A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

ATA SYSTEM : 57

TITLE : WINGS - BOTTOM SKIN PANEL NO.2 - AILERON ACCESS DOOR - INSTALL REINFORCING

PLATE

MODIFICATION No. : 12525H5572

This page transmits Revision No. 03 of Service Bulletin No. A310-57-2081

ADDITIONAL WORK

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

This Service Bulletin has been issued at Revision 03 to inform operators that:

- the Part Nos. of the Landings supplied by the operator have been amended

- the countersink washers, Items 18 and 19, are used to fill the existing countersinks in the aileron

hinge ribs.

The opportunity has also been taken to update the effectivity.

CHANGES

SUMMARY :

- EFFECTIVITY

. Effectivity revised.

PLANNING INFORMATION :

- EFFECTIVITY

. 1.A. Effectivity revised. NOTE added.

MATERIAL INFORMATION :

- Price and Availability

. 2.A.(2) Cost updated for Kit B01 and Kit B02.

- LIST OF MATERIALS - OPERATOR SUPPLIED

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 1 of 2

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

. 2.D.(2) The Part Nos. of the Landings have been amended.

ACCOMPLISHMENT INSTRUCTIONS :

- GENERAL

. 3.A. CAUTION has been updated.

- MODIFICATION

. 3.B.(1)(a)2 The Part Nos. of the Landings have been amended.

. 3.B.(1)(b)3 NOTE added.

NOTE : Layout changes due to computerization of this revision are not identified.

FILING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

Revision 01 was issued to change the Kit prices and to add an inspection procedure for cracks in the

landing-plate before embodying the modification.

Revision 02 was issued to inform operators that:

- the reference to, Item 6 NSA5476VHK5-10 has been amended to NSA5478VHK5-10 in the

modification worksteps

- the manhours have been increased to 28 manhours

- the embodiment of the modification is now recommended at 10,200 FC

- other minor changes to this Service Bulletin have been added.

REVISION SEQUENCE

ORIGINAL : Jun 11/02

REVISION No. : 01 - Feb 26/03

REVISION No. : 02 - Oct 18/07

REVISION No. : 03 - Oct 13/10

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is

not approved for modification of the aircraft

ATA SYSTEM : 57

TITLE : WINGS - BOTTOM SKIN PANEL NO.2 - AILERON ACCESS DOOR - INSTALL REINFORCING

PLATE

MODIFICATION No. : 12525H5572

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

On the full scale wing fatigue test, skin cracking occurred in the area covered by this modification. The crack

was found at 51,500 simulated flights and started from one of the access door landing plate attachment

holes. Service Bulletin A310-57-2004 (Modification 05106H0894) was issued for the removal of the clearance

fit bolts, the holes reamed oversize and the installation of interference fit bolts. The mandatory Inspection

Service Bulletin A310-57-2037 (now superseded by Inspection Service Bulletin A310-57-2082) was also

issued for HFEC inspections around the bolt heads of the access door landing to detect cracks.

During routine maintenance on a Post Mod. 05106H0894 A310 aircraft, a crack of 62mm in length was

found on the RH wing in the bottom skin panel. The crack was found at the trailing edge, forward of the

all-speed-aileron servo control bay access door.

This Service Bulletin has been issued for a modification to the LH and RH wing, as follows:

- the cutting of the aileron access door landing plate into three parts

- the cold expansion of the landing plate fastener holes

- the installation of an interference fit plug

- the installation of an external reinforcing plate

- the cold expansion of the reinforcing plate attachment holes

- the installation of interference fit fasteners.

The embodiment of this Service Bulletin will prevent costly and time consuming repairs and should also

ensure that the area is crack free beyond the Extended Service Goal (ESG) of the aircraft.

The accomplishment of this Service Bulletin cancels the inspection requirements of the Inspection Service

Bulletin A310-57-2082.

This Service Bulletin also supersedes Service Bulletin A310-57-2004 beyond the extended service goal of

the aircraft.

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 1 of 3

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

SUMMARY

EVALUATION TABLE

COMPLIANCE Recommended CANCELS INSPECTION SB A310-57-2082

POTENTIAL AD No A/C OPERATION AFFECTED No

RELIABILITY AFFECTED No PAX COMFORT AFFECTED No

COST SAVING Yes ETOPS AFFECTED No

STRUCTURAL LIFE EXTN Yes VENDOR SB INVOLVED No

KIT PRICE (USD) B01R01 3440 KIT PRICE (USD) B02R01 3440

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 12525H5572

As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural

strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes

are major changes.

EFFECTIVITY

This Service Bulletin is applicable to this (these) operator(s) :

18T 19U 52X 58X 82Z 83V 98W 99Y ACQ AFG AIB AIC BAF BBC BLE CFC DAH DEC DGA F2I FDX G8E

GAF HFY I2L IRA IRM IYE JAB JAV K1P KAC KTC KYV KZU MGL MWA PIA QAF R1T RJA ROT RZO SBI

SGX SUD THY TSC UZB WHT WTJ

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : 57-20-00-019

OEB : None

AOT : None

SIL : None

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

SUMMARY

OTHERS : None

NATURE OF THE WORK

AIRCRAFT : Yes

EQUIPMENT : No

HARD : No

SOFT : No

OBRM : No

MANPOWER

Config. 01

TOTAL MANHOURS 28.0

ELAPSED TIME (HOURS) 14.0

MATERIAL INFORMATION

AIRCRAFT DATA

Config. 01 aircraft require Kit 572081B01R01 and Kit 572081B02R01 consisting of, reinforcing plates,

skin hole plugs and fasteners.

APPENDICES

None

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 3

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 4

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

ATA SYSTEM : 57

TITLE : WINGS - BOTTOM SKIN PANEL NO.2 - AILERON ACCESS DOOR - INSTALL REINFORCING

PLATE

MODIFICATION No. : 12525H5572

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property

of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information

contained in it. It is delivered on the express condition that said document and the information contained in

it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby

delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any

manner (except for the purposes of performing the tasks described hereunder and provided that any recipient

of such document shall comply with the conditions herein), without AIRBUS’ prior written consent.

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Models

310-203 310-204 310-221 310-222 310-304 310-308 310-322 310-324 310-325

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft MSN :

0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260

0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0303 0309 0313 0316 0318

0320 0326 0331 0333 0335 0338 0339 0342 0343 0345 0346 0353 0355-0357 0359

0360 0362 0364 0367 0369 0370 0372 0375 0378 0379 0386 0389 0390 0392 0394

0397 0399 0400 0406 0407 0410 0413 0416 0418 0419 0421 0422 0425 0427-0429

0431 0434 0436 0437 0439 0441 0444-0449 0452 0454 0456-0458 0467 0472 0473

0475 0476 0478 0480-0492 0494-0500 0502 0503 0519 0520 0522-0524 0526 0527

0531 0534 0537-0539 0541 0542 0544 0545 0547 0549-0552 0562 0564 0565 0567

0568 0571 0573 0574 0576 0585-0588 0590-0595 0597 0599 0600 0620 0622 0624

0636 0638 0640 0642 0644 0646-0654 0656 0658 0660 0661 0663 0665 0667

0669 0671 0672 0674 0676 0678 0680 0682 0684 0686 0687 0689 0691 0693

0697 0700 0702 0704 0706

(b) Effectivity by Operator

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 1 of 20

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A310

SERVICE BULLETIN

The Operator/MSN relationship is provided for information only and is correct at the

time of issue in accordance with the information available to AIRBUS. Any future

changes resulting from transfer of an aircraft from one operator to another will not be

reflected in this list unless the Service Bulletin is revised for another reason.

OPERATOR MSN

18T 0473

19U 0399

52X 0410

58X 0431

82Z 0550 0551

83V 0427

98W 0672

99Y 0489

ACQ 0538 0544

AFG 0496 0497

AIB 0686

AIC 0392 0406 0407 0413 0428 0429 0654 0665 0669 0680

BAF 0367 0372

BBC 0594 0642 0700

BLE 0650 0674

CFC 0425 0441 0444 0446 0482

DAH 0291 0293

DEC 0684 0693 0697

DGA 0418 0421 0422

F2I 0309 0487

FDX 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251

0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0297 0303

0313 0316 0318 0326 0331 0333 0335 0339 0342 0343 0345 0346

0353 0355 0356 0359 0360 0362 0364 0369 0378 0394 0397 0400

0439 0449 0452 0454 0456 0457 0458 0467 0492 0500 0534 0539

0542 0549 0552 0593 0638

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 2

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A310

SERVICE BULLETIN

OPERATOR MSN

G8E 0475

GAF 0434 0484 0498 0499 0503 0522 0523

HFY 0495 0565

I2L 0640

IRA 0338 0370 0375 0379 0389 0390 0436 0671

IRM 0488 0537 0564 0586 0595

IYE 0568 0702 0704

JAB 0320 0419

JAV 0357 0481

K1P 0648

KAC 0647 0649 0663

KTC 0524 0567 0620

KYV 0386

KZU 0592 0622 0646

MGL 0526

MWA 0652

PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691

QAF 0667

R1T 0591

RJA 0416 0445 0490 0491 0531

ROT 0636 0644

RZO 0571 0624 0651 0661

SBI 0486 0520

SGX 0519 0562

SUD 0437

THY 0476 0478 0480 0502

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 3

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A310

SERVICE BULLETIN

OPERATOR MSN

TSC 0447 0472 0483 0485 0527 0541 0545 0547 0588 0597 0599

0600 0658

UZB 0574 0576 0706

WHT 0448 0573

WTJ 0494

(c) Effectivity by MSN and Kit/Configuration

The Kits and configurations applicable to these MSNs are given at the end of this list

0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257

0260 0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0303 0309 0313

0316 0318 0320 0326 0331 0333 0335 0338-0339 0342-0343 0345-0346 0353

0355-0357 0359-0360 0362 0364 0367 0369-0370 0372 0375 0378-0379 0386

0389-0390 0392 0394 0397 0399-0400 0406-0407 0410 0413 0416 0418-0419

0421-0422 0425 0427-0429 0431 0434 0436-0437 0439 0441 0444-0449 0452 0454

0456-0458 0467 0472-0473 0475-0476 0478 0480-0492 0494-0500 0502-0503

0519-0520 0522-0524 0526-0527 0531 0534 0537-0539 0541-0542 0544-0545

0547 0549-0552 0562 0564-0565 0567-0568 0571 0573-0574 0576 0585-0588

0590-0595 0597 0599-0600 0620 0622 0624 0636 0638 0640 0642 0644 0646-0654

0656 0658 0660-0661 0663 0665 0667 0669 0671-0672 0674 0676 0678 0680 0682

0684 0686-0687 0689 0691 0693 0697 0700 0702 0704 0706

KIT No. QTY PER A/C CONFIGURATION

572081B01R01 1 01

572081B02R01 1 01

NOTE : Config. 01 is valid for all aircraft given in the effectivity of this Service

Bulletin.

NOTE : Kit 572081B01R01 contains the components for the LH wing.

NOTE : Kit 572081B02R01 contains the components for the RH wing.

NOTE : The Repair Instruction R57349237 with the steel plate

R57349236202/203 and Repair Instruction R57349243 with the

aluminium plate are equivalent to this modification.

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 4

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A310

SERVICE BULLETIN

C. REASON

(1) History

On the full scale wing fatigue test, skin cracking occurred in the area covered by this

modification. The crack was found at 51,500 simulated flights and started from one of the

access door landing plate attachment holes. Service Bulletin A310-57-2004 (Modification

05106H0894) was issued for the removal of the clearance fit bolts, the holes reamed

oversize and the installation of interference fit bolts. The mandatory Inspection Service

Bulletin A310-57-2037 (now superseded by Inspection Service Bulletin A310-57-2082)

was also issued for HFEC inspections around the bolt heads of the access door landing

to detect cracks.

During routine maintenance on a Post Mod. 05106H0894 A310 aircraft, a crack of 62mm in

length was found on the RH wing in the bottom skin panel. The crack was found at the

trailing edge, forward of the all-speed-aileron servo control bay access door.

(2) Objective/Action

This Service Bulletin has been issued for a modification to the LH and RH wing, as follows:

- the cutting of the aileron access door landing-plate into three parts

- the cold expansion of the landing-plate fastener holes

- the installation of an interference fit plug at a fastener hole

- the installation of an external repair plate

- the cold expansion of the repair plate attachment holes

- the installation of interference fit fasteners.

(3) Advantages

The embodiment of this modification will prevent costly and time consuming repairs and

should also ensure that the area is crack free beyond the extended service goal of the

aircraft.

The accomplishment of this Service Bulletin cancels the inspection requirements of the

Inspection Service Bulletin A310-57-2082 beyond the ESG of the aircraft.

This Service Bulletin also supersedes Service Bulletin A310-57-2004.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to:

(1) Config. 01

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 5

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A310

SERVICE BULLETIN

(a) Get access to the modification areas at the all-speed-aileron servo control bay

(underside of the LH and RH wing).

(b) Do an HFEC inspection of the access panel landing-plate for cracks.

(c) Remove the applicable fasteners and the access panel landing-plate.

(d) Do an HFEC inspection of the landing-plate fastener holes in the wing skin for cracks.

(e) If a crack is found at the fastener hole shown in Detail A of Figure 1, do a repair in

accordance with Inspection Service Bulletin A310-57-2082.

(f) If cracks are found in other areas of the landing-plate fasteners, contact AIRBUS,

SEE-82 for instructions.

(g) If cracks are not found do the modification, as follows:

1 Transfer drill the pilot holes from the external reinforcing plate into the wing skin.

2 Ream, cold expand and countersink all the fastener holes.

3 Mark the cut lines on the landing-plate and then remove it.

4 Cut the landing-plate into three sections.

5 Install the three sections of the landing-plate.

6 Install a fastener hole plug.

7 Install the external aluminium reinforcing plate.

8 Apply protective coating to the modification area.

9 Reidentify the landing-plates.

10 Close up.

E. COMPLIANCE

(1) Classification

Recommended

(2) Accomplishment Timescale

It is recommended to embody this modification at or before 10,200 FC.

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA.21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS

origin, and which affects the content of this Service Bulletin, the operator is responsible for

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 6

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

obtaining approval by its airworthiness authority for any adaptation necessary before incorporation

of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the

work. These estimates assume that the work will be done by experienced personnel, and may

need to be revised upwards to suit operator’s circumstances. The estimates do not include the

time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying

times for paints, sealants, etc, and general administration work are also not included.

Config. 01

Get access 1.0

Prepare modification on the LH wing 9.0

Install modification on the LH wing 4.0

Prepare modification on the RH wing 9.0

Install modification on the RH wing 4.0

Close up 1.0

TOTAL MANHOURS 28.0

ELAPSED TIME (HOURS) 14.0

H. WEIGHT AND BALANCE

Config. 01

Manufacturers Empty Weight : +1.54 kg (+3.39 lb)

Effect on Balance : +43.16 kgm (+311.69 lb.ft)

I. ELECTRICAL LOAD DATA

Not applicable

J. REFERENCES

Aircraft Maintenance Manual (AMM) : 06-41-57 24-00-00

Structural Repair Manual (SRM) : 51-20-00 51-23-10 51-24-00 51-27-00

51-40-41 51-40-21 51-40-44 51-40-47

51-40-50 51-43-00 51-75-10 51-76-10

Nondestructive Testing Manual (NTM) : 51-10-01

Aircraft Maintenance Manual (AMM) : 06-41-57 24-00-00

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A310

SERVICE BULLETIN

Elec. Std. Practices Manual (ESPM) : 20-55-00

Service Bulletin (SB) : A310-57-2004 A310-57-2037

A310-57-2082

Process and Material Specification (PMS) : 01-06-12

K. PUBLICATIONS AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

None

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SERVICE BULLETIN

2. MATERIAL INFORMATION

A. MATERIAL - PRICE AND AVAILABILITY

(1) Material

Customers with aircraft shown in the effectivity of this Service Bulletin should send a

purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is :

AIRBUS

SPARES SUPPORT AND SERVICES

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet: http://spares.airbus.com

For ordering by fax: +49 40 50 76 25 90

(2) Price and Availability

Kit 572081B01R01

Cost : 3440 US dollars

Availability : 120 calendar days from receipt of order

The sales terms (cost and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin

Kit 572081B02R01

Cost : 3440 US dollars

Availability : 120 calendar days from receipt of order

The sales terms (cost and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin

NOTE : The kit availability given is the standard lead time from the date of your

purchase order. If you require the kit(s) before this time, please include your

retrofit planning schedule with your order so that we can try to comply with

your requirements.

B. INDUSTRY SUPPORT INFORMATION

None

C. LIST OF COMPONENTS

Kit 572081B01R01

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

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A310

SERVICE BULLETIN

1 NSA5476VHK4-6 11 Bolt

2 NSA5476VHK4-10 6 Bolt

3 NSA5478VHK4-12 4 Bolt

4 NSA5476VHK5-6 6 Bolt

5 NSA5476VHK5-8 4 Bolt

6 NSA5478VHK5-10 1 Bolt

7 NSA5478VHK5-12 1 Bolt

8 NSA5478VHK5-14 2 Bolt

9 NSA5478VHK5-16 2 Bolt

10 NSA5478VHK6-14 4 Bolt

11 NSA5478VHK6-16 1 Bolt

12 NSA5472-4K7 21 Nut

13 NSA5472-5K7 16 Nut

14 NSA5472-6K7 5 Nut

15 NSA5353D05B 16 Washer

16 NSA5353D04B 21 Washer

17 NSA5353D06B 5 Washer

18 R5704003020200 4 Washer

19 R5704003020400 5 Washer

20 R5734923620000 1 Plate

28 A5735801520000 1 Plug

Kit 572081B02R01

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

1 NSA5476VHK4-6 11 Bolt

2 NSA5476VHK4-10 6 Bolt

3 NSA5478VHK4-12 4 Bolt

4 NSA5476VHK5-6 6 Bolt

5 NSA5476VHK5-8 4 Bolt

6 NSA5478VHK5-10 1 Bolt

7 NSA5478VHK5-12 1 Bolt

8 NSA5478VHK5-14 2 Bolt

9 NSA5478VHK5-16 2 Bolt

10 NSA5478VHK6-14 4 Bolt

11 NSA5478VHK6-16 1 Bolt

12 NSA5472-4K7 21 Nut

13 NSA5472-5K7 16 Nut

14 NSA5472-6K7 5 Nut

15 NSA5353D05B 16 Washer

16 NSA5353D04B 21 Washer

17 NSA5353D06B 5 Washer

18 R5704003020200 4 Washer

19 R5704003020400 5 Washer

21 R5734923620100 1 Plate

28 A5735801520000 1 Plug

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 10

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A310

SERVICE BULLETIN

DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP

MAT No.

Sealant Mat. No. 09-002 As required

Sealant Mat. No. 09-005 As required

Cleaning agent Mat. No. 11-026 As required

Alodine Mat. No. 13-002 As required

Primer Mat. No. 16-006 As required

(2) Components

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

A5724279520001 1 Landing

A5724279520101 1 Landing

NOTE : The items above will only be necessary if the old landings are found to be

cracked. If necessary, procure by spares purchase order.

E. PARTS TO BE RE-IDENTIFIED BY THE OPERATOR

LH Wing:

ITEM NEW PART No. KEYWORD ITEM OLD PART No. INT

22 A57358015202 Landing A57242795200 03

23 A57358015204 Landing A57242795200 03

24 A57358015206 Landing A57242795200 03

RH Wing:

ITEM NEW PART No. KEYWORD ITEM OLD PART No. INT

25 A57358015203 Landing A57242795201 03

26 A57358015205 Landing A57242795201 03

27 A57358015207 Landing A57242795201 03

F. TOOLING - PRICE AND AVAILABILITY

Fatigue Technology Inc (FTI) has allocated tool Kit A310-572081-1 for accomplishment of this

Service Bulletin. Operators who require these tools should contact:

FATIGUE TECHNOLOGY INC.

401 Andover Park East

Seattle

WA 98188-7605

USA

Tel: (206) 246-2010

Telex: 321004

Fax: (206) 244-9886

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A310

SERVICE BULLETIN

G. SPECIAL TOOLS

None

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A310

SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL

WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING : PUT THE SAFETY DEVICES AND WARNING NOTICES IN POSITION BEFORE

YOU START A TASK ON OR NEAR:

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- LANDING GEAR AND RELATED DOORS

- COMPONENTS THAT MOVE.

CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY

SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR

MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND

THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER

CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND

DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00, CLEANING.

(1) Preparation

(a) Config. 01

1 Make sure the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

block 301)

2 Put access platforms in position under the LH and RH wing in the area of the

all-speed-aileron servo control bay.

3 Open the access panels 575CB (675CB) (Refer to AMM 06-41-57, Page block 1).

(2) Standard Practices

(a) For the removal/installation of fasteners, refer to SRM 51-40-21.

(b) For the drilling/reaming of fastener holes, refer to SRM 51-40-44.

(c) For cold expanding fastener holes, refer to SRM 51-40-41.

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 13

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A310

SERVICE BULLETIN

(d) For the countersinking of fastener holes, refer to SRM 51-40-47.

(e) For fastener spacing and margin data, refer to SRM 51-40-50.

(f) For the cutting of the landing plates, refer to SRM 51-27-00.

(g) For the wet assembly of components, refer to SRM 51-76-10.

(h) For the torque value of the fasteners, refer to Figure 1, Sheet 2.

(i) For the application of protective coating, Alodine 13-002 and primer 16-006, refer to

SRM 51-75-10.

(j) For the application of paint coatings, refer to SRM 51-23-10.

(k) For the re-identification of items, refer to PMS 01-06-12.

(l) Clean the modification areas with cleaning agent (Mat. No. 11-026).

B. MODIFICATION

(1) Config. 01

(a) Preparation of the Landing plate, Wing Skin and Reinforcing Plate

Kit 572081B01R01 (LH wing) and Kit 572081B02R01 (RH wing)

Refer to Figure 1, Sheet 1, Sheet 2

The worksteps that follow are applicable to the LH and RH wing.

1 At the access panel area (575CB/675CB), do a HFEC inspection around the

landing-plate fasteners and along the full length of the landing-plate between the

fasteners, LH and RH wing. Inspect the inside and outside surfaces except for

the four hole positions at the aileron hinge ribs where it is only possible to inspect

the outside surface. (Refer to Figure 1, Sheet 1 and NTM 51-10-08, Part 6).

2 If cracks are found on the landing-plate after workstep (a), a new landing-plate

A5724279520001 (LH) or A5724279520101 (RH) will be necessary.

NOTE : Use the old landing-plate as a template to transfer drill the fastener

holes to the new landing-plate. Transfer the camlok receptacles

from the old landing-plate to the new landing-plate. Use the

old landing-plate as a template for the position of the camlok

receptacles on the new landing-plate.

3 At the access panel area (575CB/675CB), remove and discard the landing-plate

fasteners. Remove and retain the landing-plate if no cracks were found at

workstep (a).

CAUTION : GREAT CARE MUST BE TAKEN NOT TO DAMAGE THE WING

SKIN WHEN YOU CUT THE LANDING-PLATE IN ITS INSTALLED

POSITION.

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 14

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A310

SERVICE BULLETIN

NOTE : If it is difficult to remove the landing-plate in one piece, you can cut

the plate in its installed position, at the applicable areas (Refer to

Figure 1), and then remove the plate.

4 Do a HFEC inspection of the landing plate fastener holes (Refer to NTM

51-10-01 Part 6, Procedure A and Figure 1, Sheet 1):

- if only the fastener hole shown in Detail A is found cracked, do a repair in

accordance with Service Bulletin A310-57-2082,

- if cracks are found in other areas of the landing plate fasteners, contact

AIRBUS, SEE-82, for instructions,

- if cracks are not found, continue with the modification, as follows:

5 Remove and discard the fasteners in the area where the reinforcing plate

will be installed.

6 Put the landing plate in its installation position on the wing skin and temporarily

slave bolt in position.

7 Put the reinforcing plate, Item 20 or Item 21, temporarily in position and transfer

drill the ten pilot holes into the wing skin.

8 Attach the reinforcing plate, Item 20 or Item 21, with slave bolts.

9 Drill/ream the existing and new fastener holes of the skin, landing and reinforcing

plate to the start hole diameter. Cold expand the holes and ream to the final hole

diameter, Refer to Figure 1, Sheet 1, Sheet 2 and the FTI tool Kit A310-572081-1.

NOTE : The skin plug, Item 28, installation hole is to be cold expanded

through the landing plate and skin only (Refer to Figure 1, Sheet

1, Detail A).

NOTE : Alternate the installation of the temporary slave bolts of the landing

plate and reinforcing plates to allow the reaming and cold expansion

of the fastener holes.

10 Refer to Figure 1, Sheet 1 and mark the landing plate to the dimensions shown.

11 Remove the reinforcing plate and the landing plate.

12 Countersink the fastener holes (Refer to Figure 1, Sheet 2).

13 Deburr all the holes.

14 Cut the landing plate at the two positions that you have marked.

NOTE : If necessary, reprofile the reinforcing plate, Item 20 and/or Item 21,

to prevent any overlap of adjacent fasteners (the minimum edge

clearance must be 2D). If re-profiled, make sure the plate edge

radius is 0.22in. (5.6mm).

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 15

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A310

SERVICE BULLETIN

15 Apply protective coating to the cut areas of the landing plates and, if applicable,

to the reprofiled areas of the reinforcing plate.

(b) Installation of the Landing Plates and Reinforcing Plate (LH and RH wing)

Kit 572081B01R01 and Kit 572081B02R01

Refer to Figure 1, Sheet 1, Sheet 2

1 Install the three sections of the landing plates, Items 22, 23, 24 or Items 25, 26,

27, on the wing skin.

For the landing plate, Items 22 (25), wet install with sealant (Mat. No. 09-005)

these fasteners:

4 Bolts NSA5476VHK4-6 Item 1

3 Bolts NSA5478VHK4-12 Item 3

7 Washers NSA5353D04B Item 16

7 Nuts NSA5472-4K7 Item 12

For the landing plate, Item 23 (26), wet install with sealant (Mat. No. 09-005)

these fasteners:

6 Bolts NSA5478VHK4-6 Item 1

1 Bolt NSA5478VHK5-10 Item 6

6 Nuts NSA5472-4K7 Item 12

1 Nut NSA5472-5K7 Item 13

1 Washer NSA5353D05B Item 15

6 Washers NSA5353D04B Item 16

For the landing plate, Item 24 (27), wet install with sealant (Mat. No. 09-005)

these fasteners:

1 Bolt NSA5476VHK4-6 Item 1

1 Bolt NSA5478VHK4-12 Item 3

2 Washers NSA5353D04B Item 16

2 Nuts NSA5472-4K7 Item 12

1 Bolt NSA5478VHK5-12 Item 7

1 Washer NSA5353D05B Item 15

1 Nut NSA5472-5K7 Item 13

1 Plug A57358015200 Item 28

NOTE : Make sure that the head of the skin plug, Item 28, is installed to the

dimensions given in Detail A of Figure 1, Sheet 1. Fill the void at the

tail of the plug with sealant (Mat. No. 09-002).

2 Apply protective coating to the head of the plug and the heads of the fasteners in

the landing plates.

3 Apply sealant (Mat. No. 09-005) and put these countersink washers in position

on the fastener holes at the aileron hinge ribs:

4 Washers R57040030202 Item 18

5 Washers R57040030204 Item 19

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 16

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A310

SERVICE BULLETIN

NOTE : The countersink washers, Items 18 and 19, are used to fill the

existing countersinks in the aileron hinge ribs.

4 Apply sealant (Mat. No. 09-005) to the mating surfaces of the reinforcing

plate, Item 20 or Item 21, and the skin.

5 Put this reinforcing plate in position:

1 Plate R57349236200 Item 20

or:

1 Plate R57349236201 Item 21

and wet install these fasteners with sealant (Mat. No. 09-005):

6 Bolts NSA5476VHK4-10 Item 2

6 Washers NSA5353D04B Item 16

6 Nuts NSA5472-4K7 Item 12

and:

4 Bolts NSA5476VHK5-8 Item 5

4 Washers NSA5353D05B Item 15

4 Nuts NSA5472-5K7 Item 13

and:

6 Bolts NSA5476VHK5-6 Item 4

6 Washers NSA5353D05B Item 15

6 Nuts NSA5472-5K7 Item 13

and:

2 Bolts NSA5478VHK5-14 Item 8

2 Washers NSA5353D05B Item 15

2 Nuts NSA5472-5K7 Item 13

and:

4 Bolts NSA5478VHK6-14 Item 10

4 Washers NSA5353D06B Item 17

4 Nuts NSA5472-6K7 Item 14

and:

2 Bolts NSA5478VHK5-16 Item 9

2 Washers NSA5353D05B Item 15

2 Nuts NSA5472-5K7 Item 13

and:

1 Bolt NSA5478VHK6-16 Item 11

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 17

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

1 Washer NSA5353D06B Item 17

1 Nut NSA5472-6K7 Item 14

6 Remove all swarf from inside the servo control bay area.

7 Apply a bead of sealant around the reinforcing plate, Item 20 (21).

8 Apply protective coating to the reinforcing plate fasteners.

9 Apply external paint to the repaired area (to the applicable aircraft paint scheme).

10 Reidentify the three sections of the landing plates (LH wing), as follows:

- Item 22 as A57358015202.

- Item 23 as A57358015204.

- Item 24 as A57358015206.

11 Reidentify the three sections of the landing plates (RH wing), as follows:

- Item 25 as A57358015203.

- Item 26 as A57358015205.

- Item 27 as A57358015207.

C. TEST

None

D. CLOSE UP

(1) Config. 01

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the access panels 575CB (675CB).

(c) Remove the access platforms.

(d) Put the aircraft and the systems in a normal operating condition.

E. DOCUMENTATION

Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 18

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 1, Sheet 1

Config. 01 : Reinforcing Plate Installation DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 19

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A310

SERVICE BULLETIN

Figure 1, Sheet 2

Config. 01 : Reinforcing Plate Installation

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 20

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

REPORTING SHEET

TITLE : WINGS - BOTTOM SKIN PANEL NO.2 - AILERON ACCESS DOOR - INSTALL REINFORCING

PLATE

MODIFICATION No. : 12525H5572

Please complete the appropriate item (A or B):

A - SB WILL BE embodied .................................................................. YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiement:

.............................................................................................................................................................................

.............................................................................................................................................................................

B - SB HAS BEEN embodied on aircraft: ............................................................................................................

.............................................................................................................................................................................

.............................................................................................................................................................................

Operator comments:............................................................................................................................................

.............................................................................................................................................................................

.............................................................................................................................................................................

From Airline: ........................................................................................................................................................

Name/Title: ..........................................................................................................................................................

Signature:..................... Date: .....................................................

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next

normal revision or prior to SB embodiment, please indicate required service(s):

Either : Advance data................................................................................... YES/NO

Or : Intermediate/Temporary revision ..................................................... YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational documentation

if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible

revision, this will result in

- updating of maintenance documentation to show pre and post SB data.

- updating of maintenance and operational documentation to show post SB data

after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include

them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SEDCC1 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

Or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 1 of 1

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

REPORTING QUALITY

TITLE : WINGS - BOTTOM SKIN PANEL NO.2 - AILERON ACCESS DOOR - INSTALL REINFORCING

PLATE

MODIFICATION No. : 12525H5572

Use this form to tell us what is your perception of the quality of this Service Bulletin.The reported data that you

provide us will be used to analyse areas of difficulties and to take corrective action to futher improve the quality

of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

-Quality rating of this SB 4 3 2 1

-Quality rating of the Accomplishment Instructions 4 3 2 1

-Quality rating of the Illustrations 4 3 2 1

-Is this SB easy to understand ? Y / N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short

description of the issue.

Planning Material Instructions

X Effectivity X Kit Content X Preparation

X Reason X List of Materials X Mod/Inspection

X Manpower Operator Supplied X Test

X References X Re-identification X Close-up

X Publication X Tooling X Illustrations

Comments :

Operator : Date:

Name/Title :

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SEMB Service Bulletins Management

FAX: (+33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2081

REVISION No. : 03 - Oct 13/10 Page : 1 of 1

Printed in France © AIRBUS 2008 All rights reserved