SD3-60 STRUCTURAL REPAIR MANUAL - STRUCTURAL IDENTIFICATION

Transcription

1 SRM CENTRE WING - STRUCTURAL IDENTIFICATION 1. General This subject identifies the structural components and skin plating of the centre wing. Details are given of specific location, material specifications and related commercial designations, material thicknesses, references to applicable repair schemes contained in the manual, as well as limits of allowable damage. 2. Construction The centre wing consists of a conventional all metal construction with front and rear spars which extend the full length of the centre wing. The front spar web of L72 material has a manufactured joint at the centreline and is reinforced locally at system penetration and inspection holes. The front spar top and bottom booms are machined angle sections of 7075-T73510 material, the top boom being continuous whilst the bottom boom is broken each side of the centreline. The rear spar is of a similar construction to the front spar and supports the flap trailing edge shrouds and control surfaces. The leading edge spar extends between wing station 45 inches and inches and is a selfflanged construction of L72 material with vertical stiffeners. Ribs are numbered using wing stations measured from the centreline of the aircraft outboard and are intercostal to the spars. Ribs generally consist of a self flanged diaphragm of L72 material with stringer cutouts ans separate shear cleats; End ribs at station inches consist of L72 webs with L73 booms. Nose ribs at station inches and inches are manufactured from S527 material and act as firewalls. Ribs at stations 68.8 inches and inches are locally reinforced to support the flap hinge arms. These hinge arms are attached through L64 machined brackets which are located at the lower inside skin and on the aft face of the rear spar at the rib datums. The chemi-etched centre wing upper and lower skins of L73 material are formed in two sections joined at the centreline using a buttstrap of L72 material. Along the surface of the upper skin are panels of L73 material for access to various systems. Shroud panels, nose box skins, leading edge skins and wing joints are of L72 material. Local reinforcing plates on both top and bottom skins at stations 45.0 inches and inches are of L73 material. Page 1

2 The stringers for both top and bottom skins are formed 'Z' section members of L73 material rivetted to the respective skins, and machined parts are used in high stress areas. 3. Structural Identification The following pages contain diagrams and text to define the components, skin materials and thicknesses that comprise the centre wing. Page 2

3 Key diagram - Centre wing Figure 1 Page 3

4 ITEM NO. MATERIAL THICKNESS/ GAUGE Items 1, 2, 3 & 4 Structural Classification is not applicable. Items 6, 7, 8, 9, 10 & 11 are Class 2. Items 5, 12, 13, 14 & 15 are Class 3. PART NO. DESCRIPTION 1 SD G.A. Centre Wing Structure 2 SD G.A. of Skins 3 SD G.A. of Inner Flap - Left 4 SD G.A. of Inner Flap - Right 5 SD G.A. of Trailing Edge Flap Shroud 6 SD Access Door Assy 7 SD Access Door Assy 8 SD Assy of Hinge Arm - Stn Left 9 SD Assy of Hinge Arm - Stn Right 10 SD Assy of Hinge Arm - Stn Left 11 SD Assy of Hinge Arm - Stn Right 12 SD Upper Fariing Wing Joint - Left 13 SD Upper Fairing Wing Joint - Right 14 SD Lower Fairing Wing Joint - Left 15 SD Lower Fairing Wing Joint - Right Key to Figure 1 Page 4

5 Structure - Centre Wing Figure 2 Page 5

6 ITEM NO. MATERIAL THICKNESS/ GAUGE PART NO. DESCRIPTION SD G.A. OF FRONT SPAR SD G.A. OF REAR SPAR SD G.A. OF L/E SPAR SD SD MAIN BOX RIB SD MAIN BOX RIB SD SD MAIN BOX RIB SD SD MAIN BOX RIB SD MAIN BOX RIB SD MAIN BOX RIB SD SD MAIN BOX RIB SD SD MAIN BOX RIB SD SD MAIN BOX RIB SD SD MAIN BOX RIB SD SD MAIN BOX RIB SD SD MAIN BOX RIB SD SD MAIN BOX RIB SD SD MAIN BOX RIB SD SD MAIN BOX RIB SD SD NOSE BOX RIB SD SD SD NOSE BOX RIB Key to Figure 2 Page 6

7 ITEM NO. MATERIAL THICKNESS/ GAUGE PART NO. DESCRIPTION SD NOSE BOX RIB SD SD NOSE BOX RIB SD SD NOSE BOX RIB SD SD NOSE BOX RIB SD SD NOSE RIB FIREWALL ASSY SD SD ASSY ENG.CONTR CTR SECT SD ASSY ENG. CONTRS BOX (L) SD ASSY ENG. CONTRS BOX (R) Key to Figure 2 Page 7

8 Top Skin diagram - Centre wing Figure 3 Page 8

9 ITEM NO. MATERIAL * and ** denote bonded components (Redux) ** denotes rivetted & bonded components (Redux) * denotes these items are chemi-etched. Items 1 thru 8, and item 15 are Class 2 Items 8 thru 14 are Class 3. THICKNESS/ GAUGE PART NO. DESCRIPTION 1* L73 OR L " (11G) MAIN BOX TOP SKIN 2 L72 OR L " (12G) BUTT STRAP 3 L72.036" (20G) *NOSE BOX TOP SKIN (OUTER) BONDED 4 L72.028" (22G) *INNER SKIN 5 L72.018" (26G) *EDGE REINFORCING 6 L72.072" (15G) NOSE SKIN 7 L73.092" (13G) REINF. PLATE Stn L73.080" (14G) REINF. PLATE Stn 45 9 L72.022" (24G) ***SHROUD ***PANEL (TOP) SKIN 10 L72.028" (22G) ***T/E SKIN 11 L72.016" (27G) ***STRIP (BONDED) 12 L72.028" (22G) **SKIN-WING JOINT TOP SHROUD 13 L72.028" (22G) **EDGE STRIP 14 L72.048" (18G) **EDGE PACKING STRIP 15* L73.128" (10G) ACCESS PANEL Key to Figure 3 Page 9

10 Top Skin diagram - Centre wing Figure 4 Page 10

11 ITEM NO. MATERIAL THICKNESS/ GAUGE *, **, *** and denote bonded components (Redux) denotes rivetted components $ denotes this item is chemi-etched Items 1 thru 9 and 17, are Class 2. Items 10 thru 16 are Class 3 PART NO. DESCRIPTION 1 L73 OR L " (16G) * MAIN BOX BTM SKIN 2 L73 OR L " (26G) * REINFORCING 3 L73 OR L " (24G) * REINFORCING 4 L72.080" (14G) ** BUTTSTRAP 5 L72 OR L " (20G) ** NOSE BOX BTM SKIN (OUTER) BONDED 6 L72 OR L " (22G) ** INNER SKIN 7 L72 OR L " (26G) *** EDGE REINFORCING 8 L73.080" (14G) REINF. PLATE Stn 45 9 L73.092" (13G) REINF. PLATE Stn L72.018" (26G) *** SHROUD PANEL SKIN 11 L72.022" (24G) *** DOUBLER 12 L72.018" (26G) SHROUD PANEL SKIN 13 L72.022" (24G) ZED MEMBER 14 L72.028" (22G) SKIN-WING JOINT BTM SHROUD 15 L72.028" (22G) EDGE STRIP 16 L72.048" (18G) EDGE PACKING STRIP 17 $ L73.128" (10G) ACCESS PANEL Key to Figure 4 Page 11

12 SRM CENTRE WING - ALLOWABLE DAMAGE 1. General This subject defines the allowable damage limitations for the aircraft centre wing. The limitations are given in tabular form as follows: - Wing Top & Bottom Skin. Refer to Table Wing Shroud Skin. Refer to Table Wing Spar Web and Rib Web. Refer to Table 103. Definition of types of damage. Refer to , pb1. Page 101

13 TYPE OF DAMAGE 'D' MAX DEPTH 'L' LENGTH MIN EDGE DIST INCHES MIN DIM FROM LINES OF FASTENERS OTHER LIMITATIONS REMEDIAL ACTION REQUIRED Isolated dents 1.50xtb 10D min Dents smooth and free of cracks and delamination. Gouges, nicks, scratches and surface corrosion * (See Note) No dents allowed on skin at rib station, along spar flanges or on stringer. If beyond limits repair is required. 0.10xtb 0.50 max - - Must not extend over more than two adjacent fasteners except where damage does Clean up damage Refer to , pb1. not exceed depth of cladding. If beyond limits repair is required. Punctures Repair is required. Cracks Repair is required. owable damage - Top & bottom skin Table 101 NOTE: tb = thickness of skin Page 102 NOTE: * WING CORROSION, INSPECTION & REPAIR PROCEDURES. Refer to , pb1.

14 TYPE OF DAMAGE 'D' MAX DEPTH 'L' LENGTH MIN EDGE DIST INCHES MIN DIM FROM LINES OF FASTENERS OTHER LIMITATIONS REMEDIAL ACTION REQUIRED Isolated dents 2.00xtss 10D min Dents smooth and free from cracks. No dents allowed in skin at rib station. Gouges, nicks, scratches and surface corrosion * (See Note) NOTE: tss = thickness of shroud skin 0.10xtss 0.50 max - - Must not extend over more than two adjacent fasteners except where damage does not exceed depth of cladding. If beyond limits repair is required. Clean up damage Refer to , pb1. If beyond limits repair is required. Punctures Repair is required. Cracks Repair is required. owable damage - Wing shroud skin Table 102 NOTE: * WING CORROSION, INSPECTION & REPAIR PROCEDURES. srefer to , pb1. Page 103

15 TYPE OF DAMAGE 'D' MAX DEPTH 'L' LENGTH MIN EDGE DIST INCHES MIN DIM FROM LINES OF FASTENERS OTHER LIMITATIONS REMEDIAL ACTION REQUIRED Isolated dents (1) Spar web (2) Rib web Nicks, scratches, surface corrosion, and abrasions (1) Spar web (2) Rib web * (See Note) 1.50xts 1.50xtr 0.10xts 0.10xtr 10D min 10D min 0.50 max 0.50 max Dents smooth and free from cracks. - - Must not extend over more than two adjacent fasteners, except where damage does not exceed depth of cladding. If beyond limits repair is required. Clean up damage Refer to , pb1. If beyond limits repair is required. Punctures Repair is required. Cracks (a) Radiating from lightening holes (b) Radiating from bend relief (c) Other cracks owable damage - Wing spar web and rib web Table 103 Repair Refer to , pb1. Repair Refer to , pb1. Repair is required. Page 104 NOTE: ts = thickness of spar web tr = thickness of rib web NOTE: * WING CORROSION, INSPECTION & REPAIR PROCEDURES. Refer to , pb1.

16 SRM CENTRE WING - REPAIRS 1. General The following pages contain details of approved repairs to the centre section of the aircraft mainplane. Reference must also be made to CHAPTER 51 for further information on structural damage and repair practices of a general nature. 2. List of Approved Repairs: - Wing Skin Access Panel for Rib Repairs. Refer to Figure Flange and Web Repair - Wing Spar. Refer to Figure Typical Wing Shear Cleat Repair - Single Flange. Refer to Figure Typical Shroud T.E. Skin Repair (Flap and Aileron Shroud). Refer to Figure Typical Shroud Skin Repair (Flap Shroud). Refer to Figure Lower Wing Skin Repair at Flap Hinge Arm - STN Refer to Figure Repair to wing top skin R.H.S. (Stn 75.5V V). Refer to Figure 207 (Sheet 1). - Repair to centre wing skin panel top surface in way of stn 100 by installation of heat shields. Refer to Figure 208 (Sheet 1). - Repair to nose box top skin stn R.H.S.. Refer to Figure 209 (Sheet 1). A. Alternative materials. Refer to , pb1. B. Alternative Fasteners Refer to , pb1. Page 201

17 Wing skin access panel for rib repairs Figure 201 Page 202

18 Flange & web repair - Wing spar Figure 202 Page 203

19 Typical wing shear cleat repairs - Single flange Figure 203 Page 204

20 Typical shroud trailing edge skin repair Figure 204 Page 205

21 Typical shroud skin repairs Figure 205 Page 206

22 Lower wing skin repair at flap hinge arm Figure 206 Page 207

23 Repair to wing top skin R.H.S. (Stn 75.5V-118.5V) Figure 207 (Sheet 1) Page 208

24 Repair to Wing Top Skin R.H.S. Stn 75. 5V-118.5V Figure 207 (Sheet 2) Page 209

25 Repair to centre wing skin panel top surface in way of stn 100 by installation of heat shields Figure 208 (Sheet 1) Page 210

26 Repair to center wing skin panel top surface in way of stn 100 by installation of heat shields Figure 208 (Sheet 2) Page 211

27 Repair to center wing skin panel top surface in way of stn 100 by installation of heat shields Figure 208 (Sheet 3) Page 212

28 Repair to nose box top skin Stn R.H.S. Figure 209 (Sheet 1) Page 214

29 Repair to nose box top skin stn R.H.S. Figure 209 (Sheet 2) Page 215