SRM57-10-00 2.0.0 57/57-10... · 2008. 8. 11. · 57-10-00 Jun 30/01 EFFECTIVITY: All Page 1 z SD3-60 STRUCTURAL REPAIR MANUAL SRM57-10-00 2.0.0.0 CENTRE WING - STRUCTURAL IDENTIFICATION

Jun 30/0157-10-00 Page 1EFFECTIVITY: All

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SRM57-10-00 2.0.0.0CENTRE 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 106.5 inches and is a self-flanged 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 137.0 inches consist of L72 webs with L73 booms.

Nose ribs at station 106.5 inches and 135.0 inches are manufactured from S527 material and act as firewalls. Ribs at stations 68.8 inches and 122.5 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 106.5 inches are of L73 material.



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.


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Key diagram - Centre wingFigure 1



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.

ITEM NO. MATERIAL THICKNESS/

GAUGE PART NO. DESCRIPTION

1 SD3-22-6004 G.A. Centre Wing Structure2 SD3-22-6008 G.A. of Skins3 SD3-25-0687 G.A. of Inner Flap - Left4 SD3-25-0688 G.A. of Inner Flap - Right5 SD3-22-0099 G.A. of Trailing Edge Flap Shroud6 SD3-22-0105 Access Door Assy7 SD3-22-0121 Access Door Assy8 SD3-22-0117 Assy of Hinge Arm - Stn.68.8 - Left9 SD3-22-0118 Assy of Hinge Arm - Stn.68.8 - Right

10 SD3-22-0119 Assy of Hinge Arm - Stn. 122.5 - Left11 SD3-22-0120 Assy of Hinge Arm - Stn. 122.5 - Right12 SD3-22-0953 Upper Fariing Wing Joint - Left13 SD3-22-0954 Upper Fairing Wing Joint - Right14 SD3-22-0951 Lower Fairing Wing Joint - Left15 SD3-22-0952 Lower Fairing Wing Joint - Right

Key to Figure 1



Structure - Centre WingFigure 2





1 - - SD3-22-6006 G.A. OF FRONT SPAR2 - - SD3-22-6007 G.A. OF REAR SPAR3 - - SD3-22-0113

SD3-22-0114G.A. OF L/E SPAR

4 - - SD3-22-0095 MAIN BOX RIB5 - - SD3-22-6041

SD3-22-6042MAIN BOX RIB

6 - - SD3-22-6043SD3-22-6044

MAIN BOX RIB

7 - - SD3-22-0029 MAIN BOX RIB8 - - SD3-22-0031 MAIN BOX RIB9 - - SD3-22-6045

SD3-22-6046MAIN BOX RIB

10 - - SD3-22-6047SD3-22-6048

MAIN BOX RIB

11 - - SD3-22-6049SD3-22-6050

MAIN BOX RIB

12 - - SD3-22-0039SD3-22-0040

MAIN BOX RIB

13 - - SD3-22-6115SD3-22-6116

MAIN BOX RIB

14 - - SD3-22-6051SD3-22-6052

MAIN BOX RIB

15 - - SD3-22-6053SD3-22-6054

MAIN BOX RIB

16 - - SD3-22-0047SD3-22-0048

MAIN BOX RIB

17 - - SD3-22-0049SD3-22-0050

MAIN BOX RIB

18 - - SD3-22-0051SD3-22-0052

MAIN BOX RIB

19 - - SD3-22-0053SD3-22-0054

NOSE BOX RIB

20 - - SD3-22-0055SD3-22-0056

NOSE BOX RIB

Key to Figure 2



21 - - SD3-22-0057SD3-22-0058

NOSE BOX RIB

22 - - SD3-22-0059SD3-22-0060

NOSE BOX RIB

23 - - SD3-22-0061SD3-22-0062

NOSE BOX RIB

24 - - SD3-22-6113SD3-22-6114

NOSE BOX RIB

25 - - SD3-22-0941SD3-22-0942

NOSE RIB FIREWALL ASSY

26 - - SD3-47-6025 ASSY ENG.CONTR CTR SECT.27 - - SD3-47-0101 ASSY ENG. CONTRS BOX (L)28 - - SD3-47-0103 ASSY ENG. CONTRS BOX (R)



Key to Figure 2



Top Skin diagram - Centre wingFigure 3



* 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.



1* L73 OR L165 .116" (11G) MAIN BOX TOP SKIN2 L72 OR L163 .104" (12G) BUTT STRAP3 L72 .036" (20G) *NOSE BOX TOP SKIN (OUTER)

BONDED4 L72 .028" (22G) *INNER SKIN5 L72 .018" (26G) *EDGE REINFORCING6 L72 .072" (15G) NOSE SKIN7 L73 .092" (13G) REINF. PLATE Stn 106.58 L73 .080" (14G) REINF. PLATE Stn 459 L72 .022" (24G) ***SHROUD ***PANEL (TOP) SKIN

10 L72 .028" (22G) ***T/E SKIN11 L72 .016" (27G) ***STRIP (BONDED)12 L72 .028" (22G) **SKIN-WING JOINT TOP SHROUD13 L72 .028" (22G) **EDGE STRIP14 L72 .048" (18G) **EDGE PACKING STRIP15* L73 .128" (10G) ACCESS PANEL

Key to Figure 3



Top Skin diagram - Centre wingFigure 4



*, **, *** 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



1 L73 OR L165 .064" (16G) * MAIN BOX BTM SKIN2 L73 OR L165 .018" (26G) * REINFORCING3 L73 OR L165 .022" (24G) * REINFORCING4 L72 .080" (14G) ** BUTTSTRAP5 L72 OR L163 .036" (20G) ** NOSE BOX BTM SKIN (OUTER)

BONDED6 L72 OR L163 .028" (22G) ** INNER SKIN7 L72 OR L163 .018" (26G) *** EDGE REINFORCING8 L73 .080" (14G) REINF. PLATE Stn 459 L73 .092" (13G) REINF. PLATE Stn 106.5

10 L72 .018" (26G) *** SHROUD PANEL SKIN11 L72 .022" (24G) *** DOUBLER12 L72 .018" (26G) � SHROUD PANEL SKIN13 L72 .022" (24G) � ZED MEMBER14 L72 .028" (22G) � SKIN-WING JOINT BTM SHROUD15 L72 .028" (22G) � EDGE STRIP16 L72 .048" (18G) � EDGE PACKING STRIP

17 $ L73 .128" (10G) ACCESS PANEL

Key to Figure 4



SRM57-10-00 3.0.0.0CENTRE 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 101.- Wing Shroud Skin. Refer to Table 102.- Wing Spar Web and Rib Web. Refer to Table 103.

Definition of types of damage. Refer to 51-10-00, pb1.

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NOTE: tb = thickness of skin

NOTE: * WING CORROSION, INSPECTION & REPAIR PROCEDURES. Refer to 51-10-00, pb1.

TYPE OF DAMAGE'D'

MAX DEPTH

'L' LENGTHMIN EDGE

DIST INCHES

MIN DIM FROM LINES OF

FASTENERSOTHER LIMITATIONS REMEDIAL ACTION

REQUIRED

Isolated dents 1.50xtb 10D min 1.00 1.00 Dents smooth and free of cracks and delamination.

No dents allowed on skin at rib station, along spar flanges or on stringer.

If beyond limits repair is required.

Gouges, nicks, scratches and surface corrosion* (See Note)

0.10xtb 0.50 max - - Must not extend over more than two adjacent fasteners except where damage does not exceed depth of cladding.

Clean up damageRefer to 51-10-00, pb1.


Punctures - - - - - Repair is required.

Cracks - - - - - Repair is required.

Allowable damage - Top & bottom skinTable 101

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NOTE: tss = thickness of shroud skin

NOTE: * WING CORROSION, INSPECTION & REPAIR PROCEDURES. sRefer to 51-10-00, pb1.

TYPE OF DAMAGE 'D' MAX DEPTH 'L' LENGTH

MIN EDGE DIST

INCHES

MIN DIM FROM LINES OF

FASTENERSOTHER LIMITATIONS REMEDIAL ACTION

REQUIRED

Isolated dents 2.00xtss 10D min 0.75 0.75 Dents smooth and free from cracks. No dents allowed in skin at rib station.


Gouges, nicks, scratches and surface corrosion

* (See Note)

0.10xtss 0.50 max - - Must not extend over more than two adjacent fasteners except where damage does not exceed depth of cladding.




Cracks - - - - - Repair is required.

Allowable damage - Wing shroud skinTable 102

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NOTE: ts = thickness of spar webtr = thickness of rib web

NOTE: * WING CORROSION, INSPECTION & REPAIR PROCEDURES. Refer to 51-10-00, pb1.

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

1.50xts 1.50xtr

10D min 10D min

--

1.001.00

Dents smooth and free from cracks.


Nicks, scratches, surface corrosion, and abrasions(1) Spar web(2) Rib web* (See Note)

0.10xts 0.10xtr

0.50 max 0.50 max

- - Must not extend over more than two adjacent fasteners, except where damage does not exceed depth of cladding.




Cracks(a) Radiating from lightening holes(b) Radiating from bend relief(c) Other cracks

- - - - -RepairRefer to 51-70-00, pb1.RepairRefer to 51-70-00, pb1.Repair is required.

Allowable damage - Wing spar web and rib webTable 103



SRM57-10-00 4.0.0.0CENTRE 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 201.- Flange and Web Repair - Wing Spar. Refer to Figure 202.- Typical Wing Shear Cleat Repair - Single Flange. Refer to Figure 203.- Typical Shroud T.E. Skin Repair (Flap and Aileron Shroud). Refer to Figure 204.- Typical Shroud Skin Repair (Flap Shroud). Refer to Figure 205.- Lower Wing Skin Repair at Flap Hinge Arm - STN.68.8. Refer to Figure 206.- Repair to wing top skin R.H.S. (Stn 75.5V - 118.5V). 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 98.20 R.H.S.. Refer to Figure 209 (Sheet 1).

A. Alternative materials.

Refer to 51-31-00, pb1.

B. Alternative Fasteners

Refer to 51-40-00, pb1.



Wing skin access panel for rib repairsFigure 201



Flange & web repair - Wing sparFigure 202



Typical wing shear cleat repairs - Single flangeFigure 203



Typical shroud trailing edge skin repairFigure 204



Typical shroud skin repairsFigure 205



Lower wing skin repair at flap hinge armFigure 206



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



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



Repair to centre wing skin panel top surface in way of stn 100 by installation of heat shieldsFigure 208 (Sheet 1)



Repair to center wing skin panel top surface in way of stn 100 by installation of heat shieldsFigure 208 (Sheet 2)



Repair to center wing skin panel top surface in way of stn 100 by installation of heat shieldsFigure 208 (Sheet 3)



Repair to nose box top skin Stn 98.20 R.H.S.Figure 209 (Sheet 1)



Repair to nose box top skin stn 98.20 R.H.S.Figure 209 (Sheet 2)

Documents

SRM57-10-00 2.0.0 57/57-10... · 2008. 8. 11. · 57-10-00 Jun 30/01 EFFECTIVITY: All Page 1 z SD3-60 STRUCTURAL REPAIR MANUAL SRM57-10-00 2.0.0.0 CENTRE WING - STRUCTURAL IDENTIFICATION