-295N
Figure
98-22.
Particle
separator
purge
system
98-00-00
Page 29
;
BHT-206L1-MM-12
Figure
96-24.
Engine
overspeed
98-00-00
Page 31
BHT-206L1-MM-12
EEI
DIRECTIONAL
GYRO AND
ATTITUDE
INDICATOR
206L1-M-96-25
206-075-295P
Figure
98-00-00
Page 32
96-25.
Pitot tube
heater
206L1-M-98-26-1
206-075-295T
Figure
98-26.
Component
replacement
chart
(Sheet
1 of 13)
98-00-00
Page 33
BHT-206L1-MM-12
LOADMETER
-P962-
6
I
I
AIRFRAME
GROUND
206Ll -M-98-26-2
Figure
98-00-00
, Page 34
98-26.
Component
replacement
chart
(Sheet
2)
BHT-206L1-MM-12
PILOTS
MISCELLANEOUS
ENGINE
CONTROL
DE-ICING
PANEL
SWITCH
I
DIM
I
LIGHT
LIGHT
Figure
98-26.
Component
replacement
chart
(Sheet
3)
98-00-00
Page 35
206L1-M-98-26-5
206-075-295N
Figure
98-26.
Component
replacement
chart
(Sheet
5)
98-00-00
Page 37
BHT-206L1-MM-12
206L1-M-98-26-6
Figure
98-00-00
Page 38
98-26.
Component
replacement
chart
(Sheet
6)
‘
206L1-M-98-26-7
206-075-295T
Figure
98-26.
Component
replacement
chart
(Sheet
7)
98-00-00
Page 39
BHT-206L1-MM-12
-
UPPER
i
3-20
3-20
206L1-M-98-26-8
Figure
98-00-00
Page 40
96-26.
Component
replacement
chart
(Sheet
6)
BHT-206L1-MM-12
COLLECTIVE
SWITCH
BOX
I
I
4
3
L
Figure
98-26.
Component
replacement
chart
(Sheet
9)
98-00-00
Page 41
BHT-206L1-MM-12
’
CAUTION
LIGHTS
I
Figure
98-00-00
Page 42
96-26.
Component
replacement
chart
(Sheet
10)
BHT-206L1-MM-12
LIGHT DIMMING
RELAY
206Ll-M-98-26-11
2Ow75-295P
Figure 98-26.
98-00-00
Page 43
BHT-206L1-MM-12
46154
through 45193
03
04
Figure
98-00-00
Page 44
96-26.
Component
Helicopters S/N 45 194
through 45600
Helicopters S/N 45601
and subsequent
replacement
chart
(Sheet
12)
BHT-206L1-MM-12
LOW ROTOR
MUTE RELAY
Figure
98-26.
Component
replacement
chart
(Sheet
13)
.
98-00-00
Page 45
BHT-206L1-MM-12
Figure
98-00-00
Page 48
98-29.
Bleed air heater
I -
t
Figure
98-30.
Cargo
hook
.
98-00-00
Page 49
BHT-206L1-MM-2
Subject
INDEX -
MAINTENANCE
Paragraph/Table/
Figure Number
Subject
A
-
ADF (KR-85) with combined
loop and sense antennas
(S/N 45154 through 45600) ..........
ADF (KR-85) with separate
loop and sense antennas
(S/N 45154 through 45600) ..........
ADF-IFR
............................
Airspeed indicator ......................
Altimeter ...............................
Anticollision
light .....................
Installation - anticollision
light...............................96-134
Operational check anticollision
light. .................
Removal - anticollision
light .....
Audio system - IFR ..................
Audio system (AUD-251H)(S/N
45154 through 45800) ...............
Auxiliary power circuit ..................
Auxiliary speaker system (S/N
45601 and subsequent).
............
Avionics system .........................
F97-7
F97-6
F97-8
95-l 7
95-18
.98-132
96-l 35
.96-133
F97-15
F97-1
F98-5
F97-19
97-l
B
Battery hot warning system ...........
Operational test - battery
hot warning system ...............
Battery power circuit ...................
Battery relay ...........................
Installation - battery relay ..........
Removal - battery relay ............
Battery relay caution system .........
Operational test - battery
relay caution system ............
Battery system .........................
Installation - battery ................
Maintenance - battery ..............
Removal - battery ..................
Bleed air heater .......................
96-100
96-101
F98-4
96-25
96-27
98-26
.96-102
.96-103
96-21
96-24
96-22
96-23
F98-29
Installation - caution light
panel ..............................
96-78
Operational test - caution
light panel .........................
96-79
Removal - caution light
panel ..............................
96-77
Caution light system - IFR ...........
F97-16
Circuit breakers ........................
96-l 7
Installation - circuit breakers .......
96-19
Removal - circuit breakers .........
96-18
Clock ...................................
95-47
Cockpit light ...........................
96-l 19
Installation - cockpit light ..........
96-121
Removal - cockpit light and
base..............................96-120
Combustion heater ....................
F98-28
Compass system - IFR ..............
F97-18
Component replacement chart ........
F98-26
Control boost/hydraulic
system
switch ..............................
-96-177
Control panels - electrical .............
96-13
Inspection - control panels .........
96-15
Installation - control panels .........
96-l 6
Removal - control panels ...........
96-14
D
DC indicator systems ...................
DC loadmeter ..........................
DC power system simplified
wiring diagram .......................
DC power system - IFR ..............
DC power systems .....................
Defogging blowers ....................
Defogging blowers ....................
Operational check defogging
blower .................
Dual tachometer ........................
Operational check - dual
tachometer ........................
Dual VHF transponders - IFR ........
98-65
95-44
F98-1
F97-17
96-20
F98-19
96-179
96-180
95-24
95-25
F97-10
E
C
Cabin lighting .........................
Cargo hook ............................
Caution and warning system ..........
Caution and warning system ...........
Caution light panel .....................
Paragraph/Table/
Figure Number
96-124
F98-30
F98-10
96-75
96-76
ECS system ...........................
Electrical power loading .................
Electrical power - DC ..................
Electrical systems .......................
F98-27
96-5
96-6
96-1
1-00-00
Index MM 1
BHT-206L1-MM-2
INDEX Subject
Paragraph/Table/
Figure Number
Engine and transmission
temperature
indicating
system ...............................
Engine auto-reignition
.................
Engine chip detector caution
system .............................
Operational test - engine
chip detector caution
system............................
96-105
Engine control and accessories
systems.............................
96-148
Engine deicing/anti-icing
switch ......
Installation - engine deicing/
anti-icing switch .................
Removal - engine deicing/
anti-icing switch ..................
Engine deicing/anti-icing
system.. ..........................
Engine deicing/anti-icing
system .............................
Operational check - engine
deicing/anti-icing
system .........
Engine hourmeter ......................
Operational check - engine
hourmeter .........................
Engine oil temperature/pressure
indicator .............................
Bleeding pressure gage line
- engine oil temperature/
pressure indicator .................
Operational check - engine
oil temperature/pressure
indicator ...........................
Engine out warning system .............
Operational test - engine
out warning system ................
Engine overspeed .....................
Engine rpm sensor .....................
Installation - engine rpm
sensor .......
......................
Removal - engine rpm
sensor .............................
Engine torquemeter
....................
Bleeding - engine
torquemeter gage pressure
line ................................
Operational check - engine
torquemeter
.......................
Equipment list ...........................
1-00-00
Index MM 2
MAINTENANCE
F98-8
F98-32
-98-104
96-163
.96-165
96-164
..F98-16
-96-161
96-162
95-45
95-46
95-28
95-30
95-29
96-80
96-81
F98-24
96-82
96-84
98-83
95-37
95-39
95-38
96-2
(Cont)
Paragraph/Table/
Figure Number
Subject
Equipment list - electrical .............
T96-1
Equipment location - electrical
F96-1
.......
Exterior lighting system ..............
.96-125
External electrical power ................
96-7
External power circuit ..................
F98-2
External power receptacle ..............
96-29
Installation - external power
receptacle .........................
96-31
Removal - external power
receptacle ..............
96-30
..........
External power relay ...................
96-32
Installation - external power
relay ...............................
96-34
Removal - external power
relay ...............................
96-33
External power system .................
96-28
F
Field-igniter
relay .......................
Installation - field-igniter
relay ...............................
Removal - field-igniter
relay .......
Flight controls system ................
Operational check - flight
controls system ..................
Flight instruments .....................
Flight instruments ......................
Free air temperature indicator ..........
Maintenance - free air
temperature indicator ..............
Fuel boost pumps .....................
Operational check - fuel
boost pumps .....................
Fuel control system ...................
Fuel dump switch .....................
Installation -fuel
dump
switch ...........................
Removal - fuel dump switch ......
Fuel dump valve .....................
Operational check - fuel
dump valve ......................
Fuel filter caution system ............
Operational test - fuel filter
caution system ...................
Fuel flow switch ......................
Fuel low caution system ..............
Fuel pressure indicator .................
Operational check - fuel
pressure indicator .................
96-58
96-60
96-59
.96-172
.96-173
F98-23
95-10
95-48
95-49
96-149
.96-150
F98-15
96-155
.96-157
96-156
.96-153
.96-154
.96-110
96-111
.96-114
.96-115
95-35
95-36
BHT-206L1-MM-2
INDEX -
MAINTENANCE
Paragraph/Table/
Figure Number
Subject
Fuel pump caution system ...........
Operational test - fuel pump
caution system ..................
Fuel quantity and fuel pressure
indicator systems ....................
Fuel quantity indicator ..................
Fuel quantity system ...................
Calibration procedure - fuel
quantity system ....................
Description - fuel quantity
system .............................
Fuel valve ............................
Operational check - fuel
valve ...........................
Fuel valve switch .....................
Installation - fuel valve
switch ...........................
Removal - fuel valve switch ......
.96-112
.96-113
F98-7
95-34
96-72
96-74
98-73
.96-151
..96-152
.96-158
Paragraph/Table/
Figure Number
Subject
H
Hourmeter system .....................
HS strobe power supply
(flasher unit) ........................
Installation - HS strobe
power supply .....................
Removal - HS strobe power
supply ............................
Hydraulic bypass solenoid. ...........
Installation - hydraulic
bypass solenoid .................
Removal - hydraulic bypass
solenoid ........................
Hydraulic control system ..............
F98-21
98-136
96-138
96-137
.96-174
.96-176
..96-175
F98-18
I
.,96-160
96-159
G
-
(Cont)
95-26
Gas producer tachometer ..............
Operational check - gas
..............
95-27
producer tachometer
96-36
Generator ..............................
96-37
Inspection - generator ..............
Generator failure caution
-.96-116
system ............................
F98-3
Generator power circuit ................
96-46
Generator reset switch .................
Installation - generator reset
96-48
switch .............................
Removal - generator reset
96-47
switch .............................
98-49
Generator shunt ........................
Installation - generator
96-51
shunt ..............................
96-50
Removal - generator shunt .........
96-35
Generator system ......................
F97-13
Glideslope - IFR .....................
96-l 66
Governor actuator .....................
Operational check 96-l 67
governor actuator .................
.96-188
Governor rpm switch .................
Installation - governor
.98-170
control switch ....................
Removal - governor control
..96-16 9
switch ..........................
F98-17
Governor rpm system .................
96-61
Igniter ..................................
95-l 9
Inclinometer ............................
Instrument and control panel
lighting..............................96-122
Operational check instrument and control
96-123
panel lighting .....................
F95-1
Instrument panel .......................
Instrument panel maintenance
95-7
practices ..............................
Installation - instrument
..95- 9
panel ..............................
95-8
Removal - instrument panel ........
F95-2
Instrument piping installation ...........
95-l
Instrument system .......................
Instruments maintenance
95-3
practices ..............................
.95-5
Inspection - instruments .............
............
.95-8
Installation - instruments
..............
.95-4
Removal - instruments
............
T95-1
Instruments troubleshooting
F98-12
Interior lighting system ................
.96-118
Interior lighting system ...............
K
KMA-24H Intercommunication
system (S/N 45601 and
subsequent). ........................
KR-87 ADF (S/N 45601 and
subsequent). ........................
KT-76A Transponder
(S/N
............
45601 and subsequent).
F97-20
F97-22
F97-21
1-00-00
Index MM 3
BHT-206L1-MM-2
INDEX -
MAINTENANCE
Paragraph/Table/
Figure Number
Subject
KX-155 NAV/COMM system
N 45601 and subsequent)
(S/
. . . . . . . . . . F97-23
L
Landing light relays ..................
.96-142
Installation - landing light
relays.............................
96-144
Removal - landing light
relays .............................96-143
Landing light switch ..................
.96-145
Installation - landing light
switch ............................
96-147
Removal - landing light
switch ...........................
.96-146
Landing light system ..................
F98-14
Landing lights ........................
.96-139
Operational check - landing
lights ...........................
..96-14 1
Replacement - landing
lights ...........................
..96-14 0
Lighting system troubleshooting
96-4
.......................
Lighting Systems ......................
96-117
Lighting systems
troubleshooting
T96-3
......................
Line control relay .......................
96-43
Installation - line control
relay ...............................
96-45
Removal - line control relay .......
96-44
Low rotor rpm caution system ..........
96-85
Operational test - low rotor
rpm caution system ................
96-86
M
Marker beacon - IFR .................
Miscellaneous
electrical
components ...........................
Inspection - miscellaneous
electrical components
.............
Installation - miscellaneous
electrical components
.............
Removal - miscellaneous
electrical components
.............
Miscellaneous
electrical system ......
Miscellaneous
instruments
.............
F97-14
96-9
96-12
96-l 1
96-l 0
96-l 78
95-43
N
NAV 1 NAV 2 -
IFR .........................
IFR .......................
1-00-00
Index MM 4
F97-11
..F97-12
(Cont)
Paragraph/Table/
Figure Number
Subject
Navigation
instruments
95-20
.................
0
Overhead console panel
(typical) ..............................
F96-2
P
Particle separator ....................
.96-171
Particle separator purge system ...... F98-22
Pitot tube heater ......................
F98-25
Pitot-static system ......................
95-11
Cleaning - pitot-static
system .............................
95-13
Inspection - pitot-static
system .............................
95-14
Installation - pitot tube and
static ports ........................
95-15
Removal - pitot tube and
static ports ........................
95-12
Testing - pitot-static system .......
95-16
Pop-out floats .........................
F98-31
Position and anticollision
lights. .......
F98-13
Position lights .........................
96-126
Installation - position light ........
.96-128
Installation - tail light ..............
96-130
Operational check - position
lights ...........................
..96-13 1
Removal - position light ..........
96-127
Removal - tail light ...............
.96-129
Propulsion instruments .................
95-23
R
Rotor rpm sensor .......................
Installation - rotor rpm
sensor .............................
Removal,rotor rpm sensor
RPM warning system ..................
96-87
.......
96-89
96-88
F98-11
S
Standby magnetic compass ............
Calibration - standby
magnetic compass .................
Starter ..................................
Starter and igniter circuits ..............
Starter relay ............................
Installation - starter relay ...........
Removal - starter relay .............
Starter switch ..........................
Installation - starter switch .........
95-21
95-22
96-54
F98-6
96-55
96-57
96-56
96-62
96-84
BHT-206L1-MM-2
INDEX -
i
MAINTENANCE
Paragraph/Table/
Figure Number
Subject
Removal - starter switch.. . . . . . . . . . . 96-63
Starter-generator
brush wear.. . . . . . . . . . F96-3
Starter/generator/igniter
. . . . . . . . . . . 96-3
systems - troubleshooting
Starter/generator/igniter
systems troubleshooting
chart.................................T96-2
Starter-igniter
system . . . . . . . . . . . . . . . . . . 96-52
Operational check - starter
system circuitry.. . . . . . . . . . . . . . . . . . . 96-53
T
,
-
Tachometer generators..
. . . . . . . . . . . . . . . 96-69
Installation - tachometer
generators..
. . . . . . . . . . . . . . . . . . . . . . . 96-71
Removal - tachometer
generators..
. . . . . . . . . . . . . . . . . . . . . . . 96-70
Tachometer indicating system.. . . . . . . . . F98-9
Tail rotor gearbox chip detector
caution system.. . . . . . . . . . . . . . . . . . . . . 96-108
Operational test - tail rotor
gearbox chip detector
caution system . . . . . . . . . . . . . . . . . . .96-109
Temperature
bulbs . . . . . . . . . . . . . . . . . . . . . 96-66
Installation - temperature
bulbs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 96-68
Removal - temperature
bulbs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 96-67
Transmission
chip detector
caution system. . . . . . . . . . . . . . . . . . . . . .96-106
Operational test transmission
chip detector
caution system . . . . . . . . . . . . . . . . . . .96-l 07
Transmission
oil pressure
caution system.. . . . . . . . . . . . . . . . . . . . . . 96-90
Operational test transmission
oil pressure
caution system . . . . . . . . . . . . . . . . . . . . 96-91
Transmission
oil pressure
switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 96-92
Installation - transmission
oil pressure switch . . . . . . . . . . . . . . . . 96-94
oil
Removal - transmission
pressure switch.. . . . . . . . . . . . . . . . . . . 96-93
Transmission
oil temperature
caution system.. . . . . . . . . . . . . . . . . . . . . . 96-95
Operational test transmission
oil
(Cont)
Paragraph/Table/
Figure Number
Subject
temperature caution
system.............................
96-96
Transmission
oil temperature
switch . . . . . . . . . . . . . . . . . , . . . . . . . . , . . . . . 96-97
Installation - transmission
oil temperature switch . . . . . . . . . . . . . 96-99
Removal - transmission
oil
temperature switch . . . . . . . . . . . . . . . . 96-98
Transmission
oil temperature/
pressure indicator.. . . . . . . . . . . . . . . . . . . 95-31
Bleeding pressure gage line
- transmission
oil
temperature/pressure
indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . 95-33
Operational check transmission
oil
temperature/pressure
indicator . . . . . . . . . . . . . . . . . . . . . , . . . . . 95-32
Transmitter and test set
connection . . . . . . . . . . . . . . . . . . . . . , . . . . . F96-4
Transponder
(KT-76) (S/N
45154 through 45600) . . . . . . . . . , . . . . . F97-4
Transponder
(KT-76A) (S/N
45154 through 45600) . . . . . . . . . . . . . . . F97-5
Transponder - IFR . . . . . . . . . . . . . . . . . . . . F97-9
Troubleshooting
instruments
. . . . . . . . . . . . 95-2
Turbine outlet temperature
indicator . . . . . . . . . . . . . . . . . . . . . . . , . . . . . 95-40
Maintenance - turbine outlet
temperature indicator..
. . . . . . . . . . . . 95-41
Operational check - turbine
outlet temperature indicator
and circuitry . . . . . . . . . . . . . . . . . . . . . . . 95-42
Turbine outlet temperature
indicator system . . . . . . . . . . . . . . . , . . . . F98-20
V
VHF COMM/NAV system (KX1708) (S/N 45154 through
45600) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
VHF COMM/NAV system (KX170B) with audio system
(AUD-251H)
(S/N 45154 through 45600) . . . . . . . . .
Voltage regulator.. . . . . . . . . . . . . . . . . . . . . .
Adjusting - voltage regulator . . . . . . .
Inspection and repair voltage regulator . . . , . . . . . . . . . . . . . .
F97-2
F97-3
96-38
96-42
96-40
1-00-00
Index MM 5