REFERENCE FM0300705 ISSUE 1.0 SKILL TEMPLATE FOR STATIC STRESS REPORTS NB PAGES 79 DATE 15 Nov 2011 ATA 53 S16-18 ATA CHAPTER A/C SECTION A/C SUB ASSEMBLY A/C PART ENGINE APPLICABILITY METALLIC STATIC STRENGTH ANALYSIS TYPE A/C APPLICABILITY* *Indicate the last A/C-Type-Series WV, which had an impact on this report. For a Post Mod, indicate it in the title (Post Mod XXXXX) NAME FUNCTION PREPARED BY David Conde Algueró Stress Engineer APPROVED BY Irene Valadés Egido Stress Chief Engineer AUTHORIZED BY Irene Valadés Egido Stress Chief Engineer DATE SIGNATURE © EDDM S.L. 2011 . All rights reserved. Confidential and proprietary document. This document and all information contained herein is the sole property of EDDM S.L.. No intellectual property rights are granted by the delivery of this document or the disclosure of its content. This document shall not be reproduced or disclosed to a third party without the express written consent of EDDM S.L..This document and its content shall not be used for any purpose other than that for which it is supplied. EDDM Plaza Carlos Trías Bertrán 4 28020 MADRID SPAIN +34 91 491 2868 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 SUMMARY The following document describes the M-100 aircraft fuselage static justification between frame 39 and frame 54 from stringer 0 to stringer 40 of the right zone. Skin panels, frames, window panels, skin-stringer, shear ties joints and lugs have been analysed. A detailed finite element model has been developed to analyse window panels. In conclusion, from a static point of view, the airframe has been justified by showing all RF's greater than 1 and FF's less than 0. The critical points identified on this area are the following ones: R.F. = 1.00 Load case / Load loop = 17501 Criteria = Global Buckling Location = Skin panel Strg 10-11 Frame 56-57 R.F. = 1.00 Load case / Load loop = 17501 Criteria = Bolt Shear Location = Stringer 11 R.F. = 1.01 Load case / Load loop = 17507 Criteria = Strenght Location = Stringer 14 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE ii SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 LOCATION This document will consider right side of sections S16 and S18 of M-100 aircraft between frame 39 and frame 54 from stringer 0 to stringer 40 of the right zone. © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE iii SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 LIST OF DISTRIBUTION DEPARTMENT/ COMPANY NAME P.O. BOX COVER PAGE ONLY NOTE NOTE WITH WITHOUT ATTACHATTACHMENT MENT NO. OF COPIES Agreement for Airbus distribution © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE iv SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RECORD PF REVISIONS ISSUE DATE EFFECT ON PAGE REASONS FOR REVISION PARA © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE v SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 TABLE OF CONTENTS 1 2 General Notes .................................................................................................................... 1-1 1.1 Introduction ................................................................................................................ 1-1 1.2 FAR/CS Regulations .................................................................................................. 1-1 1.3 A/C Data Basis and Main Typical Definition or Options .............................................. 1-1 1.4 Sub-Component Description ...................................................................................... 1-2 1.4.1 Skin panels.......................................................................................................... 1-2 1.4.2 Frames ................................................................................................................ 1-3 1.4.3 Stringers .............................................................................................................. 1-3 1.4.4 Window panels .................................................................................................... 1-3 1.4.5 Roller track .............................................................. ¡Error! Marcador no definido. 1.4.6 Cargo floor beam..................................................... ¡Error! Marcador no definido. 1.4.7 Shield wall ............................................................... ¡Error! Marcador no definido. 1.4.8 Corner fittings .......................................................... ¡Error! Marcador no definido. 1.4.9 Struts....................................................................... ¡Error! Marcador no definido. 1.4.10 Skin and stringer joints ........................................................................................ 1-4 1.4.11 Shear ties ............................................................................................................ 1-4 1.5 Main Drawings Reference and Modification Applicability ............................................ 1-4 1.6 References................................................................................................................. 1-5 1.6.1 Documents .......................................................................................................... 1-5 1.6.2 Software .............................................................................................................. 1-5 1.6.3 Storage of Data ................................................................................................... 1-5 1.7 Abbreviations and Units ............................................................................................. 1-5 1.8 Partial Testing ............................................................................................................ 1-6 Analysis General Requirements....................................................................................... 2-1 2.1 Load Cases and associated Criteria ........................................................................... 2-1 2.2 Main Hypotheses and Methods .................................................................................. 2-1 2.3 Material Properties ..................................................................................................... 2-3 2.4 Fastener Properties .................................................................................................... 2-3 2.5 FEM Description (Global and Local) ........................................................................... 2-3 2.6 Applicable factors ....................................................................................................... 2-4 3 Reserve Factors Summary ............................................................................................... 3-1 4 Skin 4.1 4.1.1 Geometric Data and Strength Characteristics ............................................................ 4-1 Skin elements...................................................................................................... 4-1 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE vi SKILL TEMPLATE FOR STATIC STRESS REPORTS 4.1.2 5 7 DATE 15 Nov 2011 Stringer ............................................................................................................... 4-1 4.2 Sizing and Typical Selected Load Cases.................................................................... 4-2 4.3 Specific Post-Processing Hypotheses, Methods and Tools ........................................ 4-2 4.3.1 Local buckling ..................................................................................................... 4-2 4.3.2 Panel strength ..................................................................................................... 4-3 4.3.3 Rivet local buckling.............................................................................................. 4-3 4.3.4 Global Buckling ................................................................................................... 4-3 4.4 FEM Detailed Description ........................................................................................... 4-4 4.5 Calculations (Limit Loads and Ultimate Loads) ........................................................... 4-1 Stringer 5.1 Geometric Data and Strength Characteristics ............................................................ 5-1 5.2 Sizing and Typical Selected Load Cases.................................................................... 5-1 5.3 Specific Post-Processing Hypotheses, Methods and Tools ........................................ 5-1 5.3.1 6 REFERENCE FM0300705 ISSUE 1.0 Local Crippling .................................................................................................... 5-1 5.4 FEM Detailed Description ........................................................................................... 5-1 5.5 Calculations (Limit Loads and Ultimate Loads) ........................................................... 5-2 Window panels .................................................................................................................. 5-3 6.1 Geometric Data and Strength Characteristics ............................................................ 6-1 6.2 Sizing and Typical Selected Load Cases.................................................................... 6-1 6.3 Specific Post-Processing Hypotheses, Methods and Tools ........................................ 6-1 6.3.1 Panel strength ..................................................................................................... 6-1 6.3.2 Global Buckling ................................................................................................... 6-1 6.4 FEM Detailed Description ........................................................................................... 6-1 6.5 Calculations (Limit Loads and Ultimate Loads) ........................................................... 6-2 Frame 7.1 Geometric Data and Strength Characteristics ............................................................ 7-1 7.1.1 Frame web .......................................................................................................... 7-1 7.1.2 Frame chord ........................................................................................................ 7-1 7.2 Sizing and Typical Selected Load Cases.................................................................... 7-1 7.3 Specific Post-Processing Hypotheses, Methods and Tools ........................................ 7-1 7.3.1 Web Frame Buckling ........................................................................................... 7-1 7.3.2 Crippling .............................................................................................................. 7-2 7.3.3 Strength .............................................................................................................. 7-2 7.4 FEM Detailed Description ........................................................................................... 7-2 7.5 Calculations (Limit Loads and Ultimate Loads) ........................................................... 7-3 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE vii SKILL TEMPLATE FOR STATIC STRESS REPORTS 8 DATE 15 Nov 2011 Joints 8.1 9 REFERENCE FM0300705 ISSUE 1.0 Geometric Data and Strength Characteristics ............................................................ 8-1 8.1.1 Bearing Skin-Stringer .......................................................................................... 8-1 8.1.2 Shear Tie Joint .................................................................................................... 8-1 8.2 Sizing and Typical Selected Load Cases.................................................................... 8-1 8.3 Specific Post-Processing Hypotheses, Methods and Tools ........................................ 8-1 8.3.1 Skin-Stringer ....................................................................................................... 8-1 8.3.2 Shear tie joint ...................................................................................................... 8-3 8.4 FEM Detailed Description ........................................................................................... 8-4 8.5 Calculations (Limit Loads and Ultimate Loads) ........................................................... 8-5 Element or Junction j Calculation ............................................ ¡Error! Marcador no definido. 9.1 Geometric Data and Strength Characteristics ............................................................ 9-1 9.2 Sizing and Typical Selected Load Cases.................................................................... 9-2 9.3 Specific Post-Processing Hypotheses, Methods and Tools ........................................ 9-2 9.4 FEM Detailed Description ........................................................................................... 9-6 9.5 Calculations (Limit Loads and Ultimate Loads) ........................................................... 9-7 APPENDIX A ACD Sheets ........................................................................................................ 1 APPENDIX B 1 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE viii SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 1 General Notes 1.1 Introduction The following document describes the M-100 aircraft fuselage static justification of the section 16-18 between frame 39 and frame 54, from stringer 0 to stringer 40 in the right zone. The following components were analysed: skin panels, frames, stringers, window panels, skin and stringer joints, shear ties-skinframes-stringers joints and lugs. 1.2 FAR/CS Regulations The applicable FAR/CS airworthiness regulations paragraphs for which this report shows compliance with are: Paragraph Title MOC CS25.0305 Strength and deformation 2 CS25.0307 Proof of Structure 2 1.3 A/C Data Basis and Main Typical Definition or Options A/C type: Data basis for design references: Weight variant: MTOW: MLW: MZFW: Engines: Loads Data basis: M-100 From WV000 to WV001 68200 kg 52400 kg 50600 kg RDW and DMF © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 1-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 1.4 Sub-Component Description The components analysed in this document are: skin panels, frames, stringers, window panels, skin and stringer joints, shear ties joints and lugs. 1.4.1 Skin panels Skin panels receive the pressurization loads. © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 1-2 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 1.4.2 Frames Frames keep shape of the fuselage and support loads from skin panels. 1.4.3 Stringers Stringers stiffen skin panel to keep them out from buckling modes. 1.4.4 Window panels These panels stiffen the window frame. © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 1-3 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 1.4.5 Skin and stringer joints Skin and stringer joints fasten both elements. 1.4.6 Shear ties joints Shear ties transfer loads from skin panels to frames and are joint to frames, stringers and skin. 1.4.7 Lugs Lugs support the loads of the passage deck. 1.5 Main Drawings Reference and Modification Applicability N/A © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 1-4 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 1.6 References 1.6.1 Documents Nº TITLE REFERENCE ISSUE [1] Analysis and design of flight vehicle structures E.F. Bruhn [2] Airframe Structural design M.C.Y Niu [3] Handbook of structural stability Herbert Becker [4] ESDU 91008, Strength of Lugs [5] Static Strength Analysis of Pin-loaded Lugs [6] [7] ESDU 75034, Flat square plates with central circular hole ESDU 75035, Initial buckling of square plates in shear with central [8] Nota Técnica Materiales Metálicos EDDM Iss 2 [9] Nota Técnica Uniones EDDM Iss 2 Ekvall, J.C flanged circular hole 1.6.2 Software Nº SOFTWARE VERSION DEVELOPER [S1] Optistruct 2019 Altair 1.6.3 Storage of Data Loads are been extracted from ‘GFEM_M100_SECC_16_18_Iss4.op2’. A DFEM was carried out to calculate buckling in the window area and the results are storage in ‘Launcher.h3d’. 1.7 Abbreviations and Units Units defined along this technical note are: Mass kg (Tn in FEM as required for coherence) Length mm Forces N Moments N·mm Stress N / mm2 Strain m/m Pressure N / mm2 Flow N/mm Tensile modulus MPa The rest of combination of the defined units unless otherwise stated. GFEM: Global Finite Element Model DFEM: Detailed Finite Element Model FF: Fitting Factor RF: Reserve Factor © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 1-5 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 UL: Ultimate Load LL: Limit Load Ftu: Ultimate tensile strength E: Tensile modulus N/A: Not applicable 1.8 Partial Testing N/A © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 1-6 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 2 Analysis General Requirements Three load sources were considered Pressure load: A pressure of 0.1 MPa was applied to each skin element. Aerodynamic load: These mechanical loads were produced by the aircraft's flight manoeuvres. Thermal load: These loads were produced by the thermal changes on account of the different aircraft stages. Two case were set, hot (70 ºC) and cold (-55 ºC). The reference temperature was set in 20 ºC. 2.1 Load Cases and associated Criteria GFEM Nomenclature Description 17501 2P Load Case 17502 Aerodynamic Load Case 17503 Temperature Cold -55 ºC 17504 Temperature Hot 70 ºC 17505 Temperature Cold + Pressure + Aerodynamic 17506 Temperature Hot + Pressure + Aerodynamic 17507 Temperature Hot + Pressure + Aerodynamic 17508 Temperature Cold + Pressure + Aerodynamic 17509 Temperature Hot + Pressure + Aerodynamic 17510 Temperature Cold + Pressure + Aerodynamic 17511 Temperature Hot + Pressure + Aerodynamic 17512 Temperature Cold + Pressure + Aerodynamic 27500 Temperature Cold + Pressure + Aerodynamic 2.2 Main Hypotheses and Methods The calculation methodology used to analyse all elements will be described from paragraph 4 and following sections. References used are in paragraph 1.6.1. © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 2-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 The next failure modes will be analysed: STABILITY Local buckling Skin panels Stringers Web frames Inter rivet Windows Crippling Stringers Frames Global Buckling Skin/Stringer STRENGTH Skin/Stringer Window panels Flange frame Web frame Joints Bearing Skin panel-Stringer Shear tie-Skin-Frame-Stringer Shear Skin panel-stringer-frame Shear tie-Skin-Frame-Stringer Shear out Skin panel-stringer-frame Shear tie-Skin-Frame-Stringer Tension Shear tie-Skin-Frame-Stringer Pull through Shear tie-Skin-Frame-Stringer Combined Shear and Tension Shear tie-Skin-Frame-Stringer Tension through the hole Shear tie-Skin-Frame-Stringer Lugs Oblique Loading Permanent deformation The main general hypotheses considered for all components in this document are: This analysis is valid for small strains. The plastic regime shall not be considered. The support condition to calculate all constants of allowable load has been considered as the most unfavorable in each case. © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 2-2 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 2.3 Material Properties Next table shows the material properties used in this stress report. The values are extracted from [Ref 8]. Material E[MPa] Al2024 T3511 Plate Al2024 T3511 Extrude Ti 6Al 4V αβ Annealed Plate 70000 70000 0.3 0.3 [1E-06*1/deg.C] 22.0 22.0 Ftu (L) [MPa] 427 427 Fsu [MPa] 460 460 Fbru (e/D=2.0) [MPa] 815 688 9.5 934 934 1804.1 110300 0.31 2.4 Fastener Properties The properties of rivets NASM 20470 are extracted from 1.6.1 table in [Ref 9]. The diameter is 5.58 mm. Ftu [MPa] 6560 Fsu [MPa] 655 2.5 FEM Description (Global and Local) A GFEM were developed to calculate internal forces of all components of the fuselage sections to be analysed in this document. These forces are required to calculate the failure modes described in 2.2. © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 2-3 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 2.6 Applicable factors Describe here all design and regulations factors used for analysis © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 2-4 Indicate hereafter a summary of the Reserve Factors calculated in the stress report. The following table should be used. PAGE DESCRIPTION MATERIAL LOAD CASE STRESS1 STRAIN1 FORCE1 Skin panel Strg 10-11 Frame 56-57 Aluminium 2024 T3511 17501 St Stringer 14 Aluminium 2024 T3511 17507 St Strg 10-11 Frame 56-57 Stringer 15 17511 St St Aluminium 2024 T3511 17501 St Aluminium 2024 T3511 17501 St Stringer 14 Aluminium 2024 T3511 17507 St Window Panel Frame 45-46 Aluminium 2024 T3511 27500 St Aluminium 2024 T3511 27500 St Aluminium 2024 T3511 17505 - Window Rod Frame 45-46 Window Frame 45-46 Stringer 10 Aluminium 2024 T3511 17501 F Stringer 11 NASM2047 17501 F 475.96 MPa 81.03 MPa 162.89 MPa 159.73 MPa/172.58 MPa 13.81 MPa 299.78 MPa 422.27 MPa 351.34 MPa 310.35 MPa 8836.32 N 8855 N REMARKS 1.05 Local Buckling 9.37 Local Buckling 6.36 Inter-rivet buckling 1.60 Crippling 169.32 MPa 514.78 MPa 1.00 Global Buckling T 427 MPa 1.42 Strength T 427 MPa 1.01 Strength T 427 MPa 1.21 Strength T 427 MPa 1.37 Strength - 1.52 Buckling 1.64 Bearing 1.00 Bolt Shear 2.13 Shear out 1.19 Buckling -0.49 Crippling T S C C C S C C B S Stringers Aluminium 2024 T3511 - - 13388.48 N - Aluminium 2024 T3511 17501 St 169.48 MPa S Frame 56 Aluminium 2024 T3511 17503 St 96.54 MPa C 139.88 MPa 203.13 MPa 4464.10 MPa 516.10 MPa 262.00 MPa 14500.48 N 8836.32 N 28562.68 N 202.08 MPa 189.40 MPa DATE 15 Nov 2011 PAGE 3-1 RF/FF Web Frame 54 Strain = Str, Stress = St, Force = F 2 Units are SI: Stress in N/mm , Force in N, Shear Flow in N/mm, Moment in Nmm 3 Kind of Loading: B = Bearing, Bn = Bending, C = Compression, S = Shear, T = Tension 2 ALLOWABLE VALUE2 REFERENCE FM0300705 17507 25.63 MPa 172.58 MPa KIND OF LOADING3 ISSUE 1.0 Aluminium 2024 T3511 Skin panel Strg 11 Frame 56-57 Skin panel Strg 10-11 Frame 56-57 1 Aluminium 2024 T3511 APPLIED VALUE2 SKILL TEMPLATE FOR STATIC STRESS REPORTS © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 3 Reserve Factors Summary . DESCRIPTION MATERIAL LOAD CASE Frame 55 Aluminium 2024 T3511 17507 STRESS4 STRAIN1 FORCE1 St Frame 54 Aluminium 2024 T3511 17501 St Joint SHTI-Stringer Frame 45-90º Joint SHTI-Stringer Frame 45-270º Joint SHTI-Skin Frame 45-90º Joint SHTI-Skin Frame 45-90º Aluminium 2024 T3511 17501 F NASM2047 17501 F NASM2047 17501 F NASM2047 17501 F Joint SHTI-Skin Frame 45-270º NASM2047 17501 F Lug+bar right side Al2024 T3511 17503 F Lug+bar left side Al2024 T3511 17503 F Shear tie-Stringer Al2024 T3511 - - Shear tie Al2024 T3511 - - APPLIED VALUE5 KIND OF LOADING6 ALLOWABLE VALUE2 RF/FF REMARKS 173.66 MPa 169.48 MPa T 427 MPa -0.59 Strength 460 MPa -0.63 Strength 7.51 Bearing 12.41 Shear 18.98 Tension 24.10 Pull through 2.67 Combined ShearTension 74.61 Oblique 74.49 Oblique Permanent Deformation 5.33 Shear out 1.83 Tension through the hole 133.00 N 711.46 N 466.67 N 466.67 N 465.03 N 129.87 N T B S T T T S 834.20 N T 834.20 N T 5355.39 N 2677.70 N - 5355.39 N 8855 N 8855 N 11248.91 N 8855 N 8855 N 62247.10 N 62139.80 N 28562.68 N 4913.916 N SKILL TEMPLATE FOR STATIC STRESS REPORTS © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE DATE 15 Nov 2011 Strain = Str, Stress = St, Force = F 2 Units are SI: Stress in N/mm , Force in N, Shear Flow in N/mm, Moment in Nmm 6 Kind of Loading: B = Bearing, Bn = Bending, C = Compression, S = Shear, T = Tension 5 REFERENCE FM0300705 ISSUE 1.0 PAGE 3-2 4 . SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 4 Skin The skin has longitudinally riveted stiffeners called stringers. With frames, the skin is divided in elemental panels. This part is made of Al2024 T3511. 4.1 Geometric Data and Strength Characteristics 4.1.1 Skin elements The skin elements consist of a stiffener and two panels. Panel dimensions are as follows a [mm] b [mm] t [mm] r [mm] 500 149.1 3.2 1895 4.1.2 Stringer The Stringers are cane-shaped with a semicircle in the upper part. This part is made of Al2024 T3511. b2 b3 b1 Stringer dimensions are as follows a [mm] b1 [mm] b2 [mm] b3 [mm] t [mm] r [mm] 500 22 25 16.6 3.5 1895 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 4-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 4.2 Sizing and Typical Selected Load Cases The sizing load case is 17501 and the critical failure mode is Global Buckling with RF value of 1.00. 4.3 Specific Post-Processing Hypotheses, Methods and Tools The panels are made up of half the length of the skin section on both sides of the stringer and the stringer itself. Element reference system was been considered. Panels with short edge clamped and long edge hinged were been considered. 4.3.1 Local buckling Allowed values for calculating RF’s were been calculated using [Ref 1] Where Fc [MPa]: Kc: : t [mm]: b [mm]: Allowed compression buckling value Buckling constant from [Ref 1] charts Poisson’s ratio Panel thickness Panel width Where Fs [MPa]: Ks: : t [mm]: b [mm]: Allowed shear buckling value Shear buckling constant from [Ref 1] charts Poisson’s ratio Panel thickness Panel width Where RFLB: FC [MPa]: Fs [MPa]: T [MPa]: S [MPa]: RF local buckling Allowed compression buckling value Allowed shear buckling value Axial stress Shear stress © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 4-2 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 4.3.2 Panel strength Von Mises’s stress were been used Where VM,pi [MPa]: x [MPa]: y [MPa]: [MPa]: Von Mises’s stress Stress in the x-direction of the element Stress in the y-direction of the element Shear stress RFVM: VM,p1[MPa]: VM,p2[MPa]: 1[MPa]: Strength RF Von Mises’s stress panel 1 Von Mises’s stress panel 2 Stringer axial stress Where 4.3.3 Inter Rivet local buckling Allowed values for calculating RF’s were been calculated using [Ref 1] Where Fir [MPa]: c: t [mm]: s [mm]: Allowed rivet local buckling fixing coefficient Panel thickness Pitch Fir[MPa]: C[MPa]: Allowed rivet local buckling Panel compression stress Where 4.3.4 Global Buckling The objective is to calculate the column allowed value of the assembly, 2 panels from the skin and a stringer. Allowed values for calculating RF’s were been calculated using [Ref 1]. © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 4-3 SKILL TEMPLATE FOR STATIC STRESS REPORTS Where RFGB [MPa]: PCO [MPa]: Fps1 [MPa]: Fps2 [MPa]: Pc [MPa]: fs1 [MPa]: fs2 [MPa]: REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF global buckling Buckling allowable as a column Allowed shear strength of panel 1 in pure shearing Allowed shear strength of panel 2 in pure shearing Axial stress of the assembly Shear stress in panel 1 Shear stress in panel 2 The equation to calculate Fpsn is in 4.3.1. Ks is extracted from [Ref 1] charts Where PCO [MPa]: L [mm]: C: I [mm4]: A[mm2]: Buckling allowable as a column Column length Boundary conditions Assembly moment of inertia Assembly area The moment of inertia must be corrected from the centre of gravity to a point in the centre of the skin surface as follows Where A [mm2]: z [mm]: I0 [mm4]: b [mm]: t [mm]: zn: Stringer area Distance from centre of gravity of the stringer to midline of the panel Stringer moment of inertia Distance between stringers Panel thickness Correct factor from [Ref 1] charts 4.4 FEM Detailed Description Skin panels have been modelled with elements shells and rods © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 4-4 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 4.5 Calculations (Limit Loads and Ultimate Loads) RF Local Buckling LC 17501 strg 0-1 strg 1-2 strg 2-3 strg 3-4 strg 4-5 strg 5-6 strg 6-7 strg 7-8 strg 8-9 strg 9-10 strg 10-11 strg 11-12 strg 12-13 strg 13-14 strg 14-15 strg 15-16 frame 39-40 113.55 frame 40-41 11938 69.57 frame 41-42 3051.2 5 1523.5 5 frame 42-43 13637. 99 frame 43-44 8917.8 8 961.82 1649 354.41 512.85 429.68 866.91 415.48 583.96 714.21 220.08 357.31 376.96 432.59 665.25 215.45 287.6 445.74 601.39 2326.4 3 6807.8 6 1009.8 4 5058.0 5 9438.0 5 frame 44-45 23657. 83 2557.4 6 1422.0 2 1271.2 4 2102.1 5 10073. 05 28511. 16 1855.4 2 frame 45-46 57959. 52 8952.3 2 4313.0 2 4069.7 6 5846.9 7 17059. 38 20380 97.78 19441. 81 4428.5 1 1927.9 8 1114.4 6 359.16 620.87 42247. 3 10287. 84 1162.9 5 19513. 64 33.79 164.32 224.59 370.42 652.3 17.43 30.97 61.27 105.75 219.25 595.15 6.97 16.21 27.55 53.18 110.19 303.8 5.51 10.17 18.01 33.39 70.07 188.25 4.88 8.08 13.72 24.66 49.93 131.14 745.81 4.73 7.37 11.67 19.93 38.31 97.13 548.23 5.21 7.52 11.2 17.8 32.22 77.47 446.22 frame 46-47 21914 17.3 16241 9.92 83385. 36 50513. 97 36889. 5 25329. 69 17867. 24 12995. 97 10459. 66 8950.0 3 frame 47-48 60894 0.04 80642. 84 41578. 94 45968. 96 37677 9.79 50245. 28 5749.9 8 1834.7 4 frame 48-49 38938 9.86 45032. 67 15262. 14 10494. 25 18983. 3 51951 6.83 3790.5 7 frame 49-50 56673 244.7 12517 19.86 39811. 47 10451. 29 9182.5 8 16122 1.05 3841.4 8 frame 50-51 15018 8.8 34667. 95 16273 5.79 58075. 9 12360. 15 41417. 72 5045.5 3 frame 51-52 18542 9.34 23708. 22 15322. 46 26637. 36 31226 2.3 49099 22.42 6200.2 6 frame 52-53 67144. 72 27916. 52 48894 7.61 5140.8 2 1742.7 3 1343.3 2 frame 53-54 6033.2 5 1159.1 8 1781.3 9 35061. 49 frame 54-55 3343.8 4 frame 55-56 3854.8 9 frame 56-57 4809.0 9 468.58 434.49 528.65 311.42 166.92 181.37 1021.9 7 124.04 77.59 506.26 761.8 1179.2 1 11.93 174.49 72.52 23.12 3.77 1249.9 130.86 28.72 7.15 2.23 788.23 513.09 416.45 402.64 491.91 167.92 15.2 4.5 1.61 876.39 311.48 166.09 111.2 82.08 86.37 253.21 7.78 3.93 1.27 524.95 168.4 80.36 47.7 31.62 23.4 27.34 5.05 4.07 1.08 7791.9 359.13 107.67 49.3 26.68 16.71 11.39 4.62 10.75 4.09 1.05 254.04 75.89 33.52 18.13 10.2 6.64 2.42 176.3 53.18 24.48 13.03 7.7 4.07 2.39 4.1 2.72 18572. 64 6250.0 9 3921.2 6 2065.2 4 117.15 38.08 18.48 10.71 6.43 3.78 1.89 13.15 91.49 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 4-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF Local Buckling LC 17501 strg 16-17 strg 17-18 strg 18-19 strg 19-20 strg 20-21 strg 21-22 strg 22-23 strg 23-24 strg 24-25 strg 25-26 strg 26-27 strg 27-28 strg 28-29 strg 29-30 strg 30-31 strg 31-32 strg 32-33 frame 39-40 frame 40-41 frame 41-42 frame 42-43 frame 43-44 frame 44-45 frame 45-46 frame 46-47 frame 47-48 frame 48-49 frame 49-50 frame 50-51 frame 51-52 frame 52-53 frame 53-54 frame 54-55 frame 55-56 frame 56-57 2687.3 4 83.19 31.88 19.14 8.12 9.18 10.41 11.21 11.84 12.97 14.93 20.05 36.14 230.58 1906.2 4 121.26 42.93 15.53 12.02 13.93 6.85 7.3 8.62 10.04 11.81 14.35 19.48 31.9 90.55 5951.7 8 300.51 62.28 32.73 17.48 13.51 11.25 5.94 6.25 7.72 9.67 12.35 17.03 26.14 54.09 239.85 8114.4 128.98 48.22 26.04 23.24 27.61 10.83 4.75 5.82 7.57 10.18 14.34 22.31 40.39 107.92 915.41 921.38 111.75 45.52 28.06 26.33 16.17 9.72 10.25 4.75 1352.4 1 1187.1 2 1437.7 1 1483.8 3 1352.4 1 1038.9 7 19737 1.24 1897.9 1 3134.5 1 9003.4 4 19737 1.24 57235. 91 10163. 16 924.12 337.28 136.35 74.94 31.2 13.03 8.72 4.75 187.71 69.68 39.85 30.16 23.23 13.03 8.72 4.18 283.45 104 55.79 35.98 24.27 15.17 9.57 4.78 484.93 177.19 86.84 47.7 26.5 18.18 11.5 6.31 924.12 337.28 136.35 74.94 31.2 24.99 14.24 10.26 2581.6 583.93 236.06 115.49 48.11 36.49 19.64 23.7 8275.8 9 33929 6.28 31864. 41 1090.8 8 376.09 184.13 87.38 52.78 38.85 46.08 2610.9 614.6 316.98 211.09 107.5 151.08 95.09 6597.3 1 1364.1 1 550.17 640.75 298.66 557.19 126.82 4.17 9.7 14 20.55 32.28 53.71 105.12 257.86 4.27 6.31 8.32 11.82 17.68 29.28 56.38 153.56 4.65 7.01 9.57 13.77 21.13 35.65 70.46 192.7 5.52 8.12 11.35 16.58 25.81 43.58 86.64 228.11 7.11 9.7 14 20.55 32.28 53.71 105.12 257.86 9.97 11.86 17.86 26.49 40.15 68.11 121.95 292.38 13.36 15.85 22.82 35.89 51.41 88.5 147.69 331.72 953.98 19.13 24.32 30.52 51.76 64.86 118.15 166.5 363.09 760.68 3708.7 28.74 38.26 50.59 72.59 97.7 155.65 220.87 413.78 759.24 2598.5 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 4-2 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF Local Buckling LC 17501 strg 33-34 strg 34-35 strg 35-36 strg 36-37 strg 37-38 strg 38-39 strg 39-40 frame 39-40 frame 40-41 frame 41-42 frame 42-43 frame 43-44 frame 44-45 frame 45-46 frame 46-47 frame 47-48 26.76 80.9 112.17 143.74 232.24 278.59 423.6 592.54 954.24 33.67 165.06 48.57 265.27 78.75 475.67 231.25 548.45 242.24 439.09 398.79 677.88 730.68 689.43 965.32 3819.9 9 16691. 21 86131. 06 1103.8 6 2057.2 2 5475.7 7 42422. 42 1604.4 5 3559.1 4 11415. 81 82774. 09 1076.7 7 1642.8 8 2929.8 3 7471.7 4 63927. 78 487.66 721.39 939.03 1356.8 1959.9 6 5308.7 8 1219.9 8 1558.7 3 2399.4 5 4443.2 1 11563. 93 11207 2.11 frame 48-49 2154.5 4 2110.8 2 2453.6 6 3636.2 6 6133.6 2 14754. 25 16211 6.75 frame 49-50 6222.2 1 4612.0 3 4740.5 5 6483.5 8 9305.5 4 19306. 14 25763 7.38 frame 50-51 38899 3.03 99850. 45 19418. 05 22294. 88 28022. 88 51634. 78 12809 26.69 frame 51-52 10161. 47 19641 35 66560. 75 34344. 77 24429. 5 35559. 05 70838 6.46 frame 52-53 2490.4 7 13234. 13 75396 2.82 15121 8.62 83121. 11 10064 8.2 20828 5667 frame 53-54 10691. 9 50910 0.58 41118. 39 18183. 36 14319. 88 22992. 08 22190 0.34 frame 54-55 1314.2 9 8003.7 6 24340 1.36 89959 776.6 34716 0.51 99247. 2 11902 54.15 frame 55-56 15704 7.84 35656 7.86 frame 56-57 6530.1 166.53 8240.8 279.66 79.87 93.12 7316.4 5 1088.7 6 3062.9 3 17518. 77 1197.1 4 3680.3 1 18568. 79 75413. 43 frame 39-40 frame 40-41 frame 41-42 frame 42-43 frame 43-44 frame 44-45 frame 45-46 frame 46-47 frame 47-48 frame 48-49 frame 49-50 frame 50-51 frame 51-52 frame 52-53 frame 53-54 frame 54-55 frame 55-56 frame 56-57 7.57 6.42 6.91 6.93 6.99 7 6.99 6.97 6.95 6.93 6.9 6.89 6.9 6.96 7 7.09 6.46 8.48 8.14 6.38 6.91 6.88 6.96 6.97 6.98 6.97 6.96 6.94 6.93 6.91 6.91 6.93 6.94 7.04 6.46 9.01 7.77 6.59 6.82 6.86 6.89 6.93 6.94 6.95 6.94 6.94 6.94 6.91 6.88 6.87 6.87 6.97 6.37 9.98 8.32 6.5 6.89 6.79 6.83 6.83 6.85 6.86 6.87 6.89 6.89 6.87 6.81 6.77 6.79 6.91 6.16 10.62 8.83 6.5 6.9 6.78 6.73 6.68 6.66 6.66 6.7 6.75 6.8 6.82 6.79 6.71 6.66 6.78 5.86 9.31 9.13 6.53 6.94 6.75 6.6 6.45 6.35 6.34 6.4 6.52 6.66 6.78 6.86 6.82 6.56 6.45 5.36 6.8 8.93 6.5 6.96 6.66 6.4 6.15 6 5.97 6.05 6.23 6.48 6.74 6.96 7.08 6.71 6.06 4.49 4.66 137.8 336.11 45539 19380. 82 44414. 5 32665 6.83 422.18 952 18572. 64 RF's Skin Strenght LC 17501 strg 0-1 strg 1-2 strg 2-3 strg 3-4 strg 4-5 strg 5-6 strg 6-7 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 4-3 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF's Skin Strenght LC 17501 strg 7-8 strg 8-9 strg 9-10 Strg 10-11 strg 11-12 strg 12-13 strg 13-14 strg 14-15 strg 15-16 strg 16-17 strg 17-18 strg 18-19 strg 19-20 strg 20-21 strg 21-22 strg 22-23 strg 23-24 frame 39-40 frame 40-41 frame 41-42 frame 42-43 frame 43-44 frame 44-45 frame 45-46 frame 46-47 frame 47-48 frame 48-49 frame 49-50 frame 50-51 frame 51-52 frame 52-53 frame 53-54 frame 54-55 frame 55-56 frame 56-57 8.02 6.4 6.79 6.47 6.14 5.87 5.71 5.66 5.74 5.94 6.25 6.62 6.93 7.18 7.13 5.83 3.73 3.08 7.16 6.02 6.4 6.15 5.91 5.7 5.57 5.53 5.57 5.72 5.99 6.35 6.62 6.78 7.38 5.52 3.58 2.04 6.11 5.41 5.84 5.82 5.79 5.72 5.67 5.63 5.63 5.68 5.77 5.95 6.11 5.97 7.04 5.21 4.12 1.52 5.13 4.79 5.34 5.61 5.84 5.97 6.03 6.03 5.96 5.85 5.71 5.54 5.52 5.1 5.51 6.97 4.6 1.42 4.34 4.32 5.04 5.57 6.07 6.43 6.64 6.68 6.54 6.24 5.81 5.32 4.87 4.29 4.06 2.28 3.81 4.13 4.97 5.7 6.41 6.98 7.34 7.43 7.21 6.72 6.03 5.23 4.49 3.54 3.53 3.14 3.7 4.21 5.16 5.98 6.79 7.44 7.84 7.91 7.63 7.06 6.27 5.34 4.38 3.28 3.18 10.94 4.04 4.2 3.73 3.25 2.95 2.83 4.57 4.71 5.63 6.12 6.47 6.72 6.93 7.2 7.5 7.9 8.23 8.12 7.29 5.41 6.27 2.86 4.39 4.34 5.09 5.7 6.19 6.65 7.03 7.43 7.78 8.1 8.13 7.63 6.71 5.49 7.59 3.05 4.39 4.14 4.8 5.39 6.01 6.57 7.12 7.57 7.95 8.08 7.85 7.14 6.44 5.72 9.4 3.64 3.94 4.19 4.69 5.32 5.95 6.59 7.16 7.63 7.9 7.86 7.51 6.93 6.36 6.25 5.88 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 4-4 5.42 5.33 4.1 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF's Skin Strenght LC 17501 strg 24-25 strg 25-26 strg 26-27 strg 27-28 strg 28-29 strg 29-30 strg 30-31 strg 31-32 strg 32-33 strg 33-34 strg 34-35 strg 35-36 strg 36-37 strg 37-38 strg 38-39 strg 39-40 frame 39-40 frame 40-41 frame 41-42 frame 42-43 frame 43-44 frame 44-45 frame 45-46 frame 46-47 frame 47-48 frame 48-49 frame 49-50 frame 50-51 frame 51-52 frame 52-53 frame 53-54 frame 54-55 frame 55-56 frame 56-57 4.22 5.13 5.68 5.91 6.19 6.42 6.64 6.78 6.9 6.95 6.99 6.96 6.88 6.67 6.27 5.69 4.82 4.1 4.39 4.39 4.87 5.31 5.83 6.35 6.83 7.2 7.4 7.38 7.18 6.87 6.59 6.43 6.24 5.69 4.82 4.81 4.87 4.59 5.12 5.47 5.9 6.33 6.71 6.99 7.15 7.16 7.06 6.9 6.72 6.53 6.19 5.83 4.92 5.87 5.53 4.85 5.4 5.68 6.03 6.35 6.64 6.85 6.98 7.03 7 6.95 6.82 6.61 6.2 5.99 5.13 7.31 6.31 5.13 5.68 5.91 6.19 6.42 6.64 6.78 6.9 6.95 6.99 6.96 6.88 6.67 6.27 6.19 5.37 9.01 7.14 5.4 5.92 6.13 6.32 6.51 6.65 6.77 6.86 6.93 6.97 6.97 6.91 6.69 6.44 6.35 5.65 10.69 7.62 5.71 6.08 6.31 6.43 6.59 6.67 6.77 6.84 6.91 6.94 6.96 6.9 6.7 6.58 6.44 5.99 11.58 8.22 6.03 6.26 6.5 6.56 6.71 6.78 6.83 6.91 6.93 7 6.97 6.96 6.77 6.78 6.63 6.32 12.24 8.61 6.23 6.43 6.57 6.65 6.7 6.81 6.79 6.92 6.86 6.98 6.9 6.94 6.77 6.82 6.77 6.49 12.23 8.62 6.45 6.63 6.72 6.82 6.84 6.94 6.9 7.01 6.95 7.06 6.98 7.01 6.88 6.9 6.92 6.64 11.64 8.66 6.46 6.71 6.72 6.82 6.84 6.91 6.91 6.96 6.96 6.99 6.97 6.97 6.91 6.89 7 6.6 11.21 8.7 6.43 6.76 6.73 6.8 6.83 6.88 6.9 6.93 6.94 6.96 6.95 6.94 6.92 6.9 7.03 6.53 11.12 8.76 6.41 6.78 6.74 6.79 6.82 6.86 6.88 6.9 6.91 6.93 6.93 6.93 6.92 6.91 7.03 6.48 11.08 8.76 6.38 6.8 6.74 6.78 6.81 6.84 6.86 6.88 6.9 6.91 6.92 6.92 6.93 6.91 7.03 6.43 10.98 8.76 6.35 6.81 6.74 6.78 6.8 6.83 6.86 6.87 6.89 6.89 6.91 6.92 6.93 6.91 7.02 6.39 10.92 8.77 6.33 6.81 6.74 6.77 6.8 6.82 6.85 6.86 6.89 6.89 6.91 6.92 6.94 6.92 7.02 6.38 10.94 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 4-5 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF inter rivet buckling LC17511 frame 39-40 frame 40-41 frame 41-42 frame 42-43 frame 43-44 frame 44-45 frame 45-46 frame 46-47 frame 47-48 frame 48-49 frame 49-50 frame 50-51 frame 51-52 frame 52-53 frame 53-54 frame 54-55 frame 55-56 frame 56-57 strg 0-1 260.49 139.13 54.99 37.52 28.95 24.57 22.09 20.49 19.84 19.67 19.12 17.97 16.53 15.54 15.88 17.85 23.83 20.31 strg 1-2 117.37 91.59 47.96 35.93 29.77 25.93 23.57 22.19 21.19 20.57 20.23 19.44 18.13 16.95 16.26 16.32 19.56 16.84 strg 2-3 58.52 82.2 47.81 39.59 34.49 30.74 28 26.81 25.72 24.33 23.52 23.43 23.07 21.06 18.11 15.65 16.01 12.97 strg 3-4 50.98 78.15 60.62 54.81 48.58 45.23 43.49 41.94 39.48 36.09 33.8 34.29 36.23 33.08 24.48 17.16 14.05 9.69 strg 4-5 38.4 69.56 81.67 111.43 139.6 188.52 214.2 156.24 109.37 87.65 73.82 65.27 65.95 67.71 43.38 21.9 13.41 7.99 strg 5-6 28.72 64.58 156.24 253.68 117.62 119.07 99.07 35.93 14.53 7.06 strg 6-7 22.07 85.88 4718.59 189.82 87.47 133.07 74.09 17.86 6.36 strg 7-8 30.98 88.64 1529.17 54.84 58.94 58.7 23.77 6.51 strg 8-9 32.21 245.39 53.72 29.86 21.47 25.74 8.39 strg 9-10 24.82 136.15 21.79 11.13 16.78 18.29 strg 10-11 51.44 23.8 8.64 9.91 strg 11-12 20.61 strg 12-13 152.77 strg 13-14 88.36 strg 14-15 strg 15-16 strg 16-17 strg 17-18 strg 18-19 strg 19-20 strg 20-21 77.6 151.09 97.83 96.52 132.54 1668.18 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 4-6 37.23 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF inter rivet buckling LC17511 frame 39-40 frame 40-41 frame 41-42 frame 42-43 frame 43-44 frame 44-45 frame 45-46 frame 46-47 frame 47-48 frame 48-49 frame 49-50 frame 50-51 frame 51-52 frame 52-53 frame 53-54 frame 54-55 frame 55-56 frame 56-57 strg 21-22 strg 22-23 strg 23-24 2144.81 strg 24-25 strg 25-26 107.45 strg 26-27 111.81 35.14 strg 27-28 66 28.48 strg 28-29 57.46 318.2 30.24 strg 29-30 59.44 198.26 34.79 strg 30-31 64.01 194.06 39.94 strg 31-32 66.35 594.06 180.49 44.96 strg 32-33 77.2 194.98 422.38 54.72 strg 33-34 73.89 133.4 strg 34-35 61.12 120.37 287.71 strg 35-36 53.2 94.37 119.58 227.79 625.57 strg 36-37 46.46 73.89 82.28 98.53 124.08 159.72 211.46 295.43 408.78 548.67 571.45 462.6 318.2 strg 37-38 41.34 61.18 60.67 65.87 71.77 79.97 89.17 99.9 110.46 119.84 124.17 122.6 strg 38-39 36.34 50.09 48.61 50.45 52.69 55.73 59.68 63.64 68.1 71.58 74.15 strg 39-40 34.5 45.53 44.14 45.33 46.6 48.45 51.19 53.86 57.1 59.57 61.69 73.33 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 4-7 660.6 954.62 80.64 627.94 246.86 250.22 77.79 230.65 175.69 144.11 141.27 70.09 116.46 108.5 104.99 92.78 107.94 57.32 74.66 73.95 73.04 72.59 72.65 74.79 45.97 62.39 62.6 62.32 63.56 64.23 66.86 40.23 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF’s Global buckling LC 17501 frame 39-40 frame 40-41 frame 41-42 frame 42-43 frame 43-44 frame 44-45 frame 45-46 frame 46-47 frame 47-48 frame 48-49 frame 49-50 frame 50-51 frame 51-52 frame 52-53 frame 53-54 frame 54-55 frame 55-56 frame 56-57 strg 0 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 1 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 2 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 3 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 4 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB 21.48 strg 5 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB 33.35 14.78 strg 6 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB 7.72 10.44 strg 7 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB 4.14 5.51 strg 8 15.01 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB 2.94 strg 9 8.12 NB NB NB NB NB NB NB NB NB NB NB NB NB NB 4.88 3.10 1.75 strg 10 5.06 NB NB NB NB NB NB NB NB NB NB NB NB NB 10.47 5.73 3.24 1.19 strg 11 NB NB NB NB NB NB NB NB NB NB NB NB NB NB 4.15 NB NB 1.00 strg 12 NB NB NB NB NB NB NB NB NB NB NB NB NB NB 2.75 NB strg 13 NB NB NB NB NB NB NB NB NB NB NB NB NB NB 2.38 NB strg 14 NB NB NB NB NB NB NB NB NB NB NB NB NB NB 4.6 NB strg 15 NB strg 16 NB strg 17 NB strg 18 NB strg 19 NB © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 4-8 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF’s Global buckling LC 17501 frame 39-40 frame 40-41 frame 41-42 frame 42-43 frame 43-44 frame 44-45 frame 45-46 frame 46-47 frame 47-48 frame 48-49 frame 49-50 frame 50-51 frame 51-52 frame 52-53 frame 53-54 strg 20 NB NB NB NB 14.83 16.77 19.45 24.35 34.37 77.96 NB NB NB NB NB NB strg 21 NB NB NB NB NB NB 11.12 15.48 NB NB NB NB NB NB NB NB strg 22 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 23 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 24 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 25 3.32 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 26 3.73 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB 2.85 strg 27 4.49 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB 3.12 strg 28 5.76 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB 4.06 strg 29 7.75 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB 9.92 5.98 strg 30 10.25 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB 12.89 strg 31 12.86 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB 37.88 strg 32 15.99 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 33 16.68 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 34 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 35 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 36 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 37 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 38 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 39 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB strg 40 NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB NB © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 4-9 frame 54-55 frame 55-56 frame 56-57 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 4-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 4-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 5 Stringer 5.1 Geometric Data and Strength Characteristics See paragraph 4.1.1.1 5.2 Sizing and Typical Selected Load Cases The sizing load case is 17507 and the critical failure mode is Strength with RF value of 1.01. 5.3 Specific Post-Processing Hypotheses, Methods and Tools All sections were considered straight 5.3.1 Local Crippling Allowed values for calculating RF’s were been calculated using [Ref 2] Where Fcc [MPa]: bn [mm]: tn [mm]: Fccn [MPa]: Where RFCR : Fcc [MPa]: c [MPa]: Allowable crippling stresses Individual segment lengths Individual segment thicknesses Allowable crippling stresses of individual segments from [Ref 2] charts RF’s Crippling Allowable crippling stresses Compression stress 5.4 FEM Detailed Description Stringer are modelled with rods © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 5-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 5.5 Calculations (Limit Loads and Ultimate Loads) © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 5-2 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF’s Crippling LC 17507 frame 39-40 strg 0 NC 21.83 19.26 14.29 NC 11.92 10.38 9.49 8.9 8.68 8.63 8.41 7.94 7.36 7 7.2 8.35 8.99 29.31 strg 1 NC 48.35 27.26 19.28 NC 15 12.78 11.44 10.59 10.15 9.92 9.55 8.9 8.1 7.49 7.36 8 8.21 21.83 strg 2 NC 68.9 46.43 27.1 NC 21.4 17.67 15.52 14.3 13.08 12.09 11.57 10.83 9.74 8.72 7.74 7.23 6.75 13.19 strg 3 NC NC NC 141.78 NC 60.47 40.43 30.53 26.17 23.39 19.86 16.89 15.91 15.15 12.2 9.22 7.47 6 8.69 strg 4 NC NC NC NC NC NC NC NC NC 262.07 74.16 45.9 36.44 32.32 24.56 14.06 8.56 5.46 5.71 strg 5 NC NC NC NC NC NC NC NC NC NC NC NC NC 135.15 80.52 29 11.74 5.59 NC strg 6 NC NC NC NC NC NC NC NC NC NC NC NC NC NC 281.67 102.89 22.6 6.27 NC strg 7 NC NC NC NC NC NC NC NC NC NC NC NC NC NC 80.35 146.41 58.96 7.74 NC strg 8 NC NC NC NC NC NC NC NC NC NC NC NC NC NC 41.73 36.64 29.59 9.92 NC strg 9 NC NC NC NC NC NC NC NC NC NC NC NC NC NC 64.26 16.91 9.3 10.42 NC strg 10 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC 13.28 4.82 7.14 NC strg 11 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC 18.88 3.92 4.26 NC strg 12 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC strg 13 NC NC NC NC NC NC NC NC NC NC NC NC NC NC 456.16 NC NC NC NC NC NC NC strg 14 1.6 frame 40-41 1.75 frame 41-42 1.8 frame 42-43 NC frame 42-43 frame 43-44 1.86 1.9 frame 44-45 1.95 frame 45-46 1.99 frame 46-47 2.04 frame 47-48 2.09 frame 48-49 frame 49-50 2.14 2.2 frame 50-51 2.25 frame 51-52 2.32 frame 52-53 2.46 frame 53-54 3.5 frame 54-55 frame 55-56 frame 56-57 strg 15 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC strg 16 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC strg 17 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC strg 18 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 5-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF’s Crippling LC 17507 frame 39-40 frame 40-41 frame 41-42 frame 42-43 frame 42-43 frame 43-44 frame 44-45 frame 45-46 frame 46-47 frame 47-48 frame 48-49 frame 49-50 frame 50-51 frame 51-52 frame 52-53 frame 53-54 frame 54-55 frame 55-56 frame 56-57 strg 19 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC strg 20 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC strg 21 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC strg 22 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC strg 23 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC 26.36 31.14 NC strg 24 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC strg 25 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC strg 26 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC 102.02 NC strg 27 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC 40.25 NC strg 28 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC 27.53 NC strg 29 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC 20.54 NC strg 30 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC 117.99 23.44 NC strg 31 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC 129.24 22.51 NC strg 32 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC 235.56 22.65 NC strg 33 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC 182.11 29.74 NC strg 34 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC 68.28 31.85 NC strg 35 NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC 164.38 48.01 31.03 NC strg 36 NC NC NC NC NC NC NC NC NC NC NC NC NC NC 219.84 63.92 43.29 25.76 NC strg 37 NC NC NC NC NC NC NC NC NC NC NC NC 381.34 105.11 60.23 42.47 33.6 24.91 NC strg 38 NC 142.48 286.85 189.47 NC 173.83 138.65 124.45 105.39 91.33 76.21 62.56 50.97 41.98 35.56 31.27 28.21 22.79 NC strg 39 42.14 27.01 31.98 29.58 NC 30.52 29.97 30.62 30.59 30.81 30.42 29.62 28.37 26.85 25.71 24.37 25.18 19.74 NC © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 5-2 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF’s Crippling frame 39-40 LC 17507 strg 40 21.8 frame 40-41 17.18 frame 41-42 18.32 frame 42-43 frame 42-43 18.47 NC frame 43-44 18.86 frame 44-45 19.42 frame 45-46 frame 46-47 20.17 frame 47-48 20.94 frame 48-49 21.79 frame 49-50 22.47 frame 50-51 23.02 frame 51-52 23.23 frame 52-53 23.37 frame 53-54 23.3 frame 54-55 24.02 frame 55-56 24.35 frame 56-57 21.92 NC RF's Strength LC 17507 frame 39-40 frame 40-41 frame 41-42 frame 42-43 frame 43-44 frame 44-45 frame 45-46 frame 46-47 frame 47-48 frame 48-49 frame 49-50 frame 50-51 frame 51-52 frame 52-53 frame 53-54 frame 54-55 frame 55-56 frame 56-57 strg 0 COM 1.15 9.91 6.01 72.04 16.04 1.39 22.78 6.66 8.88 COM 10.1 COM 10.77 13.34 32.85 15.99 12.32 strg 1 COM COM 10.95 5.61 28.36 1.33 18.47 35.97 6.54 7.99 1.59 81.92 COM 11.64 14.53 10.13 16.83 11.92 strg 2 7.46 COM 11.04 5.32 16.91 COM 7.22 84.72 6.59 7.8 COM 22.88 16.36 13.29 11.59 40.67 19.68 COM strg 3 11.77 COM 15.1 5.6 12.08 COM 16.04 COM 6.87 8.14 COM 24.02 17.1 15.89 10.72 1.9 24.47 COM strg 4 4.35 1.15 20.74 5.49 9.28 COM 7.26 COM 7.4 8.95 COM 20.96 17.32 22.76 9.29 COM 36.31 COM strg 5 4.87 11.12 32.68 6 7.93 1.33 23.78 COM 8.09 10.15 COM 19.56 17.12 25.86 10.24 COM 45.07 COM strg 6 5.49 5.6 74.42 6.35 7.22 COM 11.77 14.12 9.18 12.04 COM 20.08 16.4 37.37 10.42 COM 77.27 COM strg 7 4.82 10.65 COM 6.86 7.08 COM 12.83 14.6 10.94 9.78 46.09 17.61 18.38 71.42 10.79 1.9 292.26 COM strg 8 4.89 5.28 COM 7.53 7.29 COM 13.6 14.7 15.59 7.85 18.72 18.43 18.02 541.81 11.2 COM COM COM strg 9 4.91 12.74 COM 8.29 7.79 COM 14.52 14.52 17.31 7.46 12.4 18.64 20.11 COM 11.8 COM COM COM strg 10 122.74 5.42 6.82 9.27 7.19 102.12 14.57 13.97 23.45 7.07 9.83 18.38 24.11 COM 12.49 COM COM COM strg 11 448.61 5.86 6.93 10.76 6.42 26.02 11.93 17.18 38.28 6.89 8.69 17.51 23.39 COM 14.23 COM COM COM strg 12 43.56 6.55 6.96 14.38 5.84 14.99 12.33 16.87 98.11 6.95 8.38 COM 125.89 1.8 15.87 104.28 strg 13 30.98 7.11 6.92 15.68 5.67 10.62 12.47 16.09 COM 7.24 8.67 COM 11.46 COM 18.25 51.14 strg 14 1.01 9.67 6.15 11.33 8.36 10.02 1.39 6.24 6.96 15.97 1.58 1.65 21.18 9.83 13.6 COM strg 15 COM © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 5-3 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF's Strength LC 17507 frame 39-40 frame 40-41 frame 41-42 frame 42-43 frame 43-44 frame 44-45 frame 45-46 frame 46-47 frame 47-48 frame 48-49 frame 49-50 frame 50-51 frame 51-52 frame 52-53 frame 53-54 frame 54-55 frame 55-56 frame 56-57 strg 16 27.33 strg 17 30.01 strg 18 31.01 strg 19 30.57 strg 20 4.85 26.48 5.09 8.78 10 9.55 21.45 7.97 8.43 COM 21.96 COM 9.27 8.92 COM 28.43 strg 21 26.3 6.95 6.8 20.58 5.87 8.59 12.39 15.69 COM 7.75 9.54 COM 31 COM 19.2 105.15 strg 22 23.92 5.51 8.29 31.41 5.89 7.52 12.03 14.47 COM 8.63 10.86 COM 9.81 COM 30.52 COM strg 23 21.78 5.59 8.51 69.85 6.21 7.16 COM 30.31 1.52 9.7 12.9 COM 42.89 1.79 49.93 COM 2.14 13.61 strg 24 18.74 5.61 7.87 COM 6.66 7.23 COM 7.96 COM 11.17 10.09 64.1 1.72 47.05 110.29 COM COM 13.18 strg 25 32.69 5.6 7.09 COM 7.26 7.68 COM 18.23 COM 11.69 8.85 24.2 COM 10.15 COM 445.29 COM 10.87 strg 26 13.21 5.52 6.52 COM 8.06 8.3 COM 7.73 COM 17.52 7.83 15.25 COM 34.18 COM 151.13 COM 13.13 strg 27 10.24 COM 14.14 1.27 9.05 8.41 133.64 21.71 1.52 25.63 7.55 11.62 COM 12.22 COM 66.16 2.15 15.18 strg 28 7.63 COM 5.67 COM 10.26 7.21 25.52 1.46 25.79 41.99 7.4 9.95 1.72 140.85 COM 35.21 22.1 17.41 strg 29 5.83 COM 11.62 COM 10.65 6.44 14.27 COM 8.26 111.97 7.47 9.32 COM 21.93 12.5 25.26 9.1 18.67 strg 30 4.9 159.78 5.96 COM 15.27 6.17 10.21 COM 20.83 COM 7.8 9.46 COM 22.12 12.9 22.01 23.46 20.07 strg 31 4.01 55.45 12.76 1.27 21.38 5.97 8.31 COM 8.73 COM 8.43 10.27 COM 18 13.01 20.34 9.97 20.86 strg 32 4.04 35.89 1.21 14.03 33.01 6.06 7.47 1.45 40.12 COM 9.19 11.73 COM 15.68 12.89 17.92 20.55 25.11 strg 33 4.21 27.45 COM 6.12 71.89 6.21 7.23 COM 17.61 17.26 10.45 13.05 COM 15.69 12.47 10.86 13.71 28.07 strg 34 7.23 23.28 COM 11.7 COM 6.57 7.46 COM 18.9 18.09 12.45 10.83 123.22 14.32 12.74 10.33 14.09 33.53 strg 35 5.19 14.86 COM 5.92 COM 7.14 8.04 COM 18.51 18.35 17.81 8.67 35.49 14.87 13.28 11.37 12.73 38.88 strg 36 6.16 12.17 1.21 16.28 COM 7.86 8.88 COM 18.84 18.16 19.9 8.55 20.99 15.03 15.28 11.1 11.49 78.8 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 5-4 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF's Strength LC 17507 frame 39-40 frame 40-41 frame 41-42 frame 42-43 frame 43-44 frame 44-45 frame 45-46 frame 46-47 frame 47-48 frame 48-49 frame 49-50 frame 50-51 frame 51-52 frame 52-53 frame 53-54 frame 54-55 frame 55-56 frame 56-57 strg 37 7.01 8.92 COM 7.85 10.08 8.87 9.67 153.05 19.39 17.38 27.54 8.17 15.27 14.88 18.37 12.45 10.13 236.7 strg 38 7.7 7.16 COM 8.59 10.33 10.51 8.16 27.57 15.97 20.43 46.99 8.08 12.44 14.33 18.32 13.45 12 COM strg 39 8.3 6.41 COM 9.45 10.39 14.7 6.89 14.68 16.63 19.81 144.61 8.23 11.09 COM 58.07 14.2 12.36 COM strg 40 8.79 6.64 293.26 10.22 10.3 16.15 6.55 10.31 16.82 20.32 COM 8.65 10.76 COM 12.06 14.71 12.44 COM © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 5-5 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 6 Window panels 6.1 Geometric Data and Strength Characteristics This document has been analyzed the window on the left side between frame 45 and frame 46. This part is made of Al2024 T3511. 6.2 Sizing and Typical Selected Load Cases The sizing load case is 27500 and the critical failure mode is Strength with RF value of 1.37. 6.3 Specific Post-Processing Hypotheses, Methods and Tools 6.3.1 Panel strength See paragraph 4.3.2 6.3.2 Global Buckling A DFEM model was been carried out to lunch a 105 solution of Optistruct. 6.4 FEM Detailed Description See paragraph 4.4 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 6-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 6.5 Calculations (Limit Loads and Ultimate Loads) 6.5.1 Strength Element RF Element RF Element RF 45900168 7.81 45900086 6.48 45900110 2.08 45900199 8.15 45900087 4.96 45900111 5.69 45900068 2.61 45900088 6.24 45900112 8.39 45900069 1.22 45900089 2.98 45900113 3.42 45900070 4.54 45900090 6.28 45900114 2.85 45900071 3.93 45900091 3.31 45900115 4.94 45900072 3.25 45900092 6.49 45900116 5.09 45900073 1.21 45900093 7.72 45900117 2.98 45900132 2.49 45900094 2.49 45900118 4.33 45900133 2.77 45900095 4.56 45900119 3.23 45900134 3.11 45900096 2.65 45900120 4.07 45900135 3.06 45900097 5.42 45900121 4.18 45900074 2.43 45900098 6.96 45900122 4.4 45900075 4.22 45900099 2.38 45900123 4.29 45900076 2.65 45900100 4.27 45900124 5.57 45900077 7.35 45900101 2.54 45900125 4.05 45900078 3.42 45900102 3.9 45900126 4.06 45900079 6.43 45900103 3.84 45900127 4.14 45900080 3.2 45900104 4.41 45900128 4.62 45900081 6.43 45900105 4.86 45900129 2.56 45900082 2.73 45900106 4.95 45900130 7.2 45900083 6.37 45900107 3.96 45900131 3.41 45900084 4.44 45900108 3.23 45900085 7.73 45900109 4.02 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 6-2 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 6.5.2 Buckling Load Case 17501 17502 17503 17504 17505 17506 17507 17508 17509 17510 17511 17512 27500 RF 23.78 60.51 19.3 109.6 1.52 13.34 8.49 5.19 22.27 8.6 39.74 13.68 4.43 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 6-3 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 6-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 6-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 7 Frame Frames were composed of two chords. The cross-section of each chord was considered a flange of the frame plus half length of the web. 7.1 Geometric Data and Strength Characteristics This part is made of Al2024 T3511. 7.1.1 Frame web Material E [MPa] µ a [mm] b [mm] t [mm] r [mm] Al2024 T3511 plate 70000 0.3 149.1 81.2 1.8 1852 7.1.2 Frame chord Material Al2024 T3511 plate E [MPa] 70000 µ 0.3 Web [mm] 81.2 Inner Flange[mm] 21.1 Outer Flange [mm] 24.1 t[mm] 1.8 7.2 Sizing and Typical Selected Load Cases The sizing load case is 17507 and the critical failure mode is Buckling with RF value of 1.19. 7.3 Specific Post-Processing Hypotheses, Methods and Tools Frames were considered symmetric. Frames were considered as two L-shaped profiles. For the crippling analysis is assumed the web frame has buckled. The allowable loads for each chord shall be considered to be applied at the geometric centre of the chord. The axial load is evenly distributed between both chords. 7.3.1 Web Frame Buckling See paragraph 4.3.1 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 7-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 7.3.2 Crippling Allowed values for calculating RF’s were been calculated using [Ref 2] Where PCC,i [N]: FCC,i [MPa]: bi [mm]: ti [mm]: Allowed crippling load Stress from [2] charts Individual segment lengths Individual segment thicknesses The failure factor is defined as follows Where PCC,i [N]: PO [N]: PI [N]: Allowed crippling load Outer chord compression load Inner chord compression load A negative value of FFCC,i gives us a safe value. 7.3.3 Strength Where fO [MPa]: fI [MPa]: Ultimate outer fibre stress Ultimate inner fibre stress 7.4 FEM Detailed Description This element has been modelled with an element 1D type bar. © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 7-2 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 7.5 Calculations (Limit Loads and Ultimate Loads) © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 7-3 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF’s web buckling LC 17501 Frame 39 Frame 40 Frame 41 Frame 42 Frame 43 Frame 44 Frame 45 Frame 46 Frame 47 Frame 48 Frame 49 Frame 50 Frame 51 Frame 52 Frame 53 Frame 54 Frame 55 Frame 56 strg 0-1 60.37 225.99 743.22 1262.21 10701.4 2953.58 6420.84 5209.15 23256.6 9652.25 3210.42 2134.09 2215.74 6324.6 4136.67 2424.94 3865.95 13011.4 strg 1-2 60.23 229.22 612.9 3615.16 1287.52 2146.5 1520.9 2266.76 5040.25 4073.91 1332.24 835.52 813.21 1747.68 2024.39 884.04 1108.7 2941.82 strg 2-3 2533.09 590717. 7 1773.92 1599.99 3296.41 1522.46 2031.35 2791.67 31421.1 5 1859.94 850.93 563.44 488.68 645.31 3917.22 965.54 766.17 2249.49 2599.98 1239.44 765.77 535.26 414.36 385.48 555.08 15069.3 2 853.39 1386.66 strg 3-4 3158.91 1633.62 strg 4-5 2115.75 3840.81 strg 5-6 2258.09 22041.7 strg 6-7 2692.42 2134.09 29243.4 5 10327.2 3 5583.34 2762.94 3664.5 5541.44 12306.6 1 3996.73 3520.36 1837.95 1214.46 946.05 804.35 722.32 641.24 542.73 412.16 296.9 260.29 389.65 1361.72 1336.46 3567.13 1442.18 853.63 595.36 484.03 437.89 438.15 475.61 542.93 594.64 530.74 332.57 202.52 181.01 216.06 7961.15 1033.44 774 436.27 346.7 298.22 287.23 299.3 345.2 445.48 627.88 884.3 698.74 263.92 136.23 115.12 376.39 166.16 126.41 117.78 strg 7-8 84.58 1245.18 816.13 373.87 301.23 243.71 228.44 224.28 237.4 271.09 353.17 562.15 1431 2230.8 30766.5 4 strg 8-9 98.58 870.23 383.28 325.39 246.41 233.65 224.31 229.06 241.14 269.9 336.16 561.51 2995.52 576.64 191.7 647.43 285.61 87.61 576.42 131.42 50.03 43.34 118.9 17.69 27.53 11.99 strg 910 strg 1011 strg 1112 strg 1213 strg 1314 strg 1415 strg 1516 strg 1617 strg 1718 629.09 675.72 396.13 282.31 289.19 292.17 313.54 331.34 350.74 377.84 429.17 654.02 39913.3 5 1268.17 569.09 441.69 515.01 770.36 1640.88 8343.47 5593.91 3682.77 8611.04 68688.1 3367.83 1312.12 570.41 633.54 1004.28 970.93 13611 556.12 314.71 233.48 199.62 185.42 186.18 198.69 242.63 304.83 699.23 330.93 291.07 296.21 465.93 168.75 118.33 96.23 85.71 79.98 77.62 77.8 81.62 89.79 111.89 163.61 607.48 262.35 223.94 100.27 65.03 54.78 49.57 46.67 45.12 44.44 44.58 45.8 48.77 55.51 74.37 196.63 2097.71 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 7-1 116.16 SKILL TEMPLATE FOR STATIC STRESS REPORTS strg 1819 strg 1920 strg 2021 strg 2122 strg 2223 strg 2324 strg 2425 strg 2526 strg 2627 strg 2728 strg 2829 strg 2930 strg 3031 strg 3132 strg 3233 strg 3334 strg 3435 strg 35- 296.39 101.18 REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 76.87 63.78 57.33 53.66 51.35 50.53 50.52 52.12 54.82 61.45 74.39 134.18 217.06 590.83 343.8 265.25 246.66 255.12 312.28 455.02 1032.36 5379.94 7439.76 11861.8 110.83 2505.16 539.76 660.46 19560.1 8 493.99 82.29 76.88 77.69 81.82 93.73 95.13 104.2 93.68 96.11 81.01 87.85 87.41 195.71 350.11 229.06 71.4 391.35 69.68 263.45 70.18 229.72 66.21 222.19 57.43 241.91 53.35 337.78 58.25 364.68 1.19 14.69 2.34 2557.21 551.96 104.72 315.65 102.1 246.35 129.71 226.31 159.54 229.58 190.38 270.97 137.54 423.69 6.22 524.8 478.77 274.67 168.9 161.6 139.3 105.47 88.98 78.41 73.88 70.4 70.71 71.66 77.46 85.82 101.85 120.93 131.31 152.64 171.2 295.74 504.02 1127.75 352.2 293.91 232.74 199.1 179.26 169.68 167.54 171.7 183.78 201.8 226.71 250.92 295.98 979.3 909.63 700.73 9436.38 6064.86 1858.77 594.52 589.3 726.41 3487.11 1363.61 1932.97 1490.95 1319.74 1578.61 1916.67 2405.2 2757.78 3210.42 4255.89 17072.7 6 1310.37 1026.97 398.27 314.34 257.52 232.05 217.06 212.12 211.89 221.69 240.12 281.18 330.23 366.72 320.13 380.71 397.2 3606.33 533.9 660.16 270.69 214.38 175.31 153.31 140.11 133.97 132.68 136.75 145.79 163.4 185.15 215.81 231.05 344.88 439.58 2794.31 279.4 295.44 259.97 188.47 163.92 133.67 125.66 113.39 116.04 111.79 124.85 123.74 157.47 165.68 346.46 266.78 2786.4 316.73 235.4 671.72 4666.01 3571.44 2251.21 2623.08 1701.37 2184.6 1493.97 2232.49 1440.07 2752.64 1484.21 8204.41 2692.42 8463 3499.51 4023.96 2737.33 2261.55 588.71 735.63 609.61 476.69 484.35 421.09 448.46 438.21 485.14 513.04 569.2 572.51 522.38 927.92 786.99 607.23 291.79 388.68 146.95 128.22 104.94 91.28 83.33 78.55 77.53 79.36 82.45 90.19 93.78 105.98 103.76 168.24 177.24 408.63 158.33 103.08 151.65 146.95 100.68 105.75 82.56 85.64 78.61 80.92 84.31 85.2 99.41 100.39 149.8 134.16 354.99 105.06 228.23 129.87 478.85 3876.1 543.83 3032.43 550.73 1097.98 604.37 676.8 668.98 543.43 926.76 695.61 9288.01 766.96 2702.27 117.96 945.14 1419.99 1030.92 1111.2 1154.19 902.68 994.13 859.6 934.97 925.88 967.12 1055.22 1010.46 1190 1112.04 2492.47 1835.66 4906.29 638.89 250.3 3545.72 744.53 2082.92 652.72 1360.47 766.96 1160.54 1107.45 1220.49 1792.22 1054.85 1452.1 755.97 3786.65 3628.48 203.48 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 7-2 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 36 strg 3637 strg 3738 strg 3839 strg 3940 934.97 529.22 2413.06 4305.52 5930.9 1973 3206.93 2077.06 2630.08 2411.09 2492.47 3079.86 2590.86 3796.38 2588.59 4890.04 10779.5 2 6179.05 4980.75 4481.92 4488.73 3410.61 3969.87 2924.34 3289.07 2904.21 3109.04 3224.44 3249.27 3767.33 3352.54 4481.92 3896.55 8636.22 7752.2 2904.21 105485. 3 7082.94 33563.5 9466.62 173740. 5 75733.0 3 173740. 5 17686.1 5 295358. 85 5066.18 6052.43 10819 16408.8 2 3511.99 10548.5 3 3495.37 46149.8 2 4733.31 6622.39 6682.32 4318.11 16686.9 4 29834.2 2 4614.98 6563.53 3020.02 8047.92 1705.3 1175.32 1070.52 6003.22 21878.4 3 2307.49 7671.65 5190.84 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 7-3 691.54 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 8 Joints 8.1 Geometric Data and Strength Characteristics 8.1.1 Skin-Stringer Pitch [mm] D [mm] e [mm] t [mm] 30 5.56 11 1.8 8.1.2 Shear Tie Joint Shear ties are joined to three structural elements: skin, frame and stringer. Pitch [mm] D [mm] e [mm] t [mm] 30 5.56 11 1.4 8.2 Sizing and Typical Selected Load Cases The sizing load case is 17501 and the critical failure mode is Bolt Shear with RF value of 1.00. 8.3 Specific Post-Processing Hypotheses, Methods and Tools 8.3.1 Skin-Stringer 8.3.1.1 Bearing RF’s were been calculated using [Ref 1] Where: Pbru [N]: S [N]: Fbru [MPa]: D [mm]: t [mm]: Allowed bearing Shear load Allowed bearing stress Rivet diameter Plate thickness 8.3.1.2 Shear-out Allowed values for calculating RF’s were been calculated using [Ref 1] © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS e [mm]: D [mm]: Pallow [N]: t [mm]: Fsu [MPa]: REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 Distance to the edge Rivet diameter Minimum between allowed rivet shearing and plate bearing Plate thickness Allowed plate shearing © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-2 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 8.3.1.3 Bolt-shear RF’s were been calculated using [Ref 1] Where Pi [N]: q [N/mm]: p: Rivet shear Shear flux Pitch Where Ps allo fast [N]: Pi [N]: Allowed shear value Rivet shear 8.3.2 Shear tie The negative values in axial forces were analysed not as compression but as tension in the opposite direction. 8.3.2.1 Bearing See paragraph 8.3.1.1 8.3.2.2 Bolt-shear See paragraph 8.3.2.2 8.3.2.3 Tension RF’s were been calculated using [Ref 1] Where Pt adm fast [N]: Pt [N]: Bolt tension allowed Bolt tension load 8.3.2.4 Pull through RF’s were been calculated using [Ref 1] Where PPt allow [N]: Pull through allowed Where D [mm]: t [mm] : Bolt diameter Plate thickness © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-3 SKILL TEMPLATE FOR STATIC STRESS REPORTS Fsu [MPa]: Pt [N]: REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 Ultimate shear strength Bolt tension load 8.3.2.5 Combined Shear and Tension RF’s were been calculated using [Ref 1] Where RFBr: RFShear: RFPull-Through: RFTension-bolt: Bearing reserve factor Shear reserve factor Pull-Through reserve factor Tension-bolt reserve factor 8.3.2.6 Shear-out See paragraph 8.3.1.2 8.3.2.7 Tension through the hole RF’s were been calculated using [Ref 1] Where e [mm]: D [mm]: t [mm]: Ftu [MPa]: Pallow: Distance to the edge Bolt diameter Plate thickness Ultimate tensile strength Minimum between allowed shear bolt value and plate bearing 8.4 FEM Detailed Description This joints have been modelled as nodes. © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-4 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 8.5 Calculations (Limit Loads and Ultimate Loads) © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-5 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF's Bearing Skin LC 17501 strg 0 strg 1 strg 2 strg 3 strg 4 strg 5 strg 6 strg 7 strg 8 strg 9 strg 10 strg 11 strg 12 strg 13 frame 39-40 25.0284 452 25.0284 452 45.9108 409 37.0061 249 37.0061 249 41.7833 103 65.9112 727 29.8412 907 22.1151 781 10.7634 204 7.35437 799 5.62522 5 4.75537 832 4.63167 578 frame 40-41 2517.44 444 52.9060 128 52.9060 128 47.1039 501 44.9098 117 44.9098 117 72.0413 355 42.9516 588 17.7250 147 11.3911 513 8.00035 311 6.45544 554 5.84998 709 5.87539 708 frame 41-42 135.670 659 96.7214 514 50.7435 61 49.6591 781 49.6591 781 54.7270 531 89.6419 387 39.0974 978 19.5234 813 12.3488 214 9.49979 036 8.13682 887 7.59792 086 7.78189 936 frame 42-43 303.103 679 80.2728 078 62.4159 78 52.9060 128 52.9060 128 61.3595 125 117.393 782 43.2385 496 22.1964 242 15.3294 993 12.1290 15 10.7150 627 10.2150 586 10.5100 313 frame 43-44 260.425 287 110.521 951 70.7478 532 65.7677 794 65.7677 794 76.9337 861 162.415 771 52.3256 351 29.3769 854 20.6866 012 16.8956 003 15.1248 331 14.5307 039 15.0770 255 frame 44-45 446.443 35 143.398 734 102.288 939 90.7187 187 90.7187 187 108.277 18 219.438 257 83.5281 106 46.0742 247 33.0517 87 27.0531 343 24.3885 899 23.6071 894 24.7010 084 frame 45-46 frame 46-47 725.024 4531.4 276.304 878 180.894 212 162.415 771 162.415 771 178.051 081 278.855 385 262.689 855 122.470 27 81.5733 573 64.9663 082 58.0204 866 56.8557 089 61.7777 778 1192.47 368 802.017 699 573.594 937 446.443 35 338.164 179 263.453 488 213.242 353 186.861 856 174.620 424 170.996 226 167.829 63 153.087 838 135.670 659 frame 47-48 2384.94 737 839.148 148 566.425 549.260 606 549.260 606 482.063 83 151.551 839 81.2078 853 54.6940 253 42.6083 686 36.8556 324 33.8669 656 32.4134 478 32.1603 974 frame 48-49 1888.08 333 620.739 726 340.706 767 262.689 855 262.689 855 327.176 895 127.286 517 55.1936 663 33.6907 063 24.7482 25 20.4762 765 18.5751 179 17.6319 066 17.7806 553 frame 49-50 22657 3236.71 429 542.682 635 260.425 287 230.020 305 230.020 305 135.064 083 47.4492 147 26.1854 955 17.9710 49 14.3149 581 12.4643 103 11.7637 591 11.7805 797 strg 14 strg 15 strg 16 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-1 frame 50-51 1176.98 701 536.260 355 536.260 355 604.186 667 267.339 233 267.339 233 165.681 901 46.9818 559 23.7619 297 15.2034 893 11.2066 279 9.42470 882 8.44622 554 8.38915 116 frame 51-52 1332.76 471 446.443 35 328.362 319 328.362 319 402.791 111 1332.76 471 197.446 623 52.5989 553 23.9566 482 14.4358 076 10.1589 508 7.60748 762 6.51812 428 6.08241 611 frame 52-53 802.017 699 489.881 081 489.881 081 179.106 719 99.7007 701 88.3313 84 88.3313 84 66.5403 818 32.1034 361 16.5894 197 10.4182 09 7.46462 4 5.08717 373 4.33813 604 frame 53-54 228.282 116 98.9388 646 98.9388 646 119.247 368 57.1064 902 32.4831 541 29.1034 04 29.1034 04 37.9196 653 45.4048 096 14.2901 293 5.86057 941 4.53979 863 3.86951 881 frame 54-55 155.184 932 60.1380 226 51.9954 102 51.9954 102 85.0168 856 24.1160 192 14.1650 516 10.5923 329 8.67253 589 8.01025 278 13.8765 886 frame 55-56 150.544 85 53.3733 804 37.1883 463 37.1883 463 39.3009 54 24.8227 883 9.14879 871 5.68236 253 4.95641 236 4.95641 236 5.56375 468 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 strg 17 strg 18 strg 19 strg 20 strg 21 strg 22 strg 23 strg 24 strg 25 strg 26 strg 27 strg 28 strg 29 strg 30 strg 31 strg 32 strg 33 strg 34 6.02940 589 5.66956 522 5.60504 669 5.15371 055 6.83108 465 6.08772 755 5.74831 917 5.74831 917 8.54739 225 7.40545 841 6.90393 845 6.84604 925 10.3776 48 9.09737 001 8.38449 44 8.35589 157 12.5245 992 11.1022 908 10.4506 458 10.4506 458 15.4024 473 14.0291 022 13.2691 069 13.2691 069 19.4188 987 18.1147 312 18.0282 475 18.0282 475 26.3300 407 26.3300 407 26.4144 564 26.9485 578 39.8189 807 39.8189 807 44.9990 07 58.9642 16 94.9979 036 94.9979 036 315.777 003 54.7270 531 200.949 002 62.8052 668 36.8256 806 29.3104 787 37.7774 073 24.2970 509 19.5910 073 18.3755 069 18.2570 508 15.0320 119 13.5528 638 13.5528 638 9.59127 95 9.59127 95 10.7685 361 12.3825 659 9.67421 008 9.67421 008 11.3797 087 13.04 19.5571 86 17.5431 669 5.15371 055 5.31854 46 5.88111 616 7.05001 945 9.00516 693 12.1420 15 16.8610 233 5.86626 966 6.78556 454 6.78556 454 7.62733 547 8.86337 408 10.4990 732 12.5073 144 6.84604 925 7.49673 257 7.49673 257 8.39070 456 9.63820 057 11.4011 825 13.7169 669 8.35589 157 8.76394 933 8.76394 933 9.58316 591 10.8419 667 12.6064 821 15.0720 106 10.4832 851 10.6822 254 10.6822 254 11.5376 194 12.8769 537 14.8157 594 17.1741 52 13.7544 392 13.7732 523 13.7732 523 14.7290 752 16.1893 533 18.2644 095 21.2791 735 19.3154 305 19.1683 587 19.1683 587 20.4947 987 22.3772 84 24.8909 64 27.5047 041 32.2404 838 31.6217 725 31.6217 725 33.7032 354 35.9634 921 38.4342 663 42.0157 626 88.2453 749 87.9030 068 87.9030 068 91.7287 449 88.2453 749 79.0820 244 77.7255 575 91.2668 681 111.063 725 111.063 725 136.900 302 228.858 586 596.236 842 228.282 116 30.5144 781 35.2500 972 35.2500 972 42.0547 564 54.5294 826 76.1579 832 129.839 542 18.4653 627 21.9757 517 21.9757 517 26.5304 45 34.5249 524 47.7995 781 64.1387 12 14.1297 162 17.3318 034 17.3318 034 20.6394 899 25.6591 166 32.1832 386 42.4885 138 13.7003 779 15.8108 863 15.8108 863 17.5533 604 20.2656 53 25.2445 682 31.4680 556 10.6671 375 14.1805 664 14.1805 664 14.6292 171 15.5664 72 17.4251 106 21.9757 517 9.06642 657 10.4434 201 10.4434 201 11.7652 863 13.7753 458 17.2888 211 22.2892 277 8.57732 349 8.57732 349 8.57732 349 9.79762 162 12.0451 887 14.9996 69 18.6247 431 24.0711 819 26.0126 292 25.8567 76 25.8567 76 18.8298 359 21.1945 744 28.3478 261 42.7087 653 18.6938 944 19.7877 729 26.4221 574 41.6297 657 21.5319 553 23.4483 829 29.0567 49 43.0536 817 23.0195 58 24.0520 17 31.2833 966 51.2891 907 28.9916 827 30.7109 454 36.7659 229 52.0551 407 34.7766 692 35.1407 522 43.2385 496 63.6432 584 50.7151 651 50.7151 651 56.0816 832 70.8031 25 73.3236 246 73.3236 246 77.9260 533 92.0081 218 162.415 771 139.213 518 132.303 65 132.303 65 408.234 234 512.022 599 234.787 565 204.117 117 111.473 555 142.273 155 228.858 586 953.978 947 64.9663 082 71.6426 877 110.927 785 310.369 863 47.2759 52 53.2792 475 70.9139 28 154.919 658 37.3569 662 47.4492 147 84.2267 658 343.287 879 32.5181 198 37.8405 01 60.5802 139 125.349 931 38.0470 193 55.4978 567 97.7648 328 1461.74 194 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-2 SKILL TEMPLATE FOR STATIC STRESS REPORTS strg 35 strg 36 strg 37 strg 38 strg 39 strg 40 28.5712 484 34.4855 403 44.4037 237 58.8111 616 93.3347 065 439.941 748 58.4696 774 71.7561 362 94.4041 667 139.642 527 231.785 166 552.609 756 62.6316 517 97.1361 2 141.827 856 248.295 89 556 1118.86 42 57.6147 489 83.9148 148 118.467 974 172.624 762 285.892 744 839.148 148 72.9106 999 96.3103 082 135.467 862 231.785 166 489.881 081 1118.86 42 REFERENCE FM0300705 ISSUE 1.0 65.7677 794 89.9087 302 117.090 439 163.588 448 271.341 317 761.579 832 82.9167 429 102.520 362 136.487 952 208.340 23 379.196 653 1029.86 364 83.4511 971 105.381 395 134.065 089 183.457 49 298.118 421 879.883 495 DATE 15 Nov 2011 106.246 19 123.978 112 158.440 559 220.506 083 361.067 729 1132.85 137.942 161 153.606 78 191.602 537 253.859 944 399.242 291 1332.76 471 204.117 117 211.747 664 253.150 838 308.258 503 448.653 465 1647.78 182 429.516 588 429.516 588 467.154 639 529.988 304 frame 48-49 1152.99 479 379.066 781 208.059 211 160.416 667 160.416 667 199.796 931 77.7299 86 33.7050 853 20.5738 848 15.1129 847 frame 49-50 13835.9 375 1976.56 25 331.399 701 159.033 764 140.466 371 140.466 371 82.4795 082 28.9757 853 15.9906 819 10.9743 704 frame 50-51 725.024 3625.12 802.017 699 580.948 718 492.543 478 492.543 478 596.236 842 2665.52 941 363.967 871 1224.70 27 frame 51-52 813.878 676 272.629 31 200.520 833 200.520 833 245.972 222 813.878 676 120.574 619 32.1205 746 14.6295 929 8.81550 653 frame 52-53 489.767 699 299.155 405 299.155 405 906.28 906.28 995.912 088 45314 427.490 566 374.495 868 374.495 868 472.020 833 1461.74 194 304.120 805 1618.35 714 1849.55 102 974.494 624 974.494 624 3356.59 259 262.689 855 262.689 855 288.624 204 431.561 905 647.342 857 1742.84 615 frame 53-54 139.404 912 60.4189 41 60.4189 41 72.8207 237 34.8731 884 19.8364 695 17.7725 594 17.7725 594 23.1563 808 27.7273 297 frame 54-55 94.7666 952 36.7244 526 31.7520 08 31.7520 08 51.9172 139 14.7269 159 8.65016 411 6.46841 398 5.29605 263 4.89161 658 frame 55-56 91.9331 395 32.5934 923 22.7097 866 22.7097 866 23.9998 916 15.1585 182 5.58689 178 3.47004 514 3.02672 956 3.02672 956 652 RF's Bolt Shear 17501 strg 0 strg 1 strg 2 strg 3 strg 4 strg 5 strg 6 strg 7 strg 8 strg 9 frame 39-40 15.2841 066 15.2841 066 28.0363 475 22.5985 096 22.5985 096 25.5157 907 40.25 18.2231 643 13.5050 634 6.57289 192 frame 40-41 1537.32 639 32.3080 852 32.3080 852 28.7649 428 27.4250 496 27.4250 496 43.9934 42 26.2292 654 10.8241 248 6.95622 8 frame 41-42 82.8499 251 59.0648 346 30.9875 42 30.3253 425 30.3253 425 33.4201 389 54.7415 925 23.8756 471 11.9223 934 7.54104 783 frame 42-43 185.096 154 49.0201 506 38.1155 303 32.3080 852 32.3080 852 37.4703 791 71.6887 953 26.4044 609 13.5546 779 9.36125 677 frame 43-44 159.033 764 67.4923 78 43.2035 519 40.1623 73 40.1623 73 46.9811 121 99.1823 477 31.9536 663 17.9396 272 12.6326 752 frame 44-45 272.629 31 87.5692 247 62.4647 291 55.3991 491 55.3991 491 66.1215 651 134.004 237 51.0080 645 28.1361 21 20.1837 163 frame 45-46 442.75 168.730 945 110.466 567 99.1823 477 99.1823 477 108.730 354 170.288 462 160.416 667 74.7888 514 49.8143 564 frame 46-47 2767.18 75 728.207 237 489.767 699 350.276 899 272.629 31 206.506 53 160.882 994 130.220 588 114.110 825 106.635 356 frame 47-48 1456.41 447 512.442 13 345.898 438 335.416 667 335.416 667 294.381 649 92.5480 769 49.5911 738 33.3999 698 26.0196 286 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-3 718.75 327.477 811 327.477 811 368.958 333 163.255 9 163.255 9 101.176 874 28.6903 836 14.5106 843 9.28430 632 109.375 60.8842 134 53.9412 768 53.9412 768 40.6341 777 19.6045 873 10.1306 517 SKILL TEMPLATE FOR STATIC STRESS REPORTS strg 10 strg 11 strg 12 strg 13 REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 4.49109 389 3.43515 3 2.90396 421 2.82842 285 4.88557 115 3.94214 332 3.57240 834 3.58792 545 5.80123 166 4.96891 273 4.63981 808 4.75216 813 7.40681 879 6.54336 131 6.23802 412 6.41815 493 10.3176 268 9.23627 336 8.87345 679 9.20707 869 16.5205 224 14.8933 665 14.4161 891 15.0841 51 39.6729 391 35.4313 38 34.7200 439 37.7258 01 104.422 17 102.488 426 93.4860 642 82.8499 251 22.5066 084 20.6815 209 19.7939 02 19.6393 719 12.5042 363 11.3432 568 10.7672 665 10.8581 028 8.74170 747 7.61157 337 7.18376 817 7.19404 004 6.84354 52 5.75538 166 5.15785 182 5.12299 824 6.20376 079 4.64566 02 3.98041 93 3.71434 564 6.36208 185 4.55841 776 3.10658 153 2.64916 711 8.72654 525 3.57887 675 2.77231 629 2.36299 688 8.47400 857 3.39761 495 3.68197 392 3.46223 022 3.42283 073 3.14721 353 4.17153 463 3.71758 917 3.51032 285 3.51032 285 5.21963 124 4.52228 714 4.21602 422 4.18067 306 6.33731 249 5.55548 585 5.12015 45 5.10268 763 7.64838 999 6.77982 972 6.38188 999 6.38188 999 9.40580 387 8.56714 396 8.10303 807 8.10303 807 11.8585 28 11.0621 127 11.0092 998 11.0092 998 16.0789 512 16.0789 512 16.1305 013 16.4566 607 24.3162 346 24.3162 346 27.4795 184 36.0076 448 58.0123 166 58.0123 166 192.835 366 33.4201 389 122.713 415 38.3532 571 22.4883 178 17.8990 136 23.0695 081 14.8374 665 11.9636 295 11.2213 605 11.1490 23 9.17959 031 8.27631 972 8.27631 972 5.85710 128 5.85710 128 6.57601 592 7.56165 46 5.90774 445 5.90774 445 6.94924 033 7.96312 95 11.9429 758 10.7130 759 3.14721 353 3.24787 265 3.59141 791 4.30523 143 5.49918 025 3.58235 161 4.14373 69 4.14373 69 4.65778 068 5.41259 169 4.18067 306 4.57802 548 4.57802 548 5.12394 686 5.88575 455 5.10268 763 5.35187 603 5.35187 603 5.85214 656 6.62085 776 6.40182 186 6.52330 858 6.52330 858 7.04567 155 7.86356 209 8.39941 569 8.41090 426 8.41090 426 8.99459 613 9.88634 334 11.7953 431 11.7055 309 11.7055 309 12.5155 473 13.6651 235 19.6882 782 19.3104 501 19.3104 501 20.5815 359 21.9618 056 53.8887 537 53.6796 799 53.6796 799 56.0159 413 53.8887 537 55.7338 872 67.8232 23 67.8232 23 83.6008 308 139.756 944 18.6342 593 21.5261 571 21.5261 571 25.6815 545 33.2994 886 11.2762 327 13.4199 2 13.4199 2 16.2013 32 21.0833 333 8.62858 591 10.5840 027 10.5840 027 12.6039 057 15.6692 384 8.36640 212 9.65522 505 9.65522 505 10.7193 008 12.3756 149 6.51409 487 8.65963 855 8.65963 855 8.93361 582 9.50596 874 5.53658 964 6.37747 753 6.37747 753 7.18470 077 8.41218 27 5.23790 933 5.23790 933 5.23790 933 5.98310 811 7.35562 865 strg 14 strg 15 strg 16 strg 17 strg 18 strg 19 strg 20 strg 21 strg 22 strg 23 strg 24 strg 25 strg 26 strg 27 strg 28 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-4 SKILL TEMPLATE FOR STATIC STRESS REPORTS strg 29 strg 30 strg 31 strg 32 strg 33 strg 34 strg 35 strg 36 strg 37 strg 38 strg 39 strg 40 REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 7.41475 75 10.2965 116 6.41146 316 7.63783 467 6.96235 376 8.37653 247 7.69839 338 9.20401 63 9.04753 147 10.4877 298 11.1535 167 12.9945 41 15.2001 511 16.7962 822 23.4706 319 25.6577 422 48.2929 756 47.4646 226 364.103 618 139.404 912 46.5073 529 79.2890 401 29.1897 416 39.1675 513 19.6533 203 25.9464 369 15.4160 864 19.2165 799 10.6409 825 13.4199 2 10.5577 547 13.6113 502 9.15983 946 11.3735 614 14.6995 352 15.8851 177 15.7899 429 15.7899 429 17.4475 883 21.0592 656 27.1159 971 35.9141 791 56.9966 529 268.658 981 11.4988 053 12.9428 789 17.3111 511 26.0809 378 35.7056 452 43.8192 795 57.6497 396 85.2754 237 141.544 118 337.461 89 11.4157 9 12.0837 882 16.1352 041 25.4220 257 38.2472 357 59.3180 6 86.6099 374 151.626 712 339.532 209 683.256 173 13.1489 071 14.3192 109 17.7440 686 26.2915 677 35.1835 664 51.2442 13 72.3447 712 105.416 667 174.585 962 512.442 13 14.0573 406 14.6878 317 19.1038 143 31.3207 414 44.5243 363 58.8137 62 82.7260 837 141.544 118 299.155 405 683.256 173 17.7043 346 18.7542 359 22.4518 256 31.7884 836 40.1623 73 54.9045 139 71.5035 53 99.8984 657 165.699 85 465.073 529 21.2370 491 21.4593 835 26.4044 609 38.8649 93 50.6347 21 62.6060 52 83.3490 211 127.227 011 231.563 808 628.906 25 30.9702 015 30.9702 015 34.2473 7 43.2373 047 50.9610 958 64.3531 977 81.8694 527 112.031 883 182.051 809 537.317 961 44.7764 968 44.7764 968 47.5870 593 56.1865 482 64.8813 013 75.7096 443 96.7548 077 134.656 326 220.493 028 691.796 875 99.1823 477 85.0134 409 80.7937 956 80.7937 956 84.2370 624 93.8029 661 117.005 814 155.024 51 243.805 066 813.878 676 249.296 171 312.676 554 143.377 591 124.648 086 124.648 086 129.307 827 154.591 48 188.244 048 273.978 96 68.0734 932 86.8818 681 139.756 944 582.565 789 262.292 654 262.292 654 285.277 062 323.647 661 39.6729 391 1006.25 2213.75 28.8699 791 32.5360 082 43.3049 687 94.6047 009 222.264 056 747.888 514 553.437 5 553.437 5 608.173 077 27671.8 75 22.8127 576 28.9757 853 51.4347 119 209.635 417 398.156 475 261.055 425 228.693 182 228.693 182 288.248 698 892.641 129 19.8578 22 23.1080 376 36.9944 853 76.5473 721 185.717 282 988.281 25 1129.46 429 595.094 086 595.094 086 2049.76 852 23.2341 52 33.8908 451 59.7019 957 892.641 129 160.416 667 160.416 667 176.253 981 263.541 667 395.312 5 1064.30 288 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-5 442.75 43.75 67.7402 081 189.533 39 489.767 699 354.767 628 300.781 25 300.781 25 364.103 618 1627.75 735 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-6 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 RF's (bearing) 180º Frame Skin Stringer 90º 0º 270º 17501 vs 101.74 SHTI 79.13 vs 28.99 SHTI 22.55 vs 105.62 SHTI 82.15 vs 29.07 17502 1647.16 1281.13 936.24 728.19 1790.48 1392.59 667.20 17503 2046.98 1592.10 192.09 149.40 547.81 426.08 192.01 17504 946.23 735.96 180.21 140.16 533.76 415.15 180.00 17505 17506 17507 17508 17509 17510 17511 17512 27500 17501 145.37 121.79 119.13 139.35 122.23 147.30 120.78 146.52 183.63 5418.73 113.06 94.73 92.66 108.38 95.07 114.56 93.94 113.96 142.82 2001.27 59.52 42.47 46.41 69.97 40.09 54.06 36.77 47.47 77.79 113.49 46.30 33.04 36.10 54.42 31.18 42.05 28.60 36.92 60.51 41.91 193.25 114.52 113.55 184.54 114.43 195.99 113.23 194.70 178.90 1397.14 150.31 89.07 88.32 143.53 89.00 152.44 88.07 151.43 139.14 516.00 41.59 33.63 31.91 38.70 34.86 43.76 36.86 47.47 36.32 111.65 17502 1494.80 552.07 322.04 118.94 2538.24 937.43 271.31 17503 3798.14 1402.75 295.77 109.24 4622.20 1707.09 294.41 17504 17505 17506 17507 17508 17509 17510 17511 17512 27500 17501 17502 17503 951.89 445.35 524.17 334.62 293.41 786.82 679.97 1093.91 3173.68 248.41 351.56 164.48 193.59 123.58 108.36 290.59 251.13 404.01 1172.12 91.74 188.77 271.05 91.70 89.21 298.59 93.00 246.72 94.49 213.35 298.81 18.77 202.41 170.48 69.72 100.11 33.87 32.95 110.28 34.35 91.12 34.90 78.79 110.36 7.51 80.97 68.19 3489.94 620.81 601.23 404.50 403.01 845.33 960.82 1245.94 2994.76 324.14 1288.92 229.28 222.05 149.39 148.84 312.20 354.86 460.16 1106.04 119.71 188.86 170.35 92.62 91.53 151.66 93.07 185.07 93.31 211.22 117.66 18.82 170.78 170.92 17504 957.37 382.95 1098.62 17505 17506 38.12 30.96 15.25 12.39 26.13 22.61 SHTI 22.61 518.9 4 149.3 4 140.0 0 32.35 26.15 24.82 30.10 27.11 34.04 28.67 36.92 28.25 41.24 100.2 0 108.7 3 69.75 62.91 34.21 33.80 56.01 34.37 68.35 34.46 78.01 43.45 7.53 68.31 68.37 439.4 5 10.45 9.04 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS 17507 17508 17509 17510 17511 17512 27500 REFERENCE FM0300705 ISSUE 1.0 35.55 45.41 28.50 34.42 25.38 30.04 49.16 14.22 18.16 11.40 13.77 10.15 12.02 19.66 DATE 15 Nov 2011 21.19 24.23 23.67 27.57 25.46 30.04 22.44 8.47 9.69 9.47 11.03 10.18 12.02 8.98 RF's (shear) 180º Frame Skin Stringer 90º 0º 270º 17501 130.85 37.28 135.83 37.39 17502 2118.31 1204.04 2302.62 858.05 17503 2632.49 247.03 704.51 246.93 17504 1216.88 231.75 686.44 231.48 17505 186.95 76.55 248.53 53.49 17506 156.63 54.62 147.27 43.25 17507 153.20 59.69 146.03 41.03 17508 179.21 89.99 237.32 49.77 17509 157.19 51.56 147.17 44.83 17510 189.43 69.53 252.05 56.28 17511 155.33 47.29 145.62 47.40 17512 188.43 61.04 250.39 61.05 27500 236.16 100.05 230.07 46.71 17501 3309.05 69.30 853.19 68.18 17502 912.83 196.66 1550.02 165.68 17503 2319.41 180.62 2822.64 179.79 17504 581.29 115.28 2131.20 115.33 17505 271.96 165.52 379.11 104.03 17506 320.10 56.00 367.15 56.56 17507 204.34 54.48 247.02 55.89 17508 179.17 182.34 246.11 92.61 17509 480.49 56.79 516.22 56.84 17510 415.24 150.66 586.74 113.02 17511 668.02 57.70 760.86 56.98 17512 1938.07 130.28 1828.81 128.98 27500 151.69 182.48 197.94 71.85 17501 12.41 12.45 17502 133.87 112.95 17503 112.75 113.05 17504 633.19 726.61 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-2 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 17505 25.21 17.28 17506 20.48 14.95 17507 23.51 14.01 17508 30.03 16.02 17509 18.85 15.66 17510 22.76 18.23 17511 16.79 16.84 17512 19.87 19.87 27500 32.51 14.84 RF's (tension) Frame Skin 45000000 45190000 45370000 45191000 17501 6626.13 192.50 1714.80 189.73 17502 2503.14 408.69 5194.12 348.60 17503 41409.95 11185.26 5864.48 8269.26 17504 1162.93 2059.30 4377.43 2415.00 17505 1621.78 387.81 3839.88 209.30 17506 3739.34 458.02 1516.54 222.97 17507 48228.21 662.47 1513.34 196.09 17508 1105.23 526.04 3819.28 185.43 17509 2176.85 376.81 1518.69 245.40 17510 2354.86 327.96 3853.56 228.94 17511 1336.86 300.17 1521.94 289.03 17512 7351.98 268.33 3874.53 266.45 27500 1001.56 396.49 2871.91 145.43 17501 65.42 18.98 67.92 19.04 17502 1741.57 1084.29 1433.75 721.91 17503 1593.84 169.20 352.46 169.71 17504 608.64 2459.72 343.45 2532.17 17505 98.80 38.56 131.22 26.75 17506 80.70 31.00 74.80 22.90 17507 82.63 35.47 76.04 21.52 17508 101.71 45.72 135.10 24.89 17509 79.46 28.60 73.99 23.93 17510 96.95 34.91 128.75 28.16 17511 77.67 25.54 72.81 25.65 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-3 SKILL TEMPLATE FOR STATIC STRESS REPORTS Stringer REFERENCE FM0300705 ISSUE 1.0 17512 94.29 30.57 125.23 30.58 27500 176.08 50.31 140.68 23.38 17501 66.58 65.38 17502 482.56 355.63 17503 120.48 119.97 17504 77.34 77.24 17505 211.84 636.39 17506 38.50 43.76 17507 36.82 45.36 17508 168.67 1304.32 17509 39.71 42.75 17510 254.45 474.24 17511 41.67 41.34 17512 363.66 343.52 27500 311.25 311.55 DATE 15 Nov 2011 RF's (Pull through) 45000000 Frame Frame Frame Frame Frame Frame Frame Frame Frame Frame Frame Frame Frame Skin Skin Skin Skin Skin Skin 17501 17502 17503 17504 17505 17506 17507 17508 17509 17510 17511 17512 27500 17501 17502 17503 17504 17505 17506 vs NT 4088.38 NT 1899.42 NT 6107.48 NT NT 3555.45 NT 2183.49 NT NT 189.97 5056.90 NT 1767.29 286.87 234.31 45190000 45370000 45191000 SHTI vs SHTI vs SHTI vs SHTI NT NT NT 2800.78 2178.39 NT NT 3179.85 NT NT 8483.56 6598.33 NT NT NT 18268.91 14209.15 NT NT 13506.20 10504.82 1477.33 3363.46 2616.03 7149.67 5560.85 3944.42 3067.89 NT NT NT 6271.68 4877.97 NT NT 4750.26 NT NT 2476.97 1926.53 NT NT NT NT NT 2471.73 1922.46 NT NT NT NT NT 6238.04 4851.81 NT NT 2765.35 NT NT 2480.48 1929.26 NT NT NT NT NT 6294.03 4895.35 NT NT 1698.27 NT NT 2485.78 1933.38 NT NT NT NT NT 6328.28 4922.00 NT NT NT NT NT 4690.70 3648.32 NT NT 83.11 55.10 24.10 NT NT NT NT 2212.39 NT NT 4163.10 1821.35 NT NT NT NT NT 1023.41 447.74 492.78 215.59 773.19 7142.17 3124.70 NT NT NT NT 125.51 111.95 48.98 NT NT NT NT 102.51 90.01 39.38 NT NT NT NT © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-4 SKILL TEMPLATE FOR STATIC STRESS REPORTS Skin Skin Skin Skin Skin Skin Skin Stringer Stringer Stringer Stringer Stringer Stringer Stringer Stringer Stringer Stringer Stringer Stringer Stringer 17507 17508 17509 17510 17511 17512 27500 17501 17502 17503 17504 17505 17506 17507 17508 17509 17510 17511 17512 27500 239.92 295.32 230.72 281.50 225.52 273.80 511.27 104.96 129.20 100.94 123.16 98.66 119.79 223.68 102.98 132.76 83.03 101.36 74.17 88.76 146.09 211.45 NT NT 245.61 672.78 122.27 116.93 535.66 126.11 808.11 132.34 1154.92 988.48 REFERENCE FM0300705 ISSUE 1.0 45.06 58.08 36.33 44.35 32.45 38.83 63.91 84.58 NT NT 98.24 269.11 48.91 46.77 214.26 50.44 323.24 52.94 461.97 395.39 NT NT NT NT NT NT NT NT NT NT NT NT NT NT DATE 15 Nov 2011 NT NT NT NT NT NT NT 207.63 NT NT 245.31 2021.08 138.97 144.04 4142.33 135.78 1506.12 131.27 1090.96 NT NT NT NT NT NT NT NT 83.05 NT NT 98.12 808.43 55.59 57.62 1656.93 54.31 602.45 52.51 436.38 NT RF's (combined) 45000000 45190000 45370000 45191000 Frame Frame Frame Frame Frame Frame Frame Frame Frame Frame Frame Frame Frame Skin Skin 17501 17502 17503 17504 17505 17506 17507 17508 17509 17510 17511 17512 27500 17501 17502 18.78 13.58 34.60 10.52 11.75 15.52 36.40 10.34 12.96 13.30 11.02 19.44 10.01 4.03 12.03 5.77 7.42 22.36 12.72 7.29 7.71 8.72 8.07 7.22 6.90 6.70 6.45 7.35 2.67 10.27 11.97 7.25 18.03 16.36 15.66 11.49 11.48 15.63 11.49 15.68 11.50 15.71 14.21 4.08 11.28 5.75 7.04 20.22 13.42 5.94 6.06 5.81 5.70 6.26 6.12 6.61 6.43 5.26 2.67 8.97 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-5 SKILL TEMPLATE FOR STATIC STRESS REPORTS Skin Skin Skin Skin Skin Skin Skin Skin Skin Skin Skin Stringer Stringer Stringer Stringer Stringer Stringer Stringer Stringer Stringer Stringer Stringer Stringer Stringer 17503 17504 17505 17506 17507 17508 17509 17510 17511 17512 27500 17501 17502 17503 17504 17505 17506 17507 17508 17509 17510 17511 17512 27500 11.68 8.47 4.62 4.32 4.36 4.67 4.30 4.59 4.27 4.55 5.60 REFERENCE FM0300705 ISSUE 1.0 5.53 13.50 3.38 3.14 3.29 3.58 3.06 3.27 2.95 3.13 3.69 4.05 7.84 4.94 4.26 5.96 3.38 3.33 5.53 3.41 6.34 3.47 7.14 6.78 7.06 7.00 5.08 4.21 4.24 5.13 4.20 5.05 4.18 5.00 5.20 DATE 15 Nov 2011 5.54 13.63 2.99 2.84 2.78 2.92 2.88 3.04 2.95 3.13 2.86 4.03 7.08 4.93 4.26 8.60 3.52 3.57 10.93 3.50 7.80 3.46 7.00 6.78 © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 8-6 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 9 Lugs This document will focus on two types of lugs within the structure which support the loads of the passage deck. 9.1 Geometric Data and Strength Characteristics The first kind of lug it is called as lug. w [mm] 44 rh [mm] 5.55 t [mm] 8 c [mm] 16.45 a [mm] 22 A2 A3 A1 A4 A1 [mm²] 185.33 A2 [mm²] 139.6 A3 [mm²] 131.6 A4 [mm²] 173.13 The second kind of lug it is called as lug+bar. © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 9-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS w [mm] 38.312 rh [mm] 5 REFERENCE FM0300705 ISSUE 1.0 t [mm] 8.7 c [mm] 14.156 DATE 15 Nov 2011 a [mm] 19.156 A3 A2 A4 A1 [mm²] 133.03 A2 [mm²] 123.16 A1 A3 [mm²] 123.16 A4 [mm²] 133.03 The material used for the lugs is as follows: Material Ftux [MPa] Ftum [MPa] ftpm [MPa] Al2024 T3511 580 468 408 9.2 Sizing and Typical Selected Load Cases Describe here Load Cases that size the structure. If all the L/C described in §2.1 have been used, just refer to them. If a selection has been done, explain the choice criteria. 9.3 Specific Post-Processing Hypotheses, Methods and Tools To calculate the oblique allowables is needed the axial and transverse allowables. © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 9-2 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 Lug+bar is a twin joint but the load considered in each lug is the full load on the bar. 9.3.1 Tensile rupture RF’s were been calculated using [4] Where RFA: PA, allowed [N]: FA, applied [N]: Tensile reserve factor Load to cause lug failure by tensile rupture Load applied on lug Where Axial tensile rupture factor from [4] charts Allowable tensile ultimate stress in the axial from [8] Nominal width of lug Diameter of hole in lug Thickness Ktux: ftux [MPa]: w [mm]: dh [mm]: t [mm]: 9.3.2 Shear-bearing rupture RF’s were been calculated using [4] Where RFA: Tensile reserve factor PCA, allowed [N]: Load to cause lug failure by shear-bearing FA, applied [N]: Load applied on lug Where Kqux: ftum [MPa]: dh [mm]: t [mm]: Shear-bearing rupture factor from [4] charts Allowable shear-bearing ultimate stress in the axial from [8] Diameter of hole in lug Thickness 9.3.3 Axial permanent deformation RF’s were been calculated using [4] Where RFDP_A: Permanent deformation reserve factor PDPA, allowed [N]: Load to cause lug failure by permanent deformation FA, applied [N]: Load applied on lug © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 9-3 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 Where Kpx: Axial permanent deformation factor from [4] charts ftpm [MPa]: Minimum tensile strength with respect to the direction of grain in the plane of the lug from [8] ftum [MPa]: Allowable shear-bearing ultimate stress in the axial from [8] Pux min [N]: Minimum value between PCA, allowed and PA, allowed 9.3.4 Transverse rupture RF’s were been calculated using [4] Where RFT: PT, allowed [N]: FT, applied [N]: Transverse reserve factor Load to cause rupture under transverse load Load applied on lug Where Transverse rupture factor from [4] charts Allowable shear-bearing ultimate stress in the axial from [8] Diameter of hole in lug Thickness Kuy: ftum [MPa]: dh [mm]: t [mm]: Two diagrams are needed to calculate the equivalent area from [4]. The following one is used with lug The following one is used with lug+bar © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 9-4 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 The expression to calculate the equivalent area is as follow: 9.3.5 Transversal permanent deformation RF’s were been calculated using [4] Where RFDP_T: Transversal permanent deformation reserve factor PDP_T, allowed [N]:Load to cause permanent deformation under transverse load FT, applied [N]: Load applied on lug Where Kpy: ftpm [MPa]: lug dh [mm]: t [mm]: Permanent deformation factor from [4] charts Minimum proof stress with respect to the grain direction in the plane of the Diameter of hole in lug Thickness Equivalent Area is needed to read Kpy chart. See paragraph 9.3.4 9.3.6 Oblique Loading RF’s were been calculated using [4] Where © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 9-5 SKILL TEMPLATE FOR STATIC STRESS REPORTS RFO: PO, allowed [N]: FO, applied [N]: Where Puxmin [N]: PT, allowed [N]: [rad]: REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 Oblique reserve factor Failure load under oblique load Oblique load applied on lug Minimum value between PA, allowed and PCA, allowed Load to cause rupture under transverse load Angle of oblique load on lug measured from x-direction 9.3.7 Oblique permanent deformation RF’s were been calculated using [4] Where RFDP_O: PDP_O [N]: FO, applied [N]: Oblique permanent deformation reserve factor Load to cause permanent deformation under oblique load Oblique load applied on lug Where PDPA, allowed [N]: Axial load to cause lug failure by permanent deformation PDP_T, allowed [N]:Load to cause permanent deformation under transverse load [rad]: Angle of oblique load on lug measured from x-direction 9.4 FEM Detailed Description Describes here in detail the FEM (if it is not already done in §2.5) and the output used for the calculation; if no specifics FEM have been used for the calculated element or junction, just put N/A (for Non-Applicable). Chosen elements for free-body analysis can be described in this section. Include model idealisation and elements considered. © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 9-6 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 9.5 Calculations (Limit Loads and Ultimate Loads) Oblique RF's Lug Subcase 17501 17502 17503 RF Left side Left side Left side Lug+bar Node RF Subcase Node RF 103.314496 Rigth side 106.717231 17501 Left side 8328.42358 Rigth side 99.7175061 Rigth side 879.940029 17504 178.823397 17505 8100.68443 101.604796 17502 17503 Node RF 55567.90504 Rigth side 79.7224383 784167.9134 Rigth side 1223.03246 48059.30668 Rigth side 74.6190551 Left side 297107.4738 Rigth side 462.195295 Left side 71668.43039 Rigth side 111.635685 84129.65379 Rigth side 119.605504 107455.4138 Rigth side 149.781661 94.1250523 Left side Left side 17504 Left side 866.277458 Rigth side 17505 Left side 173.596716 Rigth side 131.975003 Rigth side 138.465577 Rigth side 167.262381 17508 Left side 59740.87656 Rigth side 131.591468 17509 Left side 73111.63036 Rigth side 105.071132 82467.83442 Rigth side 127.002873 60878.28946 Rigth side 88.6253444 158.530671 17506 17507 Left side Left side 134.564807 138.226693 17506 17507 Left side Left side 17508 Left side 160.861124 Rigth side 17509 Left side 127.874522 Rigth side 183.221027 Rigth side 122.067369 Rigth side 197.712192 17512 Left side 105667.4172 Rigth side 200.939486 27500 Left side 51171.15916 Rigth side 79.3880914 Node RF 17510 17511 Left side Left side 17512 Left side 199.717154 Rigth side 27500 Left side 196.875405 Rigth side 186.674268 126.676743 17510 17511 Left side Left side Oblique Permanent Deformation RF's Lug Subcase Node RF 17501 Left side 17502 Left side 17503 17504 Left side Left side Lug+bar Node RF Subcase Node 99.7123132 Rigth side 100.275108 17501 Left side 82.899107 Rigth side 83.3670051 7134.66308 Rigth side 7037.63185 17502 Left side 1245.86061 Rigth side 1228.91694 87.8466633 Rigth side 74.4904267 Rigth side 75.1028516 760.628439 Rigth side 461.641096 Rigth side 464.857315 155.50307 17505 Left side 110.78555 Rigth side 112.225042 127.91294 17506 Left side 125.488018 Rigth side 125.838023 160.147955 Rigth side 160.14152 92.5868177 Rigth side 94.242411 109.756062 88.5688968 765.92768 17503 17504 Left side Left side RF 17505 Left side 153.508458 Rigth side 17506 Left side 127.557164 Rigth side 135.40798 Rigth side 141.731804 Rigth side 123.39354 17509 Left side 109.158103 Rigth side 163.756094 17510 Left side 127.229718 Rigth side 128.227657 91.0615525 Rigth side 91.8719416 162.475726 Rigth side 161.851025 79.2215315 Rigth side 79.9264469 17507 17508 Left side Left side 17509 Left side 122.721282 Rigth side 17510 Left side 162.481652 Rigth side 116.021508 Rigth side 178.015728 Rigth side 173.717969 Rigth side 17511 17512 27500 Left side Left side Left side 135.402539 144.266185 117.054024 177.331277 175.263716 17507 17508 17511 17512 27500 Left side Left side Left side Left side Left side © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE 9-7 SKILL TEMPLATE FOR STATIC STRESS REPORTS APPENDIX A REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 ACD Sheets For information only See contractual data in ACD compilation ACD Sheets shall be generated with the application ACD Toolbox* If necessary put a copy of the generated Sheets in this Appendix *for any questions about the ACD Toolbox contact the Stress Helpdesk (BOS Stress) © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE A-1 SKILL TEMPLATE FOR STATIC STRESS REPORTS REFERENCE FM0300705 ISSUE 1.0 DATE 15 Nov 2011 APPENDIX B © EDDM S.L. 2017 ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. PAGE B-1