173 ROCHEFORT FAX: (33) 5 46 87 4 12 EFFECTIVITY PAGE DATE ISSUE PAGE DATE ISSUE PAGE DATE ISSUE 1 2 3 4 5 6 7 8 9 1 11 12 13 14 15 16 17 18 19 2 21 22 23 24 25 26 27 28 29 3 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 31 32 24/7/14 24/7/14 ILA-655D29826 2/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 INTENTIONALLY BLANK ILA-655D29826 5/32
TABLE OF CONTENTS 173 ROCHEFORT FAX: (33) 5 46 87 4 12 TITLE PAGE... 1 EFFECTIVITY... 2 BLANK PAGE... 3 REVISION... 4 BLANK PAGE... 5 TABLE OF CONTENTS... 6 1 INTRODUCTION... 7 1.1. LIST OF DRAWING... 7 1.2. TOOLS OF CALCULATION... 7 1.3. LIST OF REFERENCE... 8 1.4. UNITS... 8 1.5. LIST OF ACRONYMS... 9 1.6. AIRCRAFT REFERENCE SYSTEM AXIS... 1 1.7. AIRCRAFT INTERFACE MECHANICAL PROPERTIES... 11 1.8. LOAD CASES DEFINITION... 11 1.9. CENTER OF GRAVITY... 12 1.1. REARWARD RIGHT GALLEY A13/15-J11 P/N 655D29826 WEIGHT... 13 1.11. MESH GENERATION... 15 1.12. A/C INTERFACE POINTS AND BOUNDARY CONDITIONS... 2 1.13. MATERIALS AND FASTENERS MECHANICAL PROPERTIES... 22 1.13.1. Metallic materials... 22 1.13.2. Inserts mechanical properties... 22 1.13.3. Fasteners mechanical properties... 23 1.13.4. Sandwich panels dimensions and composition... 24 1.13.5. Sandwich panels mechanical properties... 3 2... 31 3 CONCLUSION... 32 ILA-655D29826 6/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 1 INTRODUCTION The purpose of this analysis is to produce a Interface Load Analysis Report Type of structure: REARWARD RIGHT GALLEY A13/15-J11 Part number: P/N 655D29826 Aircraft: n/a Location: Rwd Right Type of aircraft: ATR 42/72. The results of the analysis are the forces applied on aircraft mechanical interfaces. 1.1. LIST OF DRAWING The finite element model (FEM) of the stowage was performed according to the following drawing: General arrangement drawing: SMRD29826 1.2. TOOLS OF CALCULATION Meshing, solver, pre - and post-processing : Patran 28r2 & Nastran 28 r1a ILA-655D29826 7/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 1.3. LIST OF REFERENCE Applicable standards - documents references: EASA/CS 25: 25.31 25.33 25.35 25.37 25.561 25.67 25.613 25.625 ATR Technical specifications: DT/MD-59/14 ed 3 421.585-94 ed. 1: ATR 42 & ATR 72 Aménagement cabine new look Spécification technique d'équipements 419.98-9 ed. 19: ATR Spécification technique d'équipements Simair specification: A9 44.28 iss.3: Calculation datas ATR programs CDCC-DT/MD-59/14 iss.: Technical Specification Rearward right galley A13/15-J11 Technical reference book: Airframe Stress Analysis and Sizing, Michael Chun-Yung NIU 1.4. UNITS The units used in this report are: Length mm Mass kg Force N Moment N.mm Stiffness N/mm Pressure MPa (N/mm 2 ) Acceleration translation gravity m/s 2 Density kg/m 3 ILA-655D29826 8/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 1.5. LIST OF ACRONYMS A/C Aircraft CS e SRW M n x, n y, n z F x F y F z Mx M y M z g G Γ x Γ y Γ z ρ K x K y K z RF SM Rwd Fwd Swd Uwd Dwd Coordinate System Thickness Simulated Reconstituted Weight Mass Load factors Load Load Load Load Load Load Acceleration translation gravity Acceleration translation gravity Acceleration translation gravity Acceleration translation gravity Acceleration translation gravity Density Stiffness Stiffness Stiffness Reserve Factor Safety Margin Rearward Forward Sideward Upward Downward ILA-655D29826 9/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 1.6. AIRCRAFT REFERENCE SYSTEM AXIS The loading directions are given in Aircraft axes. +X: -X: +Y: -Y: +Z: -Z: REARWARD direction FORWARD direction RIGHT direction LEFT direction UP direction DOWN direction ILA-655D29826 1/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 1.7. AIRCRAFT INTERFACE MECHANICAL PROPERTIES Following values are extracted from document ref. A9 44.28 iss.3, 5. Lower attachments on seat tracks Kx = 15 N/mm Ky = 15 N/mm Kz = 5 N/mm Upper attachments with tie rod 15 N/mm in rod axis direction Table 1.7-1: Aircraft interface stiffness 1.8. LOAD CASES DEFINITION Ultimate loads for cabin furniture are extracted from document ref. CDCC-AJ-DT-MD-59-14 iss., Appendix A. Load case number Max flight and landing loads description 1 3.2g Upward 2 9.g Forward 3 3.g Sideward RH 4 3.g Sideward LH 5 7.8g Downward 6 2.1g Rearward 7 8 8.6g Fwd + 1.5g Swd RH + 2.g Uwd 8.6g Fwd + 1.5g Swd LH + 2.g Uwd 9 ABUSE LOAD (1) Table 1.8-1: Load cases description (1) An abuse load is considered to substantiate the mechanical behavior of the sliding table (see 1.1). This table must support a maximum loading of 4Kg modeled applying a equally distributed pressure on its surface and oriented down. ILA-655D29826 11/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 1.9. CENTER OF GRAVITY The estimated coordinates of the center of gravity for Rearward right galley A13/15-J11 P/N 655D29826 are provided in the aircraft axis by the Table 1.9-1. Nota: Internal equipments are represented by pressure loads on compartment surfaces (see 1.1), so the CoG location for galley with loading depends on which compartment face loads are applied. Then the CoG with loading determined below is the average location. CoG coordinate Without loadings With loadings (mm) (mm) CoG X coordinate 21455 21439 CoG Y coordinate 667 66 CoG Z coordinate 314 3259 Table 1.9-1: Coordinates of center of gravity in global system aircraft. ILA-655D29826 12/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 1.1. REARWARD RIGHT GALLEY A13/15-J11 P/N 655D29826 WEIGHT All internal equipments of the REARWARD RIGHT GALLEY A13/15-J11 P/N 655D29826 and their masses are detailed in the following Figure 1.1-1, Table 1.1-1 and Table 1.1-2. This finite element modeling was done with a total mass of 427.6 kg. 4 1 7 15 13 2 3 5 14 6 8 1 12 9 16 11 Figure 1.1-1: Internal equipments location ILA-655D29826 13/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 ITEM DESIGNATION CAPACITIES Qty STRUCTURAL WEIGHT 8 kg 1 1 HOT-JUG 18 kg 1 2 WORKING AREA 2 kg 1 3 WATER-HEATER 1.6 kg 1 4 STOWAGE 3 kg 1 5 BASIN - 1 7 WATER TANK 2 kg 1 8 HALF-SIZE TROLLEY 6 kg 1 9 HALF-SIZE TROLLEY 6 kg 1 1 DF 115 OVEN 51 kg 1 11 STOWAGE 12 kg 1 12 WASTE BIN 1 kg 1 13 SU 2 kg 1 14 SU 2 kg 1 15 STOWAGE 3 kg 1 EXTERNAL WEIGHT (STOWAGE) 4 kg 1 TOTAL WEIGHT 427.6 kg TOTAL WEIGHT WITHOUT TROLLEY 37.6 kg Table 1.1-1: Weight description of internal equipments The maximum loading of the two tables are given by the Table 1.1-2. TABLES MAXIMUM LOADING ITEM DESIGNATION CAPACITIES Qty 6 FOLDING TABLE 4 kg 1 16 SLIDING TABLE 4 kg 1 Table 1.1-2: Tables maximum loading In load case 7.8g downward, trolleys weight are not taken into account, because trolleys forces are applied onto floor panels, the total weight for this load case without trolley is 37.6 kg. ILA-655D29826 14/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 1.11. MESH GENERATION The finite element model is detailed below: Nodes: 9538 Elements: 88546 Lumped Mass: Rigid element: 229 Thin shell linear quadrilateral: 9632 Thin shell linear triangle: 18 Linear rod: 3 Solid linear tetrahedron: Node to ground translational spring: 6 Constraint element: 3 The folding table is meshed in closed position and the sliding table is fully extended. The finite element model is detailed in the following figures. ILA-655D29826 15/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 FEM CAD model Internal and external metal sheets of reinforcement (3mm thickness) [PRT-359-651D19237-2 / PRT-358-651D19236-2] replaced by 2 external corners in aluminum 217T4 (3mm thickness) (see Figure 1.11-5) Composite panels are meshed with coincident nodes except for regions detailed below Figure 1.11-1: Galley A13/15-J11 meshing (1/4) ILA-655D29826 16/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 FEM CAD model Panels connected to others with metallic plates (no coincident mesh) Panels connected to others with metallic plates (no coincident mesh) Figure 1.11-2: Galley A13/15-J11 meshing (2/4) ILA-655D29826 17/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 FEM CAD model Panels connected to others with metallic corners (no coincident mesh) Cut in the decorative band FEM Figure 1.11-3: Galley A13/15-J11 meshing (3/4) ILA-655D29826 18/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 FEM CAD model Two panels connected with rigid elements Figure 1.11-4: Galley J11 meshing (4/4) Lines of 5 fasteners NAS 181-3 attached to panels 22 mm 24 mm 24 mm 26 mm Faces of the two corners in aluminum 217 T4 are parallel to the panels with which they are attached. Figure 1.11-5: Galley J11 meshing Dimensions and attachment of corners added ILA-655D29826 19/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 1.12. A/C INTERFACE POINTS AND BOUNDARY CONDITIONS The Figure 1.12-1and Table 1.12-1 provide the location of the fitting points where the boundary conditions are applied and the constrained directions. 11 12 14 15 1 13 Figure 1.12-1: Lower attachments ILA-655D29826 2/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 2 6 4 Figure 1.12-2: Upper attachments Constraints (X: Fixed / -: Free) Location Type Ux Uy Uz Rx Ry Rz Point 2 (21655.5;635.;4215.5) Tie rod X X X X - - - Point 4 (21511.2;724.;4119.) Tie rod Y X X X - - - Point 6 (2983.;733.;4119.) Tie rod Y X X X - - - Point 1 (2115.7;325.;2338.7) Seat track X X X - - - Point 11 (21512.1;325;2338.7) Seat track X X X - - - Point 12 (21791.5;325.;2338.7) Seat track X X X - - - Point 13 (2115.7;96.;2338.7) Seat track X X X - - - Point 14 (21512.1;96.;2338.7) Seat track X X X - - - Point 15 (21791.5;96.;2338.7) Seat track X X X - - - Table 1.12-1: Coordinate locations of attachments in global system ILA-655D29826 21/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 1.13. MATERIALS AND FASTENERS MECHANICAL PROPERTIES 1.13.1. Metallic materials E (MPa) ν ρ (kg/mm 3 ) Ultimate tensile strength (MPa) Yield tensile strength (MPa) 224T3 & 724.33 2.78E-6 441 268.9 224T4 (1) 217A T4 (1) 72.33 2.8E-6 38 22.6 586 H111 (1) 72.33 2.8E-6 248 96 775T6 (1) 69.33 2.8E-6 515 442 Z1CNF18-9 (1) 19.3 7.9E-6 5 175 (1) values issue from document ref. A9 44.28 iss. 3, 8.1 Table 1.13-1: Metallic material properties For 224T3 & 224T4, the stress-strain curve is represented by the Ramberg-Osgood method: ε total =(σ/e) +.2 (σ/σ.2 ) n with: ε total : total strain σ: stress σ.2 ; yield stress E: modulus of elasticity n: Ramberg-Osgood parameter (n=11 for 224 series, and n=16 for 7175 series) n/a 1.13.2. Inserts mechanical properties ILA-655D29826 22/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 1.13.3. Fasteners mechanical properties Reference Diameter [mm] Ftu [N/mm²] Fsu [N/mm²] Tensile/Compression allowable load [N] Single shear allowable load [N] Rivet ASNA-78-A5-3 (1) 3.969 - - 1979 3736 NAS 112-4 (1) 6.35 88 528 29 1254 NAS 665 (1) 6.35 11 66 26125 291 NSA514P-132 (1) 4.826 88 528 11773 764 Screw NAS 134 (1) 6.35 - - 26126 15675 NAS 135 (1) 7.938 - - 41676 255 NAS181-3 (2) 4.82 - - 1259 755 651SP1 (1) 6.35 11 66 26125 291 Nut NSA 55-4 (3) 6.35 - - 2446 - NSA 55-5 (3) - - - 43 - Rod end NSA 8143-4 (1) 7.937 - - 2162 - NSA 8143-5 (1) 9.525 - - 3194 - (1) values extracted from A9.44.28 Calculations datas ATR Iss 3 (2) see standard: 16ksi=113 MPa (3) see standard NSA55 Table 1.13-2: Fasteners strength ILA-655D29826 23/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 1.13.4. Sandwich panels dimensions and composition These panels consist of a composite sandwich structure Skins Honeycomb ID THICKNESS CORE PLIES THICKNESS Honeycomb 2x2 Fabric 1 12.7 mm HRH1 3/16 2. 26/38%/7781.21 mm Honeycomb 2x3 Fabric 1B 12.7 mm HRH1 3/16 2. 26/38%/7781.21 mm Honeycomb 2x4 Fabric 2 12.7 mm HRH1 3/16 2. 26/38%/7781.21 mm Honeycomb 2x6 Fabric 3 12.7 mm HRH1 3/16 2. 26/38%/7781.21 mm 3B 12.7 mm 1x6 Fabric Honeycomb 1x4 Fabric HRH1 3/16 2. 26/38%/7781.21 mm Honeycomb 2x8 Fabric 4 12.7 mm HRH1 3/16 2. 26/38%/7781.21 mm 5 12.7 mm Honeycomb HRH1 3/16 2. 2x1 Fabric 26/38%/7781 Table 1.13-3: Sandwich panels composition.21 mm Nota : Some panels have a specific area designed with metallic plate between glasses plies. They are specified in drawings of panel s molding and detailed in figures below. All panels are sandwich panels defined within an optimized configuration, so: = 2x2 plies means: 2 plies + honeycomb + 2 plies = 2x4 plies means: 4 plies + honeycomb + 4 plies = 2x6 plies means: 6 plies + honeycomb + 6 plies = aluminum sheet (1mm) + 2 plies + honeycomb + 2 plies + aluminum sheet (1mm) ILA-655D29826 24/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 463 mm 487 mm Figure 3: Galley A13/15-J11 Laminate areas description (1/5) ILA-655D29826 25/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 161 mm 287 mm 198 mm Figure 4: Galley A13/15-J11 Laminate areas description (2/5) ILA-655D29826 26/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 2 mm 22 mm Figure 5: Galley A13/15-J11 Laminate areas description (3/5) ILA-655D29826 27/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 4mm 6mm 11mm 4mm 6mm 8mm 12mm 12mm Figure 6: Galley A13/15-J11 Laminate areas description (4/5) ILA-655D29826 28/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 6mm 1mm 43mm 61mm 112mm 185mm 165mm 125mm Figure 7: Galley A13/15-J11 Laminate areas description (5/5) ILA-655D29826 29/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 1.13.5. Sandwich panels mechanical properties Characteristics (1) HONEYCOMB HRH1 3/16 2. FABRIC 26/38%/7781 E1 (MPa) 1 27 E2 (MPa) 1 27 ν12.5.4 G12 (MPa) 1 42 G13 (MPa) 15 11 G23 (MPa) 15 11 ρ (kg/mm 3 ) 3.2E-8 2.333E-6 σ t1 (MPa) 1.1 265 σ c1 (MPa).8 2 σ t2 (MPa) 1.1 265 σ c2 (MPa).8 2 τ 12 (MPa).32 24 ply thickness (mm).21 (1) values issue from ref. A9 44.28 iss. 3, 8.7, except for G12, G13 and G23 values extracted from doc - CAQ/DT/NT/25 iss.a - SA-653B498142 iss. Table 1.13-4: Sandwich panels mechanical properties ILA-655D29826 3/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 2 The following Table 1.13-1 provides the action load of galley A and D onto aircraft structure. Loads components are defined in aircraft axis system. Table 1.13-1: Interface loads ILA-655D29826 31/32
173 ROCHEFORT FAX: (33) 5 46 87 4 12 3 CONCLUSION The Table 1.13-1 provides the maximum and minimum forces at aircraft interfaces into its coordinate: Table 1.13-1: Max and min interface loads (N) ILA-655D29826 32/32