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

MANDATORY MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 57

TITLE : WINGS - BOTTOM SKIN PANEL No.2 - AILERON ACCESS DOOR - INSPECTION FOR CRACKS

MODIFICATION No. : None

This page transmits Revision No. 03 of Service Bulletin No. A310-57-2082

ADDITIONAL WORK

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

REASON

Revision 03 of this Service Bulletin is issued to clarify the grace periods applicable to A/C in

configuration 02.

The table references quoted in the inspection paragraphs have been corrected.

CHANGES

SUMMARY :

- REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Kit prices have been revised and kit revision numbers have been changed.

- EFFECTIVITY

. Operators 18T, 19U, 52X, 83V, 98W, ACQ, AFG, BLE, DEC, G8E, HFY, I2L, K1P, KTC, KYV,

KZU, QAF and WTJ have been added. Operators 34W, A1L, ARG, BLM, MPD, MPJ, QSC,

TAP and UAE have been deleted.

- MATERIAL INFORMATION

. Kit revision numbers changed.

PLANNING INFORMATION :

- EFFECTIVITY

. 1.A. Effectivity has been updated and kit revision numbers have been changed.

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 1 of 4

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- COMPLIANCE

- Accomplishment Timescale

. 1.E.(2)(b)1 Grace periods have been added.

- APPROVAL

. 1.F. Approval sentence has been amended to the latest standard. Sentence has been added.

- PUBLICATIONS AFFECTED

. 1.K. MPD tasks have been added.

MATERIAL INFORMATION :

- MATERIAL - PRICE AND AVAILABILITY

- Material

. 2.A.(1) AIRBUS address has been amended.

- Price and Availability

. 2.A.(2) Kit prices have been updated and kit revision numbers have been changed.

- INDUSTRIAL SUPPORT

. 2.B. Sentence has been added.

- LIST OF COMPONENTS

. 2.C. Kit B01 has been revised to amend a Part No. and the kit revision number has been changed.

. 2.C. Kit B02 has been revised to amend a Part No. and the kit revision numbers have been

changed.

. 2.C. Kit B03 has been revised to amend a Part No. and the kit revision number has been changed.

. 2.C. Kit B04 has been revised to amend a Part No. and the kit revision numbers have been

changed.

ACCOMPLISHMENT INSTRUCTIONS :

- GENERAL

. 3.A. Caution has been amended to include reference to cleaning.

- Preparation

. 3.A.(1)(a) Configs 03 and 06 have been deleted.

. 3.A.(1)(b) Configs. 03 and 06 workstep has been added.

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- INSPECTION

. 3.B.(1)(b) Reference to Table 2 has been included in the workstep.

- REPAIR

. 3.C.(1)(b)1a The contents of Kits B01 and B02 have been listed.

. 3.C.(1)(c)1a The contents of Kits B03 and B04 have been listed.

- CLOSE-UP

. 3.E.(1) Configs 03 and 06 have been deleted.

. 3.E.(2) Configs. 03 and 06 workstep has been 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

- revise item quantities in Kits B01 and B02

- improve the instructions for the inspection.

The opportunity was also taken to update the aircraft effectivity.

Revision 02 was issued to inform operators that:

- this Inspection Service Bulletin has become Mandatory

- the inspection thresholds and repeat inspections have been revised

- the grace periods for the inspection thresholds and the inspection intervals have been amended

- a new Config layout has been added

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

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 3

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

REVISION SEQUENCE

ORIGINAL : Jun 11/02

REVISION No. : 01 - Aug 22/02

REVISION No. : 02 - Oct 17/08

REVISION No. : 03 - Nov 15/10

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 4

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

MANDATORY MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 57

TITLE : WINGS - BOTTOM SKIN PANEL No.2 - AILERON ACCESS DOOR - INSPECTION FOR CRACKS

MODIFICATION No. : None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

On the full scale wing fatigue test, skin cracking occurred in the bottom skin panel adjacent to the servo

control bay all-speed-aileron access panel 575CB/675CB. The crack was found at 51,500 simulated flights

and started from one of the access door landing plate attachment bolts. 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 was

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

During routine maintenance of an A310 aircraft (Post Mod. 05106H0894), 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 mandatory HFEC inspection for cracks in the area around the

fasteners of the access door landing plate (LH and RH wing).

If cracks are found, a permanent repair (Repair Instruction R57349237 or R57349243, installation of a repair

plate and new landing plates) can be embodied or a temporary repair (crack-stop drill) can be carried out.

NOTE : A temporary repair should only be done to allow operators to do a permanent repair at or before

the next inspection interval.

The inspection thresholds and repeat inspections are also included for the different repairs.

The Service Bulletin A310-57-2081 (Modification 12525H5572) has been issued to modify the access door

landing-plate and add a reinforcing plate. The embodiment of Service Bulletin A310-57-2081 (Modification

12525H5572) cancels the inspection requirements of this Service Bulletin.

This Service Bulletin supersedes the Inspection Service Bulletin A310-57-2037.

EVALUATION TABLE

COMPLIANCE Mandatory CANCELS INSPECTION SB A310-57-2037

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 1 of 3

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

SUMMARY

POTENTIAL AD Yes A/C OPERATION AFFECTED No

RELIABILITY AFFECTED No PAX COMFORT AFFECTED No

COST SAVING Yes ETOPS AFFECTED No

STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED No

KIT PRICE (USD)B01R03 3,240 KIT PRICE (USD)B02R02 3,240

KIT PRICE (USD)B03R01 3,180 KIT PRICE (USD)B04R01 3,180

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

OTHERS : None

NATURE OF THE WORK

AIRCRAFT : Yes

EQUIPMENT : No

HARD : No

SOFT : No

OBRM : No

MANPOWER

Config. 01 thru Config. 02 and Config. 04 thru Config. 05

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

SUMMARY

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

NOTE : Config. 03 and Config. 06 None

MATERIAL INFORMATION

AIRCRAFT DATA

Config. 01 thru Config. 02 and Config. 04 thru Config. 05

Kit 572082B01R03 (LH wing), Kit 572082B02R02 (RH wing)

Aluminium Repair plate, landing plate, fasteners and fastener hole plug.

Kit 572082B03R01 (LH wing), Kit 572082B04R01 (RH wing)

Steel repair plate, landing plate, fasteners, fastener hole plug and wing skin crack-stop hole plug.

Config. 03 and Config. 06

None

APPENDICES

None

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 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. : A310-57-2082

REVISION No. : 03 - Nov 15/10 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

MANDATORY MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 57

TITLE : WINGS - BOTTOM SKIN PANEL No.2 - AILERON ACCESS DOOR - INSPECTION FOR CRACKS

MODIFICATION No. : None

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

310-203 310-203C 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. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 1 of 29

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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

80V 0538 0544

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

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 2

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A310

SERVICE BULLETIN

OPERATOR MSN

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

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

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 3

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

OPERATOR MSN

SBI 0486 0520

SGX 0519 0562

SUD 0437

THY 0476 0478 0480 0502

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

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 4

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A310

SERVICE BULLETIN

None 03

None 04

None 05

None 06

572082B01 1 01

02

572082B02 1 01

02

572082B03 1 01

02

572082B04 1 01

02

NOTE : Config. 01 is valid for aircraft Pre-mod 05106H0894 (Service

Bulletin A310-57-2004) and Pre-mod 12525H5572 (Service Bulletin

A310-57-2081).

NOTE : Config. 02 is valid for aircraft Post-mod 05106H0894 (Servicve

Bulletin A310-57-2004) and Pre-mod 12525H5572 (Service Bulletin

A310-57-2081).

NOTE : Config. 03 is valid for aircraft Post-mod 12525H5572 (Service Bulletin

A310-57-2081).

NOTE : Config 04 is valid for aircraft with the Temporary Repair.

NOTE : Config. 05 is valid for aircraft Post Repair R57349237.

NOTE : Config. 06 is valid for aircraft Post Repair R57349243.

NOTE : Kit 572082B01R03 contains the components (aluminium repair plate kit)

to embody the Repair Instruction R57349243 for the LH wing.

NOTE : Kit 572082B02R02 contains the components (aluminium repair plate kit)

to embody the Repair Instruction R57349243 for the RH wing.

NOTE : Kit 572082B03R01 contains the components (steel repair plate kit) to

embody the Repair Instruction R57349237 for the LH wing.

NOTE : Kit 572082B04R01 contains the components (steel repair plate kit) to

embody the Repair Instruction R57349237 for the RH wing.

(3) Spares

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 5

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A310

SERVICE BULLETIN

None

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

On the full scale wing fatigue test, skin cracking occurred in the bottom skin panel adjacent

to the servo control bay all-speed-aileron access panel 575CB/675CB. The crack was found

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

bolts. 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 was also issued for HFEC

inspections around the bolt heads of the access panel landing to detect cracks.

During routine maintenance of an A310 aircraft (Post Mod. 05106H0894), 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.

Service Bulletin A310-57-2081 (Modification 12525H5572) has been issued to modify the

access door landing-plate and add a reinforcing plate.

(2) Objective/Action

This Service Bulletin has been issued for a HFEC inspection for cracks in the access panel

landing-plate. If cracks are found, a permanent repair (Repair Instruction R57349237 or

R57349243, installation of repair plates and new landing-plates) can be embodied or a

temporary repair (crack stop drill) can be accomplished.

The inspection thresholds and repeat inspections are also included for the different repairs.

NOTE : A temporary repair should only be done to allow operators to do a permanent

repair at or before the next inspection interval.

(3) Advantages

The accomplishment of this Inspection Service Bulletin will find early indications of cracks

and prevent costly and time consuming repairs.

The embodiment of Service Bulletin A310-57-2081 (Modification 12525H5572) cancels the

inspection requirements of this Service Bulletin.

This Service Bulletin supersedes the inspection Service Bulletin A310-57-2037.

(4) Operational/Maintenance Consequences

None

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 6

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A310

SERVICE BULLETIN

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

(1) Config. 01 thru Config. 02

(a) Remove the access panels 575CB (675CB).

(b) Do a HFEC inspection for cracks on the wing skin and the access panel

landing-plate. The inspection is to be done on the upper surface of the landing plate

and on the lower surface of the wing skin.

(c) If cracks are found repair as necessary.

(d) Replace the access panels 575CB (675CB).

(2) Config. 03

(a) No inspections are necessary for the accomplishment of this Service Bulletin.

(3) Config. 04

(a) Remove the access panels 575CB (675CB).

(b) Do a HFEC inspection for cracks on the wing skin and the access panel

landing-plate. The inspection is to be done on the upper surface of the landing plate

and on the lower surface of the wing skin. Also inspect around the crack stop hole.

(c) If cracks are found repair as necessary.

(d) Replace the access panels 575CB (675CB).

(4) Config. 05

(a) Remove the access panels 575CB (675CB).

(b) Do a HFEC inspection for cracks on the wing skin and the access panel landing-plate.

The inspection is to be done on the lower surface of the wing skin and the upper

surface of the landing plate (the areas not covered by the repair plate), around the

fasteners on the top surface of the repair plate and also the crack stop hole.

(c) If cracks are found contact AIRBUS for a suitable repair before the next flight.

(d) Replace the access panels 575CB (675CB).

(5) Config. 06

(a) No inspections are necessary for the accomplishment of this Service Bulletin.

E. COMPLIANCE

(1) Classification

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 7

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A310

SERVICE BULLETIN

Mandatory

(2) Accomplishment Timescale

NOTE : The inspections figures in the tables that follow are given in Flight Cycles (FC)

and Flight Hours (FH). The inspections must be done at whichever occurs first.

NOTE : The A310-300 Short Range (SR) missions should be used for aircraft with

an average flight time less than or equal to four hours. The A310-300 Long

Range (LR) missions should be used for aircraft with an average flight time

greater than 4 hours.

(a) Config. 01

1 The inspection thresholds and intervals are as shown in Table 1. If the

inspection thresholds have been exceeded then the first inspection must be

done at the grace periods listed in Table 1 from receipt of this Service Bulletin.

The inspection thresholds are to be taken from aircraft first flight.

TABLE 1

Aircraft Type Inspection Threshold Inspection Interval Grace Period

FC FH FC FH FC FH

A310-200 4,000 8,000 1,170 2,300 390 780

A310-300

SR

3,400 9,600 1,000 2,800 330 940

A310-300 LR 2,000 10,200 600 3,000 200 1,000

(b) Config. 02

1 The inspection thresholds and intervals are as shown in Table 2. If the inspection

thresholds have been exceeded then the first inspection must be done at the

grace periods listed in Tables 3 thru 5 from receipt of this Service Bulletin. The

inspection thresholds are to be taken from embodiment of the mod 05106H0894

(Service Bulletin A310-57-2004).

TABLE 2

Aircraft Type Inspection Threshold Inspection Interval

FC FH FC FH

A310-200 12,000 24,000 1,170 2,300

A310-300 SR 10,200 28,900 1,000 2,800

A310-300 LR 6,100 30,600 600 3,000

TABLE 3- A310-200

For Aircraft Between Grace Period

FC FH FC FH FC FH

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 8

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A310

SERVICE BULLETIN

12,000 24,000 13,000 26,000 1,000 2,000

Above 13,000 26,000 500 1,000

TABLE 4- Short Range (SR) Mission

For Aircraft Between Grace Period

FC FH FC FH FC FH

10,200 28,700 11,000 31,000 1,000 2,800

Above 11,000 31,000 500 1,400

TABLE 5- Long Range (LR) Mission

For Aircraft Between Grace Period

FC FH FC FH FC FH

6,100 30,500 6,500 32,500 600 3,000

6,501 32,501 13,100 65,500 300 1,500

Above 13,100 65,500 200 1,000

(c) Config. 03

1 The embodiment of mod 12525H5572 (Service Bulletin A310-57-2081) takes

the aircraft beyond Extended Service Goal (ESG). Therefore the inspection

requirements of this Service Bulletin do not apply.

(d) Config. 04

1 The inspections thresholds and intervals are as shown in Table 6 thru 8. Also

shown are the maximum inspection cycles permitted before a permanent repair

has to be embodied. The threshold figures are taken from the embodiment of

the repair.

TABLE 6 - A310-200

Inspection Threshold and

Repeat Interval

Maximum Inspection Cycles

for the Permanent Repair to

be Completed by

Temporary

Repair

Crack Length Crack

Stop Hole

Diameter

FC FH FC FH

Stop drill only 15mm 6.35mm

(0.25in.)

100 200 500 1,000

Stop drill only 30mm 6.35mm

(0.25in.)

40 80 200 400

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 9

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A310

SERVICE BULLETIN

Stop drill only 46mm 6.35mm

(0.25in.)

20 40 100 200

Stop drill only 64mm 6.35mm

(0.25in.)

10 20 60 120

TABLE 7 - A310-300 (SR)

Inspection Threshold and

Repeat Interval

Maximum Inspection Cycles

for the Permanent Repair to

be Completed by

Temporary

Repair

Crack Length Crack

Stop Hole

Diameter

FC FH FC FH

Stop drill only 15mm

(0.59in)

6.35mm

(0.25in.)

95 260 470 1,330

Stop drill only 30mm

(1.18in)

6.35mm

(0.25in.)

40 110 200 560

Stop drill only 46mm

(1.82in)

6.35mm

(0.25in.)

19 50 95 260

Stop drill only 64mm

(2.52in)

6.35mm

(0.25in.)

12 35 60 170

TABLE 8 - A310-300 (LR)

Inspection Threshold and

Repeat Interval

Maximum Inspection Cycles

for the Permanent Repair to

be Completed by

Temporary

Repair

Crack Length Crack

Stop Hole

Diameter

FC FH FC FH

Stop drill only 15mm

(0.59in)

6.35mm

(0.25in.)

56 280 280 1,400

Stop drill only 30mm

(1.18in)

6.35mm

(0.25in.)

24 120 120 600

Stop drill only 46mm

(1.82in)

6.35mm

(0.25in.)

11 55 55 275

Stop drill only 64mm

(2.52in)

6.35mm

(0.25in.)

7 35 35 175

(e) Config. 05

The inspection thresholds are shown in Table 9 thru 11. The threshold figures are

taken from embodiment of the repair.

TABLE 9 - A310-200

Crack Length Inspection Threshold Inspection Interval

(mm)

Crack Stop

Hole Diameter FC FH FC FH

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 10

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A310

SERVICE BULLETIN

15.0 (0.59in) 9.53mm

(0.375in.)

None* None* None* None*

30.0 (1.18in) 9.53mm

(0.375in.)

35,500 70,500 Note (01) Note (01)

46.20 (1.82in) 9.53mm

(0.375in.)

35,500 70,500 Note (01) Note (01)

64.0 (2.52in) 9.53mm

(0.375in.)

35,500 70,500 Note (01) Note (01)

NOTE(*) The repairs will take the aircraft to ESG.

NOTE(01) Contact AIRBUS SBWST for the inspection intervals.

TABLE 10- A310-300 (SR)

Crack Length Inspection Threshold Inspection Interval

(mm)

Crack Stop

Hole Diameter FC FH FC FH

15.0 (0.59in) 9.53mm

(0.375in.)

None* None* None* None*

30.0 (1.18in) 9.53mm

(0.375in.)

30,200 85,400 Note (01) Note (01)

46.20 (1.82in) 9.53mm

(0.375in.)

30,200 85,400 Note (01) Note (01)

64.0 (2.52in) 9.53mm

(0.375in.)

30,200 85,400 Note (01) Note (01)

NOTE(*) The repairs will take the aircraft to ESG.

NOTE(01) Contact AIRBUS SBWST for the inspection intervals.

TABLE 11- A310-300 (LR)

Crack Length Inspection Threshold Inspection Interval

(mm)

Crack Stop

Hole Diameter FC FH FC FH

15.0 (0.59in) 9.53mm

(0.375in.)

None* None* None* None*

30.0 (1.18in) 9.53mm

(0.375in.)

18,000 90,300 Note (01) Note (01)

46.20 (1.82in) 9.53mm

(0.375in.)

18,000 90,300 Note (01) Note (01)

64.0 (2.52in) 9.53mm

(0.375in.)

18,000 90,300 Note (01) Note (01)

NOTE(*) The repairs will take the aircraft to ESG.

NOTE(01) Contact AIRBUS SBWST for the inspection intervals.

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 11

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

(f) Config. 06

1 The embodiment of Repair R57349243 takes the aircraft beyond ESG. Therefore

the inspection requirements of this Service Bulletin do not apply.

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

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

of the Service Bulletin.

Accomplishment of this Service Bulletin has been rendered mandatory by the issue of an

Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD

must be used as the reference document for the mandatory accomplishment timescale.

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 , Config. 02 , Config. 04 and Config. 05

Manhours

Get access 1.0

Inspection 2.0

Close up 1.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

NOTE : The above manhours do not include any repair manhours. To assist operators

maintenance planning the approximate manhours required for a permanent repair

are 14.0.

H. WEIGHT AND BALANCE

Not changed

I. ELECTRICAL LOAD DATA

Not changed

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 12

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

J. REFERENCES

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

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

Non destructive Testing Manual (NTM) : 51-10-08

Structural Repair Manual (SRM) : 51-73-10

Repair Instruction : R57349243

: R57349237

Service Bulletin : A310-57-2004 A310-57-2037

A310-57-2081

K. PUBLICATIONS AFFECTED

Maintenance Planning Document (MPD) : 575130-02-1 575130-02-2 575130-03-1

575130-03-2

L. INTERCHANGEABILITY/MIXABILITY

None

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

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

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A310

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 14

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A310

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 572082B01R03

Cost : 3,240 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 572082B02R02

Cost : 3,240 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 572082B03R01

Cost : 3,180 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 572082B04R01

Cost : 3,180 US dollars

Availability : 120 calendar days from receipt of order

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 15

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

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

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

C. LIST OF COMPONENTS

Kit 572082B01R03

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

A5724279520001 1 Landing

R5734923620000 1 Plate

NSA5476VHK4-6 11 Bolt

NSA5476VHK4-10 6 Bolt

NSA5478VHK4-12 4 Bolt

NSA5476VHK5-6 6 Bolt

NSA5476VHK5-8 4 Bolt

NSA5478VHK5-10 1 Bolt

NSA5478VHK5-12 1 Bolt

NSA5478VHK5-14 2 Bolt

NSA5478VHK5-16 2 Bolt

NSA5478VHK6-14 4 Bolt

NSA5478VHK6-16 1 Bolt

NSA5472-4K7 21 Nut

NSA5472-5K7 16 Nut

NSA5472-6K7 5 Nut

NAS1252-416L 17 Washer

NAS1252-516L 12 Washer

R5704003020200 4 Washer

R5704003020400 5 Washer

NSA5353D04A 4 Washer

NSA5353D04B 8 Washer

NSA5353D05A 6 Washer

NSA5353D05B 12 Washer

NSA5353D06A 5 Washer

NSA5353D06B 10 Washer

AN960KD416L 34 Washer

AN960KD516L 24 Washer

R5734923720000 1 Plug

MS20426AD4-5 6 Rivet

NSA55186-202 3 Camlok

Kit 572082B02R02

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

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 16

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

A5724279520101 1 Landing

R5734923620100 1 Plate

NSA5476VHK4-6 11 Bolt

NSA5476VHK4-10 6 Bolt

NSA5478VHK4-12 4 Bolt

NSA5476VHK5-6 6 Bolt

NSA5476VHK5-8 4 Bolt

NSA5478VHK5-10 1 Bolt

NSA5478VHK5-12 1 Bolt

NSA5478VHK5-14 2 Bolt

NSA5478VHK5-16 2 Bolt

NSA5478VHK6-14 4 Bolt

NSA5478VHK6-16 1 Bolt

NSA5472-4K7 21 Nut

NSA5472-5K7 16 Nut

NSA5472-6K7 5 Nut

NAS1252-416L 17 Washer

NAS1252-516L 12 Washer

R5704003020200 4 Washer

R5704003020400 5 Washer

NSA5353D04A 4 Washer

NSA5353D04B 8 Washer

NSA5353D05A 6 Washer

NSA5353D05B 12 Washer

NSA5353D06A 5 Washer

NSA5353D06B 10 Washer

AN960KD416L 34 Washer

AN960KD516L 24 Washer

R5734923720000 1 Plug

MS20426AD4-5 6 Rivet

NSA55186-202 3 Camlok

NOTE : Kit 572082B01R03 (LH wing) and/or Kit 572082B02R02 (RH wing) are required if

an aluminium repair plate and new landing plates are to be installed in accordance

with the Repair Instruction R57349243.

Kit 572082B03R01

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

A5724279520001 1 Landing

R5734923620200 1 Plate

NSA5476VHK4-6 11 Bolt

NSA5476VHK4-10 6 Bolt

NSA5478VHK4-12 4 Bolt

NSA5476VHK5-6 6 Bolt

NSA5476VHK5-8 6 Bolt

NSA5478VHK5-10 1 Bolt

NSA5478VHK5-12 1 Bolt

NSA5478VHK5-14 2 Bolt

NSA5478VHK5-16 2 Bolt

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 17

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

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

NSA5478VHK6-14 4 Bolt

NSA5478VHK6-16 1 Bolt

NSA5472-4K7 21 Nut

NSA5472-5K7 18 Nut

NSA5472-6K7 5 Nut

NAS1252-416L 17 Washer

NAS1252-516L 12 Washer

R5704003020200 4 Washer

R5704003020400 5 Washer

NSA5353D04A 4 Washer

NSA5353D04B 8 Washer

NSA5353D05A 6 Washer

NSA5353D05B 12 Washer

NSA5353D06A 5 Washer

NSA5353D06B 10 Washer

AN960KD416L 34 Washer

AN960KD516L 24 Washer

MS20426AD4-5 6 Rivet

NSA55186-202 3 Camlok

R5734923720800 1 Plug

R5734923720000 1 Plug

Kit 572082B04R01

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

A5724279520101 1 Landing

R5734923620300 1 Plate

NSA5476VHK4-6 11 Bolt

NSA5476VHK4-10 6 Bolt

NSA5478VHK4-12 4 Bolt

NSA5476VHK5-6 6 Bolt

NSA5476VHK5-8 6 Bolt

NSA5478VHK5-10 1 Bolt

NSA5478VHK5-12 1 Bolt

NSA5478VHK5-14 2 Bolt

NSA5478VHK5-16 2 Bolt

NSA5478VHK6-14 4 Bolt

NSA5478VHK6-16 1 Bolt

NSA5472-4K7 21 Nut

NSA5472-5K7 18 Nut

NSA5472-6K7 5 Nut

NAS1252-416L 17 Washer

NAS1252-516L 12 Washer

R5704003020200 4 Washer

R5704003020400 5 Washer

NSA5353D04A 4 Washer

NSA5353D04B 8 Washer

NSA5353D05A 6 Washer

NSA5353D05B 12 Washer

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 18

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A310

SERVICE BULLETIN

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

NSA5353D06A 5 Washer

NSA5353D06B 10 Washer

AN960KD416L 34 Washer

AN960KD516L 24 Washer

MS20426AD4-5 6 Rivet

NSA55186-202 3 Camlok

R5734923720800 1 Plug

R5734923720000 1 Plug

NOTE : Kit 572082B03R01 (LH wing) and/or Kit 572082B04R01 (RH wing) are necessary if a

steel repair plate and new landing plates are to be installed in accordance with the

Repair Instruction R57349237.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

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

MAT No.

Cleaning agent Mat. No. 11-026 As required

(2) Components

None

E. PARTS TO BE RE-IDENTIFIED BY THE OPERATOR

None

F. TOOLING - PRICE AND AVAILABILITY

Fatigue Technology Inc (FTI) has allocated tool Kit 572082-1 for accomplishment of the Repair

Instruction R57349237 and R57349243. Operators who require these tools should quote this

Service Bulletin number and contact:

FATIGUE TECHNOLOGY INC.

401 Andover Park East

Seattle

WA 98188-7605

USA

Tel: (206) 246-2010

Email: sales@fatiguetech.com

Fax: (206) 244-9886

G. SPECIAL TOOLS

None

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

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A310

SERVICE BULLETIN

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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.

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.

IN CASE OF CONTAMINATION, REFER TO ESPM 20-55-00, CLEANING.

(1) Preparation

(a) Config. 01 thru Config. 02 and Config. 04 thru Config. 05

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 Remove the access panels 575CB (675CB) (refer to AMM 06-41-57, Page

block 1).

(b) Config. 03 and Config. 06

1 No preparation is necessary for the accomplishment of this Service Bulletin.

(2) Standard Practices

(a) Clean the inspection area with cleaning agent (Mat. No. 11-026).

B. INSPECTION

(1) Config. 01 thru Config. 02

Refer to Figure 1, Sheet 1

Refer to NTM 51-10-08

(a) At the access panel area (575CB/675CB) on the top and bottom surfaces, do

a HFEC inspection around the landing plate fasteners and along the full length of

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

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A310

SERVICE BULLETIN

the landing between the fasteners, LH and RH wing (Refer to Figure 1, Sheet 1

and NTM 51-10-08, Part 6).

NOTE : At the four fasteners at the aileron hinge ribs it is only possible to

inspect the outside surface.

(b) If cracks are found in the landing plate only, do a repair within the inspection intervals

given in Table 1 of paragraph 1.E.2(a) and Table 2 of paragraph 1.E.2(b), refer to

para 3 C REPAIR (1) (a) and (1) (b).

(c) If cracks are found in the wing skin, do a permanent repair or a temporary repair

immediately, refer to paragraph (1) (a) and paragraph (1) (c) or (1) (d).

(d) If no cracks are found, it is recommended to embody the modification 12525H5572

(Service Bulletin A310-57-2081).

(2) Config. 03

(a) No further inspections are necessary for aircraft with modification 12525H5572

(Service Bulletin A310-57-2081) embodied.

(3) Config. 04

Refer to Figure 2

Refer to NTM 51-10-08

(a) Do a HFEC inspection at the access panel area (575CB/675CB) on the top and

bottom surfaces and around the landing plate fasteners and along the full length of

the landing between the fasteners and also around the crack stop hole, LH and RH

wing. (Refer to NTM 51-10-08, Part 6).

NOTE : At the four fasteners at the aileron hinge ribs it is only possible to

inspect the outside surface.

(b) If additional cracks are found then do a repair before the next flight, Refer to

Paragraph 3.C. REPAIR. If the cracks are still only in the landing plate then refer

to paragraph (1) (a) and (1) (b). If the cracks are in the wing skin then refer to

paragraph (1) (a) and (1) (c).

(c) If no additional cracks are found then do the repeat inspections to the limits detailed

in 1.E.(2)(d), Accomplishment Timescales.

(4) Config. 05

Refer to Figure 2

Refer to NTM 51-10-08

(a) Do a HFEC inspection at the access panel landing plate (575CB/675CB) on the

top and bottom surfaces (the areas not covered by the repair plate), around the

fasteners on the outside surface of the repair plate and also the crack stop hole.

(Refer to NTM 51-10-08, Part 6).

NOTE : At the four fasteners at the aileron hinge ribs it is only possible to

inspect the outside surface.

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

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A310

SERVICE BULLETIN

(b) If cracks are found contact AIRBUS for a suitable repair before the next flight.

(c) If no additional cracks are found then do the repeat inspections as detailed in

1.E.(2)(e), Accomplishment Timescales.

(5) Config. 06

(a) No further inspections are necessary for aircraft with repair R57349243 embodied.

C. REPAIR

(1) Config. 01 thru Config. 02 and Config. 04

(a) If the maximum length of the crack is less than 64mm (2.52in) then do one of the

repairs in paragraphs (1) (b), (1) (c) or (1) (d).

If the maximum length of the crack has exceeded 64mm (2.52in), then contact

AIRBUS for a suitable repair before the next flight.

(b) Permanent Repair for Cracks in a Landing Plate Only

1 If a crack is found in the landing plate only, do the worksteps that follow in

accordance with the Repair Instruction R57349243:

a Use these parts, which are contained in Kit 572082B01R03, for the LH wing:

1 Landing A5724279520001

1 Plate R5734923620000

11 Bolt NSA5476VHK4-6

6 Bolt NSA5476VHK4-10

4 Bolt NSA5478VHK4-12

6 Bolt NSA5476VHK5-6

4 Bolt NSA5476VHK5-8

1 Bolt NSA5478VHK5-10

1 Bolt NSA5478VHK5-12

2 Bolt NSA5478VHK5-14

2 Bolt NSA5478VHK5-16

4 Bolt NSA5478VHK6-14

1 Bolt NSA5478VHK6-16

21 Nut NSA5472-4K7

16 Nut NSA5472-5K7

5 Nut NSA5472-6K7

17 Washer NAS1252-416L

12 Washer NAS1252-516L

4 Washer R5704003020200

5 Washer R5704003020400

4 Washer NSA5353D04A

8 Washer NSA5353D04B

6 Washer NSA5353D05A

12 Washer NSA5353D05B

5 Washer NSA5353D06A

10 Washer NSA5353D06B

34 Washer AN960KD416L

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 23

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A310

SERVICE BULLETIN

24 Washer AN960KD516L

1 Plug R5734923720000

6 Rivet MS20426AD4-5

3 Camlok NSA55186-202

Use these parts, which are contained in Kit 572082B02R02, for the RH wing:

1 Landing A5724279520101

1 Plate R5734923620100

11 Bolt NSA5476VHK4-6

6 Bolt NSA5476VHK4-10

4 Bolt NSA5478VHK4-12

6 Bolt NSA5476VHK5-6

4 Bolt NSA5476VHK5-8

1 Bolt NSA5478VHK5-10

1 Bolt NSA5478VHK5-12

2 Bolt NSA5478VHK5-14

2 Bolt NSA5478VHK5-16

4 Bolt NSA5478VHK6-14

1 Bolt NSA5478VHK6-16

21 Nut NSA5472-4K7

16 Nut NSA5472-5K7

5 Nut NSA5472-6K7

17 Washer NAS1252-416L

12 Washer NAS1252-516L

4 Washer R5704003020200

5 Washer R5704003020400

4 Washer NSA5353D04A

8 Washer NSA5353D04B

6 Washer NSA5353D05A

12 Washer NSA5353D05B

5 Washer NSA5353D06A

10 Washer NSA5353D06B

34 Washer AN960KD416L

24 Washer AN960KD516L

1 Plug R5734923720000

6 Rivet MS20426AD4-5

3 Camlok NSA55186-202

- remove and discard the landing plate.

- cut a new landing plate into three sections.

- install the three new sections of landing plate.

- install a fastener hole plug in a section of the new landing plate.

- install an external aluminium repair plate on the wing skin.

- reidentify the landing plates.

(c) Permanent Repair for Cracks in the Wing Skin

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

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A310

SERVICE BULLETIN

1 If a crack is found that extends into the wing skin, do the worksteps that follow in

accordance with the Repair Instruction R57349237:

a Use these parts, which are contained in Kit 572082B03R01, for the LH wing:

1 Landing A5724279520001

1 Plate R5734923620200

11 Bolt NSA5476VHK4-6

6 Bolt NSA5476VHK4-10

4 Bolt NSA5478VHK4-12

6 Bolt NSA5476VHK5-6

6 Bolt NSA5476VHK5-8

1 Bolt NSA5478VHK5-10

1 Bolt NSA5478VHK5-12

2 Bolt NSA5478VHK5-14

2 Bolt NSA5478VHK5-16

4 Bolt NSA5478VHK6-14

1 Bolt NSA5478VHK6-16

21 Nut NSA5472-4K7

18 Nut NSA5472-5K7

5 Nut NSA5472-6K7

17 Washer NAS1252-416L

12 Washer NAS1252-516L

4 Washer R5704003020200

5 Washer R5704003020400

4 Washer NSA5353D04A

8 Washer NSA5353D04B

6 Washer NSA5353D05A

12 Washer NSA5353D05B

5 Washer NSA5353D06A

10 Washer NSA5353D06B

34 Washer AN960KD416L

24 Washer AN960KD516L

6 Rivet MS20426AD4-5

3 Camlok NSA55186-202

1 Plug R5734923720800

1 Plug R5734923720000

Use these parts, which are contained in Kit 572082B04R01, for the RH wing:

1 Landing A5724279520101

1 Plate R5734923620300

11 Bolt NSA5476VHK4-6

6 Bolt NSA5476VHK4-10

4 Bolt NSA5478VHK4-12

6 Bolt NSA5476VHK5-6

6 Bolt NSA5476VHK5-8

1 Bolt NSA5478VHK5-10

1 Bolt NSA5478VHK5-12

2 Bolt NSA5478VHK5-14

2 Bolt NSA5478VHK5-16

4 Bolt NSA5478VHK6-14

1 Bolt NSA5478VHK6-16

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 25

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A310

SERVICE BULLETIN

21 Nut NSA5472-4K7

18 Nut NSA5472-5K7

5 Nut NSA5472-6K7

17 Washer NAS1252-416L

12 Washer NAS1252-516L

4 Washer R5704003020200

5 Washer R5704003020400

4 Washer NSA5353D04A

8 Washer NSA5353D04B

6 Washer NSA5353D05A

12 Washer NSA5353D05B

5 Washer NSA5353D06A

10 Washer NSA5353D06B

34 Washer AN960KD416L

24 Washer AN960KD516L

6 Rivet MS20426AD4-5

3 Camlok NSA55186-202

1 Plug R5734923720800

1 Plug R5734923720000

- remove and discard the landing plate.

- cut a new landing plate into three sections.

- install the three new sections of landing plate.

- crack-stop drill the crack in the wing skin.

- install a crack-stop hole plug.

- install a fastener hole plug in a section of the new landing plate.

- install an external steel repair plate on the wing skin.

- reidentify the landing plates.

(d) Temporary Repair for Cracks in the Wing Skin

1 If a crack is found and a temporary repair is necessary, drill a 6.35mm (0.25in.)

crack-stop hole at the end of the crack (refer to SRM 51-73-10) and apply

protective coating to the drilled hole.

(2) Config. 03

No repair is necessary.

(3) Config. 05

If cracks are found contact AIRBUS for a suitable repair before the next flight.

(4) Config. 06

No repair is necessary.

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 26

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A310

SERVICE BULLETIN

D. TEST

None

E. CLOSE UP

(1) Config. 01 thru Config. 02 and Config. 04 thru Config. 05

(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.

(2) Config. 03 and Config. 06

(a) No close up is necessary for the accomplishment of this Service Bulletin.

F. 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. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 27

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 1, Sheet 1

Config. 01 thru 02: Landing Plate- Inspection Area

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 28

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 1

Config. 04 thru 05: Landing Plate- Inspection Area

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 29

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Jun 11/02 SERVICE BULLETIN No. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 30

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

REPORTING SHEET

TITLE : WINGS - BOTTOM SKIN PANEL No.2 - AILERON ACCESS DOOR - INSPECTION FOR CRACKS

MODIFICATION No. : None

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. : A310-57-2082

REVISION No. : 03 - Nov 15/10 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 - INSPECTION FOR CRACKS

MODIFICATION No. : None

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. : A310-57-2082

REVISION No. : 03 - Nov 15/10 Page : 1 of 1

Printed in France © AIRBUS 2008 All rights reserved