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 : 28

TITLE : FUEL - GENERAL - MODIFY THE EQUIPMENT IN THE FUEL TANKS FOR ADDITIONAL

ELECTRICAL BONDING

MODIFICATION No. : 12256H5502, 13495H5721

This page transmits Revision No. 04 of Service Bulletin No. A310-28-2142

ADDITIONAL WORK

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

Additional work is required by revision 03 of this Service Bulletin for Config. 05 and 06 aircraft modified

(inspected) by any previous revision of this Service Bulletin.

For operators who have accomplished this Service Bulletin at original issue the additional work detailed

in Revision 01 will also be necessary.

The additional work required by revision 03 of this Service Bulletin (for Config. 05 and 06 aircraft

only) is as follows:

- Config 05: Do a resistance check of the inboard and outboard overwing refuel cap mounts, remove

and bond a mounting bolt if the required resistance values are not obtained.

- Config 06: Do a resistance check of the outboard overwing refuel cap mount, remove and bond a

mounting bolt if the required resistance values are not obtained.

REASON

Revision 04 is issued to add the ’A’ Kits in the Kit by Configuration paragraph that were removed at

revision 03.

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

The opportunity is taken to update the effectivity.

CHANGES

SUMMARY :

- EFFECTIVITY

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 1 of 4

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

. Effectivity has been updated.

- MANPOWER

. Introduced by revision 03 has been added.

- MATERIAL INFORMATION

. Kits have been clarified. Introduced by revision 03 has been added.

PLANNING INFORMATION :

- EFFECTIVITY

. 1.A. Effectivity has been updated. ’A’ Kits have been added to Kit by Configuration paragraph.

Kits B09, B10 and B18 have been raised in issue. Kit/Configurations have been changed from

None to ALL. Notes have been added. Notes for Config. 05 and 06 have been amended. Note for

Config. 07 has been added.

- DESCRIPTION

. 1.D.(6)(j) Introduced by revision 03 has been added.

- COMPLIANCE

- Accomplishment Timescale

. 1.E.(2)(a) Sentence has been updated.

. 1.E.(2)(c) Introduced by revision 03 has been added.

- MANPOWER

. 1.G. Introduced by revision 03 has been added. Kits B09, B10 and B18 have been raised in issue.

MATERIAL INFORMATION :

- MATERIAL - PRICE AND AVAILABILITY

- Price and Availability

. 2.A.(2) Price has been amended. Kit lead time has been amended. Kits B09, B10 and B18

have been raised in issue.

- INDUSTRIAL SUPPORT

. 2.B. Paragraph has been amended.

- LIST OF COMPONENTS

. 2.C. Kit B09 has been raised in issue. Item 91 QTY becomes 2, Item 167 has been deleted.

Items 175 and 176 have been added.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

. 2.C. Kit B10 has been raised in issue. Item 169 QTY becomes 4.

. 2.C. Kit B18 has ben raised issue.

- LIST OF MATERIALS - OPERATOR SUPPLIED

- Components

. 2.D.(2) Introduced by revision 03 has been added.

ACCOMPLISHMENT INSTRUCTIONS :

- MODIFICATION

. 3.(6)(a) Kits B09, B10 and B18 have been raised in issue.

. 3.(12)(a)4 Workstep has been added.

. 3.(12)(a)7 Workstep has been added.

. 3.(12)(b)4 Item (13) has been added.

. 3.(13) Kit B09 has been raised in issue.

. 3.(13)(a) Kit B09 has been raised in issue.

. 3.(13)(a)1 Items (91) and (167) have been deleted. Items (175) and (176) have been added.

. 3.(13)(a)4 Items 91 and 167 have been deleted. Items 175 and 176 have been added.

. 3.(14) Kit B09 has been raised in issue.

. 3.(14)(a) Kit B09 has been raised in issue.

. 3.(14)(c) Kit B09 has been raised in issue.

. 3.(15) Kit B10 has been raised in issue.

. 3.(15)(c) Config. 06 has been added.

. 3.(16)(a)4 Workstep has been added.

. 3.(28) Kit B18 has been raised in issue.

. 3.(28)(a) Kit B18 has been raised in issue.

. 3.(31) Introduced by revision 03 has been added.

- Figure 2

. Figure 2, Sheets 2 thru 4 and 7 updated.

- Figure 6

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 3

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

. Figure 6, Sheet 6 updated.

- Figure 19

. Item numbers have been updated.

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 of this Service Bulletin was issued to include improvements further to discrepancies found

during accomplishment. These included adding additional worksteps for the Canister Bracket bonding

at Slat Track Canister 11. Figure and AMM references have been amended and the opportunity was

taken to update the effectivity.

This Service Bulletin has been validated on A310 aircraft MSN 0599.

Revision No. 02 was issued to include improvements after validation.

Revision 03 was issued to include the bonding of the bolt with the overwing refuel caps.

Additional work content has been added to include the bonding of the bolt with the overwing fuel caps.

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

REVISION SEQUENCE

ORIGINAL : Aug 26/05

REVISION No. : 01 - Jul 17/06

REVISION No. : 02 - Sep 03/07

REVISION No. : 03 - Nov 18/09

REVISION No. : 04 - Nov 30/10

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 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 : 28

TITLE : FUEL - GENERAL - MODIFY THE EQUIPMENT IN THE FUEL TANKS FOR ADDITIONAL

ELECTRICAL BONDING

MODIFICATION No. : 12256H5502, 13495H5721

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

As part of the Fuel Safety Assessment program, AIRBUS has carried out investigations of the electrical

bonding in the aircraft fuel tanks.

As a result of these investigations this Service Bulletin has been issued for additional electrical bonding of the

equipment in the wings and center fuel tanks. This modification consists of installing additional bonding leads

and electrical bonding points.

The accomplishment of this Service Bulletin provides improved electrical bonding to ensure continuous

electrical bonding protection of all the equipment in the fuel tanks for the extended service goal of the aircraft.

EVALUATION TABLE

COMPLIANCE Mandatory (1) CANCELS INSPECTION SB No

POTENTIAL AD Yes A/C OPERATION AFFECTED No

RELIABILITY AFFECTED No PAX COMFORT AFFECTED No

COST SAVING No ETOPS AFFECTED No

STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED No

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 1 of 4

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

SUMMARY

EVALUATION TABLE

DEFUEL/VENTILATION Yes

KIT PRICE (USD) See SB

NOTE(1) Service Bulletin must be accomplished.

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 12256H5502, 13495H5721

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 these operators:

19U 52X 58X 82Z 83V 99Y ACQ AFG AIB AIC BAF BBC BLE CFC CSA 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

This Service Bulletin has been validated on A310 aircraft MSN 0599.

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : None

OEB : None

AOT : None

SIL : 28-072

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 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

Center Fuel Tank - Kit 282142A01R05

TOTAL MANHOURS 67.0

ELAPSED TIME (HOURS) 44.5

NOTE : The check of the presence of blue coating for one bonding point takes approximately 5 minutes.

The measure of electrical resistance of one bonding point takes approximately 15 minutes.

Center Fuel Tank - Kit 282142A02R02

TOTAL MANHOURS 43.0

ELAPSED TIME (HOURS) 28.5

NOTE : The check of the presence of blue coating for one bonding point takes approximately 5 minutes.

The measure of electrical resistance of one bonding point takes approximately 15 minutes.

Center Fuel Tank - Kit 282142A03R02 and Kit 282142A04R00

TOTAL MANHOURS 43.0

ELAPSED TIME (HOURS) 28.5

LH and RH Wing Fuel Tanks - All aircraft

TOTAL MANHOURS 240.0*

ELAPSED TIME (HOURS) 120.0*

NOTE(*) Subject to aircraft configuration. Refer to para.1.G.MANPOWER in the Service Bulletin for the

breakdown of the wings fuel tanks manhours. The manhours are given by rib bay and aircraft

configuration.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 3

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

SUMMARY

ADDITIONAL WORK (Introduced at revision 01)

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

ADDITIONAL WORK (Introduced by revision 03)

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

MATERIAL INFORMATION

AIRCRAFT DATA

For modification of the Center Fuel Tank it will be necessary to use the kits that follow: - Kit

282142A01R05 thru Kit 282142A04R00

that consist of: clamps, screws, bolts, rivets, nuts, washers and bonding leads.

NOTE : All kits are not necessary for all configs. Refer to the Effectivity by MSN and

Kit/Configuration paragraphs.

For modification of the Wings Fuel Tanks it will be necessary to use the kits that follow: - Kit

282142B01R04 thru Kit 282142B26R01

that consist of: clamps, screws, bolts, nuts, washers, bonding leads and slat track/screwjack canisters

drain plates.

NOTE : All kits are not necessary for all configs. Refer to the Effectivity by MSN and

Kit/Configuration paragraphs.

ADDITIONAL WORK (Introduced by revision 03)

The Nut PN NSA5470-4K7 will be from the operators own stock.

APPENDICES

None

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 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 : 28

TITLE : FUEL - GENERAL - MODIFY THE EQUIPMENT IN THE FUEL TANKS FOR ADDITIONAL

ELECTRICAL BONDING

MODIFICATION No. : 12256H5502, 13495H5721

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 0427-0431

0434 0436 0437 0439 0441 0444-0449 0452 0454 0456-0458 0467 0468 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

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 1 of 231

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

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

0697 0700 0702 0704 0706

(b) Effectivity by Operator

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

19U 0399

52X 0410

58X 0431

82Z 0550 0551

83V 0427

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

CFC 0425 0441 0444 0446 0482

CSA 0672 0674

DAH 0291 0293

DEC 0684 0693 0697

DGA 0418 0421 0422

F2I 0309 0487

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

OPERATOR MSN

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

0257 0260 0264 0267 0278 0281 0283 0288 0297 0303 0313 0316

0318 0326 0331 0333 0335 0339 0342 0343 0345 0346 0349

0353 0355 0356 0359 0360 0362 0364 0369 0378 0394 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 0473 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 : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 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

WHJ 0494

WHT 0448 0573

(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 0379 0386 0389-0390

0394 0397 0400

KIT No. QTY PER A/C CONFIGURATION

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 4

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

None 05

None 06

282142A01R05 1 ALL

282142A03R02 1 See

Note

(02)

282142B01R04 2 ALL

282142B02R02 8 01

282142B02R02 6 ALL

282142B03R03 2 ALL

282142B04R02 2 ALL

282142B05R05 2 ALL

282142B06R02 2 ALL

282142B07R03 2 ALL

282142B08R03 1 ALL

282142B09R04 2 ALL

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 5

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION

282142B10R03 2 ALL

282142B11R03 2 ALL

282142B12R05 2 ALL

282142B13R03 2 ALL

282142B14R04 2 ALL

282142B15R03 2 ALL

282142B16R03 2 ALL

282142B17R03 2 ALL

282142B18R04 2 ALL

282142B19R02 2 ALL

282142B20R03 2 ALL

282142B21R04 2 ALL

282142B22R03 2 ALL

282142B23R02 2 02

282142B24R01 2 03

282142B25R02 2 04

282142B26R01 8 01

282142B26R01 6 ALL

282142B29R00 2 ALL

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

0378 0392 0399 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 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 : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 6

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A310

SERVICE BULLETIN

None 07

282142A01R05 1 ALL

282142A02R02 1 See

Note

(01)

282142A03R02 1 See

Note

(02)

282142A04R00 1 See

Note

(03)

282142B01R04 2 ALL

282142B02R02 8 01

282142B02R02 6 ALL

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 7

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION

282142B03R03 2 ALL

282142B04R02 2 ALL

282142B05R05 2 ALL

282142B06R02 2 ALL

282142B07R03 2 ALL

282142B08R03 1 ALL

282142B09R04 2 ALL

282142B10R03 2 ALL

282142B11R03 2 ALL

282142B12R05 2 ALL

282142B13R03 2 ALL

282142B14R04 2 ALL

282142B15R03 2 ALL

282142B16R03 2 ALL

282142B17R03 2 ALL

282142B18R04 2 ALL

282142B19R02 2 ALL

282142B20R03 2 ALL

282142B21R04 2 ALL

282142B22R03 2 ALL

282142B23R02 2 02

282142B24R01 2 03

282142B25R02 2 04

282142B26R01 8 01

282142B26R01 6 ALL

282142B29R00 2 ALL

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 8

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

NOTE(01) Kit 282142A02R02 is valid for aircraft on which Mod. No. 4801H5078

(FUEL - INSTALL TRIM TANK SYSTEM) is embodied.

NOTE(02) Kit 282142A03R02 is valid for aircraft on which Mod. No. 8691S20031

(FUEL - SECTION 31 - INTRODUCE MOULDED PARTS ON A310)

is not embodied.

NOTE(03) Kit 282142A04R00 is valid for aircraft on which Mod. No. 8691S20031

(FUEL - SECTION 31 - INTRODUCE MOULDED PARTS ON A310)

is embodied.

NOTE : For aircraft that are Config. 01, the total quantity of kits for Kit

282142B02R02 and Kit 282142B26R01 is 14.

NOTE : Where configurations are listed as ALL, then these kits are necessary

for all aircraft.

NOTE : For Config. 05 thru Config. 07 no kits are required.

NOTE : Config. 01 is applicable to all aircraft that have not embodied Mod.

11056 (SB A310-57-2069).

NOTE : Config. 02 is applicable to all aircraft that have not embodied Mod.

06644 (SB A310-28-2024).

NOTE : Config. 03 is applicable to all aircraft that have embodied Mod. 05436.

NOTE : Config. 04 is applicable to all aircraft that have embodied Mod. 08681

(SB A310-28-2049).

NOTE : Config. 05 is applicable to all aircraft that have not embodied Mod.

05891 (SB A310-57-2020).

If SB A310-57-2020 has been accomplished operators should consider

their aircraft as Config. 06 .

NOTE : Config. 06 is applicable to all aircraft that have embodied Mod. 05891

(SB A310-57-2020).

NOTE : Config. 07 is applicable to all aircraft that have embodied production

Mods. 05980 or 05981 require no additional work.

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 9

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

As part of the Fuel Safety Assessment program, AIRBUS has carried out investigations of

the electrical bonding in the aircraft fuel tanks.

(2) Objective/Action

As a result of these investigations this Service Bulletin has been issued for additional

electrical bonding of the equipment in the wings and center fuel tanks. This modification

consists of installing additional bonding leads and electrical bonding positions.

(3) Advantages

The accomplishment of this Service Bulletin provides improved electrical bonding to ensure

continuous electrical bonding protection of all the equipment in the fuel tanks for the

extended service goal of the aircraft.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to:

(1) Kit 282142A01R05, Kit 282142A02R02, Kit 282142A03R02 and Kit 282142A04R00

(a) Defuel and vent the center fuel tank.

(b) Get access.

(c) Check the bonding points in the center fuel tank.

(2) Kit 282142A01R05

(a) Modify or install the bonding points.

(b) Do electrical bonding resistant tests of the additional bonding leads and electrical

bonding points.

(3) Kit 282142A02R02

(a) Modify or install the bonding points.

(b) Do electrical bonding resistant tests of the additional bonding leads and electrical

bonding points.

(4) Kit 282142A03R02

(a) Modify or install the bonding points.

(b) Do electrical bonding resistant tests of the additional bonding leads and electrical

bonding points.

(5) Kit 282142A04R00

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 10

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

(a) Modify or install the bonding points.

(6) LH and RH Wing Fuel Tanks - Kit 282142B01R04 thru Kit 282142B26R01

(a) Defuel and vent the LH and RH wings fuel tanks.

(b) Fully extend the slats.

(c) Get access to the bonding areas in the rib bays 1-2 thru rib bay 29-30.

(d) Install additional bonding leads and/or electrical bonding positions.

(e) Do electrical bonding resistant tests of the additional electrical bonding positions.

(f) Re-fuel the wings fuel tanks.

(g) Check the wings fuel tanks for leaks.

(h) Close-up.

(i) ADDITIONAL WORK (Introduced at revision 01)

NOTE : If this Service Bulletin has been accomplished before revision 01, it is

necessary to do the additional work. Aircraft modified per revision 01

or later revisions are not affected by the additional work described

in this paragraph.

1 Defuel and vent the outer wings fuel tanks.

2 Get access to the bonding area in the rib bay 29-30.

3 Electrically bond the Slat Track 11 canister bracket.

4 Do electrical bonding resistance tests of the bonding positions.

5 Re-fuel the wings fuel tanks.

6 Check the wings fuel tanks for leaks.

7 Close-up.

(j) ADDITIONAL WORK (Introduced by revision 03)

NOTE : If this Service Bulletin has been accomplished by any previous revision it

is necessary to do the additional work described in this paragraph.

1 Do electrical bonding resistance tests of the overwing refuelling cap adaptor.

2 If the required resistance values are not achieved defuel and vent the outer

and inner wings fuel tanks.

3 Get access to the overwing refuelling caps between rib bays 13 to 14 and

27 to 28.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 11

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

4 Get access to the wing tank at rib bays 13 to 14 and 27 to 28, remove and

bond a refuelling cap adaptor bolt.

5 Close the access and refuel the wings.

6 Check the wing tanks for leaks.

7 Close up.

E. COMPLIANCE

(1) Classification

Mandatory

(2) Accomplishment Timescale

(a) 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.

(b) ADDITIONAL WORK (introduced at revision 01):

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.

(c) ADDITIONAL WORK (Introduced by revision 03):

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.

F. APPROVAL

Approved under EASA Design Organization 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.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labour 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.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 12

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Kit 282142A01R05

Get access 3.0

Check of the bonding points 40.0

Modif/install the bonding points 20.0

Test 1.0

Close-up 3.0

TOTAL MANHOURS 67.0

ELAPSED TIME (HOURS) 44.5

NOTE : The check of the presence of blue coating for one bonding point takes approximately

5 minutes.

The measure of electrical resistance of one bonding point takes approximately 15

minutes.

Kit 282142A02R02

Check of the bonding points 40.0

Modif/install the bonding points 3.0

Test 1.0

TOTAL MANHOURS 44.0

ELAPSED TIME (HOURS) 28.5

NOTE : The check of the presence of blue coating for one bonding point takes approximately

5 minutes.

The measure of electrical resistance of one bonding point takes approximately 15

minutes.

Kit 282142A03R02 and Kit 282142A04R00

Check of the bonding points 40.0

Modif/install the bonding points 2.0

Test 1.0

TOTAL MANHOURS 43.0

ELAPSED TIME (HOURS) 28.5

NOTE : The check of the presence of blue coating for one bonding point takes approximately

5 minutes.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 13

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

The measure of electrical resistance of one bonding point takes approximately 15

minutes.

Wings Fuel Tanks (LH and RH)

The hours for the following kits are for both wings.

Rib Bay 1-2, Kit 282142B01R04 - All Aircraft

Get access 1.0

Modification 20.0

Close up 1.0

TOTAL MANHOURS 22.0

ELAPSED TIME (HOURS) 11.0

Rib Bay 1-2, Kit 282142B23R02 - Config. 02 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 1-2, Kit 282142B25R02 - Config. 04 Aircraft

Modification 2.0

TOTAL MANHOURS 2.0

ELAPSED TIME (HOURS) 1.0

Rib Bay 2-3, Kit 282142B03R03 - All Aircraft

Get access 1.0

Modification 8.0

Close up 1.0

TOTAL MANHOURS 10.0

ELAPSED TIME (HOURS) 5.0

Rib Bay 2-3, Kit 282142B24R01 - Config. 03 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 14

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

ELAPSED TIME (HOURS) 2.0

Rib Bay 4-5, Kit 282142B04R02 - All Aircraft

Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 4-5, Kit 282142B02R02 and Kit 282142B26R01 - Config. 01 - Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 6-7, Kit 282142B05R05 - All Aircraft

Get access 1.0

Modification 8.0

Close up 1.0

TOTAL MANHOURS 10.0

ELAPSED TIME (HOURS) 5.0

Rib Bay 6-7, Kit 282142B02R02 and Kit 282142B26R01 - Config. 01 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 9-10, Kit 282142B06R02 - All Aircraft

Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 15

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Rib Bay 9-10, Kit 282142B02R02 and Kit 282142B26R01 - Config. 01 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 10-11, Kit 282142B07R03 - All Aircraft

Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 10-11, Kit 282142B02R02 and Kit 282142B26R01 - Config. 01 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 10-11, Kit 282142B23R02 - Config. 02 Aircraft

Modification 3.0

TOTAL MANHOURS 3.0

ELAPSED TIME (HOURS) 1.5

Rib Bay 11-12, Kit 282142B09R04 - All Aircraft

Get access 1.0

Modification 1.0

Close up 1.0

TOTAL MANHOURS 3.0

ELAPSED TIME (HOURS) 1.5

Rib Bay 11-12, Kit 282142B08R03 - All Aircraft (RH)

Modification 2.0

TOTAL MANHOURS 2.0

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 16

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

ELAPSED TIME (HOURS) 2.0

Rib Bay 12-13, Kit 282142B09R04 - All Aircraft

Get access 1.0

Modification 5.0

Close up 1.0

TOTAL MANHOURS 7.0

ELAPSED TIME (HOURS) 3.5

Rib Bay 12-13, Kit 282142B02R02 and Kit 282142B26R01 - Config. 01 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 13-14, Kit 282142B10R03 - All Aircraft

Get access 1.0

Modification 6.0

Close up 1.0

TOTAL MANHOURS 8.0

ELAPSED TIME (HOURS) 4.0

Rib Bay 14-15, Kit 282142B11R03 - All Aircraft

Get access 1.0

Modification 16.0

Close up 1.0

TOTAL MANHOURS 18.0

ELAPSED TIME (HOURS) 9.0

Rib Bay 14-15, Kit 282142B02R02 and Kit 282142B26R01 - Config. 01 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 17

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

ELAPSED TIME (HOURS) 2.0

Rib Bay 15-16, Kit 282142B12R03 - All Aircraft

Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 16-17, Kit 282142B13R03 - All Aircraft

Get access 1.0

Modification 5.0

Close up 1.0

TOTAL MANHOURS 7.0

ELAPSED TIME (HOURS) 3.5

Rib Bay 16-17, Kit 282142B02R02 and Kit 282142B26R01 - Config. 01 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 17-18, Kit 282142B14R04 - All Aircraft

Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 17-18, Kit 282142B02R02 and Kit 282142B26R01 - All Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 18

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Rib Bay 20-21, Kit 282142B15R03 - All Aircraft

Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 20-21, Kit 282142B02R02 and Kit 282142B26R01 - Config. 01 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 21-22, Kit 282142B16R03 - All Aircraft

Get access 1.0

Modification 5.0

Close up 1.0

TOTAL MANHOURS 7.0

ELAPSED TIME (HOURS) 3.5

Rib Bay 21-22, Kit 282142B02R02 and Kit 282142B26R01 All Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 23-24, Kit 282142B17R03 - All Aircraft

Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 23-24, Kit 282142B02R02 and Kit 282142B26R01 All Aircraft

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 19

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 24-25, Kit 282142B19R02 - All Aircraft

Get access 1.0

Modification 1.0

Close up 1.0

TOTAL MANHOURS 3.0

ELAPSED TIME (HOURS) 1.5

Rib Bay 25-26, Kit 282142B19R02 - All Aircraft

Get access 1.0

Modification 2.0

Close up 1.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 26-27, Kit 282142B20R03 - All Aircraft

Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 26-27, Kit 282142B02R02 and Kit 282142B26R01 All Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 27-28, Kit 282142B21R04 - All Aircraft

Get access 1.0

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 20

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Modification 6.0

Close up 1.0

TOTAL MANHOURS 8.0

ELAPSED TIME (HOURS) 4.0

Rib Bay 27-28, Kit 282142B02R02 and Kit 282142B26R01 All Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 28-29, Kit 282142B22R03 - All Aircraft

Get access 1.0

Modification 6.0

Close up 1.0

TOTAL MANHOURS 8.0

ELAPSED TIME (HOURS) 4.0

Rib Bay 29-30, Kit 282142B18R04 - All Aircraft

Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 29-30, Kit 282142B02R02 and Kit 282142B26R01 All Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

NOTE : The overall manhours for the wings fuel tanks can vary between 191 total manhours,

elapsed time 95.5 manhours and 240 total manhours, elapsed time 120 manhours,

depending on the aircraft configuration.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 21

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

NOTE : Operators should allow approximately 2 hours for a leak test of the wings fuel tanks

after the completion of the modification.

ADDITIONAL WORK (Introduced at revision 01)

Rib Bay 29-30, Kit 282142B29R00

Get access 1.0

Modification 2.0

Close up 1.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

NOTE : The manhours for defueling and venting the wing fuel tanks is not included.

ADDITIONAL WORK (Introduced by revision 03)

Rib bays 13-14 and 27-28

Do a check of the bonding value 0.5

If values not achieved get access 1.0

Modification 2.0

Close up 1.0

TOTAL MANHOURS 4.5

ELAPSED TIME (HOURS) 2.5

NOTE : The manhours for defueling and venting the wing fuel tanks is not included.

H. WEIGHT AND BALANCE

Not changed

I. ELECTRICAL LOAD DATA

Not changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) : 06-41-57 20-28-11 24-00-00 24-41-00

27-80-00 28-00-00 28-10-00 28-11-00

28-11-22 28-11-28 28-11-29 28-25-00

57-23-11

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 22

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Structural Repair Manual (SRM) : 51-40-21 51-47-00 51-40-30 51-40-40

51-43-00 51-75-10 51-76-20

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

Service Bulletin A310-28-2024 A310-28-2049 A310-57-2053 A310-28-2069

K. PUBLICATIONS AFFECTED

Aircraft Maintenance Manual (AMM) : 28-11-21 28-12-15 28-12-16 28-21-13

28-21-21 28-21-52 28-25-15 28-25-18

28-42-45 28-43-21 28-46-21 28-46-22

28-46-28 57-23-11

Illustrated Parts Catalogue (IPC) : 28-11-05 28-11-21 28-21-03 28-21-05

28-25-03 28-25-05 28-25-18 28-26-03

57-20-43

L. INTERCHANGEABILITY/MIXABILITY

None

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 23

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 24

Printed in France © AIRBUS 2008 All rights reserved
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

Material Logistics and Suppliers

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 282142A01R05

Cost : 426.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142A02R02

Cost : 44.00 US dollars

Availability : 30 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142A03R02

Cost : 26.00 US dollars

Availability : 30 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142A04R00

Cost : 28.00 US dollars

Availability : 30 calendar days from receipt of order

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 25

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

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

at the issue date of the Service Bulletin.

NOTE : Kit 282142B01R04 thru Kit 282142B26R01

are for the LH wing. Duplicate Kits will be required for the RH wing.

Kit 282142B01R04

Cost : 470.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B02R02

Cost : 34.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B03R03

Cost : 238.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B04R02

Cost : 164.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B05R05

Cost : 171.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B06R02

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 26

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Cost : 132.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B07R03

Cost : 287.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B08R03

Cost : 45.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B09R04

Cost : 570.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B10R03

Cost : 37.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B11R03

Cost : 407.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B12R05

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 27

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Cost : 216.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B13R03

Cost : 90.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B14R04

Cost : 130.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B15R03

Cost : 182.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B16R03

Cost : 267.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B17R03

Cost : 319.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B18R04

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 28

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Cost : 115.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B19R02

Cost : 122.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B20R03

Cost : 130.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B21R04

Cost : 332.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B22R03

Cost : 183.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B23R02

Cost : 75.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B24R01

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 29

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Cost : 164.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B25R02

Cost : 15.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B26R01

Cost : 38.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 282142B29R00

Cost : 120.00 US dollars

Availability : 60 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

The Kits availability given above is the standard lead time from the date of your purchase

order. If you require the Kits before this time, please include a 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 282142A01R05

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

1 NAS6603-2 10 Bolt

2 NAS1303-2 2 Bolt

3 NAS1149F0332P 14 Washer

4 NAS1726-4E 4 Nut

5 NSA5050-3 24 Nut

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 30

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A310

SERVICE BULLETIN

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

6 NSA5519-4B 2 Clamp

9 NAS6604-3 4 Bolt

10 A9242127720000 2 Angle

11 ASNA2050DCJ3215 4 Rivet

15 E0088-10-80 12 Lead

16 E0088-10-160 2 Lead

17 NSA5519-4 2 Clamp

18 NAS6603-1 6 Bolt

19 E0088-10-100 2 Lead

20 NSA5519-11 10 Clamp

21 NAS6603-3 4 Bolt

23 E0088-41-125 4 Lead

24 NAS1801-3-10 8 Screw

25 NAS1801-3-11 2 Screw

26 NSA5519-2B 6 Clamp

Kit 282142A02R02

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

4 NAS1726-4E 2 Nut

5 NSA5050-3 3 Nut

13 AN735D40 3 Clamp

14 NAS1801-3-8 3 Screw

23 E0088-41-125 1 Lead

27 E0088-41-160 2 Lead

Kit 282142A03R02

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

2 NAS1303-2 1 Bolt

5 NSA5050-3 1 Nut

22 E0088-10-250 1 Lead

26 NSA5519-2B 1 Clamp

Kit 282142A04R00

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

2 NAS1303-2 1 Bolt

5 NSA5050-3 1 Nut

12 NSA5355-4CA 1 Washer

22 E0088-10-250 1 Lead

26 NSA5519-2B 1 Clamp

Kit 282142B01R04

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

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 31

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A310

SERVICE BULLETIN

23 E0088-41-125 2 Lead

46 NSA5041VBV4-7 1 Bolt

74 E0088-41-160 1 Lead

75 AN742D6 1 Clamp

76 NAS1133-1 1 Screw

91 NSA5474-4K7 5 Nut

93 NSA5474-3K7 11 Nut

94 AN960KD10L 1 Washer

95 NSA5041VBV3-4 1 Bolt

98 NSA5041VBV3-9 1 Bolt

99 NSA5041VBV3-12 1 Bolt

101 NSA5041VBV3-13 2 Bolt

102 E0088-10-160 2 Lead

103 AN742D4 4 Clamp

104 NAS1133-2 4 Bolt

125 NAS1154-21 4 Screw

154 NSA5041VBV3-3 1 Bolt

160 NSA5472-5K7 1 Nut

170 AN742D3 2 Clamp

Kit 282142B02R02

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

7 A5715206420000 1 Plate LH

11 NSA5472-4K7 4 Nut

12 AN960-416 1 Washer

Kit 282142B03R03

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

3 NSA5041VBV3-5 2 Bolt

4 NSA5041VBV3-2 2 Bolt

5 AN960C10L 2 Washer

93 NSA5474-3K7 6 Nut

115 NAS1304-3 1 Bolt

116 AN960KD416L 1 Washer

154 NSA5041VBV3-3 2 Bolt

160 NSA5472-5K7 2 Nut

Kit 282142B04R02

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

24 NSA5041VBV3-6 1 Bolt

93 NSA5474-3K7 2 Nut

95 NSA5041VBV3-4 1 Bolt

Kit 282142B05R05

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 32

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A310

SERVICE BULLETIN

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

5 AN960C10L 1 Washer

91 NSA5474-4K7 3 Nut

93 NSA5474-3K7 2 Nut

95 NSA5041VBV3-4 1 Bolt

154 NSA5041VBV3-3 1 Bolt

160 NSA5472-5K7 4 Nut

173 NSA8203-226 1 O-ring

Kit 282142B06R02

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

4 NSA5041VBV3-2 3 Bolt

5 AN960C10L 1 Washer

11 NSA5472-4K7 1 Nut

93 NSA5474-3K7 3 Nut

Kit 282142B07R03

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

4 NSA5041VBV3-2 3 Bolt

11 NSA5472-4K7 1 Nut

40 E0088-40-100 1 Lead

41 ABS0114-4-10 1 Bolt

42 NSA5475-4K7 2 Nut

47 NSA5041VBV4-8 1 Bolt

93 NSA5474-3K7 3 Nut

Kit 282142B08R03

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

74 E0088-41-160 1 Lead

91 NSA5474-4K7 1 Nut

93 NSA5474-3K7 1 Nut

114 E0088-10-125 1 Lead

118 NAS1303-6 1 Bolt

120 NAS1304-11 1 Bolt

122 AN742D8 2 Clamp

123 NAS1100-3-7 3 Screw

124 NSA5472-3K7 3 Nut

130 NAS1304-9 1 Bolt

Kit 282142B09R04

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

3 NSA5041VBV3-5 1 Bolt

24 NSA5041VBV3-6 1 Bolt

41 ABS0114-4-10 1 Bolt

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 33

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A310

SERVICE BULLETIN

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

42 NSA5475-4K7 1 Nut

91 NSA5474-4K7 2 Nut

93 NSA5474-3K7 3 Nut

95 NSA5041VBV3-4 1 Bolt

153 NAS1303-3 1 Bolt

161 NSA5041VBV4-10 1 Bolt

162 E0088-40-200 1 Lead

165 NSA8203-234 4 O-ring

175 NAS1096-1-4 8 Bolt

176 NAS1291C06M 8 Nut

Kit 282142B10R03

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

91 NSA5474-4K7 2 Nut

168 NAS1304-10 1 Bolt

169 NSA5470-4K7 4 Nut

Kit 282142B11R03

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

4 NSA5041VBV3-2 1 Bolt

11 NSA5472-4K7 1 Nut

19 NAS1303-2 1 Bolt

24 NSA5041VBV3-6 1 Bolt

41 ABS0114-4-10 1 Bolt

42 NSA5475-4K7 2 Nut

74 E0088-41-160 1 Lead

75 AN742D6 1 Clamp

76 NAS1133-1 1 Screw

91 NSA5474-4K7 1 Nut

93 NSA5474-3K7 9 Nut

103 AN742D4 4 Clamp

110 NAS1100-3-6 2 Screw

114 E0088-10-125 1 Lead

123 NAS1100-3-7 2 Screw

124 NSA5472-3K7 1 Nut

131 E0088-10-100 3 Lead

144 NSA5041VBV3-7 2 Bolt

161 NSA5041VBV4-10 1 Bolt

162 E0088-40-200 1 Lead

166 NAS1154-10 4 Screw

Kit 282142B12R05

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

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 34

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

3 NSA5041VBV3-5 2 Bolt

11 NSA5472-4K7 2 Nut

19 NAS1303-2 1 Bolt

74 E0088-41-160 1 Lead

75 AN742D6 1 Clamp

76 NAS1133-1 1 Screw

91 NSA5474-4K7 1 Nut

93 NSA5474-3K7 6 Nut

154 NSA5041VBV3-3 2 Bolt

160 NSA5472-5K7 2 Nut

Kit 282142B13R03

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

4 NSA5041VBV3-2 1 Bolt

11 NSA5472-4K7 1 Nut

40 E0088-40-100 1 Lead

42 NSA5475-4K7 2 Nut

48 ABSO114-4-11 1 Bolt

93 NSA5474-3K7 1 Nut

124 NSA5472-3K7 1 Nut

153 NAS1303-3 1 Bolt

161 NSA5041VBV4-10 1 Bolt

Kit 282142B14R04

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

4 NSA5041VBV3-2 2 Bolt

11 NSA5472-4K7 1 Nut

42 NSA5475-4K7 2 Nut

93 NSA5474-3K7 2 Nut

161 NSA5041VBV4-10 1 Bolt

163 ABS0114-4-11 1 Bolt

164 E0088-40-125 1 Lead

Kit 282142B15R03

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

3 NSA5041VBV3-5 1 Bolt

34 ABS0114-4-9 1 Bolt

40 E0088-40-100 1 Lead

42 NSA5475-4K7 2 Nut

93 NSA5474-3K7 2 Nut

95 NSA5041VBV3-4 1 Bolt

161 NSA5041VBV4-10 1 Bolt

Kit 282142B16R03

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 35

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

3 NSA5041VBV3-5 1 Bolt

4 NSA5041VBV3-2 1 Bolt

34 ABS0114-4-9 1 Bolt

35 ABS0114-3-4 1 Bolt

40 E0088-40-100 1 Lead

42 NSA5475-4K7 2 Nut

47 NSA5041VBV4-8 1 Bolt

91 NSA5474-4K7 1 Nut

93 NSA5474-3K7 4 Nut

154 NSA5041VBV3-3 2 Bolt

Kit 282142B17R03

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

3 NSA5041VBV3-5 1 Bolt

37 ABS0114-3-2 2 Bolt

40 E0088-40-100 1 Lead

42 NSA5475-4K7 2 Nut

45 ABS0114-4-8 1 Bolt

93 NSA5474-3K7 3 Nut

95 NSA5041VBV3-4 1 Bolt

124 NSA5472-3K7 1 Nut

161 NSA5041VBV4-10 1 Bolt

Kit 282142B18R04

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

3 NSA5041VBV3-5 1 Bolt

29 ABS0114-3-3 1 Bolt

31 ABS0114-4-4 1 Bolt

42 NSA5475-4K7 1 Nut

93 NSA5474-3K7 1 Nut

163 E0088-40-250 1 Lead

Kit 282142B19R02

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

4 NSA5041VBV3-2 1 Bolt

91 NSA5474-4K7 1 Nut

93 NSA5474-3K7 2 Nut

154 NSA5041VBV3-3 1 Bolt

Kit 282142B20R03

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

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 36

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

4 NSA5041VBV3-2 1 Bolt

40 E0088-40-100 1 Lead

42 NSA5475-4K7 2 Nut

46 NSA5041VBV4-7 1 Bolt

49 ABS0114-4-7 1 Bolt

93 NSA5474-3K7 2 Nut

95 NSA5041VBV3-4 1 Bolt

Kit 282142B21R04

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

4 NSA5041VBV3-2 2 Bolt

36 AN960-10L 1 Washer

37 ABS0114-3-2 1 Bolt

40 E0088-40-100 1 Lead

42 NSA5475-4K7 2 Nut

43 NSA5041VBV4-5 1 Bolt

50 ABS0114-4-5 1 Bolt

91 NSA5474-4K7 1 Nut

93 NSA5474-3K7 7 Nut

124 NSA5472-3K7 1 Nut

153 NAS1303-3 1 Bolt

154 NSA5041VBV3-3 1 Bolt

169 NSA5470-4K7 1 Nut

Kit 282142B22R03

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

91 NSA5474-4K7 1 Nut

160 NAS6403-5 1 Bolt

162 NAS1154-12 2 Screw

169 NSA5470-4K7 2 Nut

Kit 282142B23R02

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

91 NSA5474-4K7 1 Nut

93 NSA5474-3K7 5 Nut

102 E0088-10-160 1 Lead

131 E0088-10-100 2 Lead

136 NAS1303-8 2 Bolt

138 NSA5476VBV-4-11 1 Bolt

140 MS21103D6 2 Clamp

141 NAS1096-3-6 2 Screw

144 NSA5041VBV3-7 1 Bolt

Kit 282142B24R01

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 37

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

93 NSA5474-3K7 2 Nut

154 NSA5041VBV3-3 2 Bolt

Kit 282142B25R02

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

79 NAS1303-4 2 Bolt

93 NSA5474-3K7 4 Nut

136 NAS1303-8 2 Bolt

Kit 282142B26R01

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

8 A5715206420100 1 Plate RH

11 NSA5472-4K7 4 Nut

12 AN960-416 1 Washer

Kit 282142B29R00

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

3 NSA5041VBV3-5 1 Bolt

29 ABS0114-3-3 1 Bolt

93 NSA5474-3K7 1 Nut

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware

components in the related kit(s) which you cannot identify in the LIST OF

COMPONENTS of this Service Bulletin. The SM will give you the correct part number

to part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

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

MAT No.

Pure Mineral Vaseline Mat. No. 04-012 As required

Varnish Mat. No. 07-001C As required

Varnish* Mat. No. 07-001B As required

Sealant Mat. No. 09-001 As required

Fuel Tank Sealant Polysulfide Mat. No. 09-002 As required

Low Density Fuel Tank Sealant Mat. No. 09-002D As required

Cleaning agent Mat. No. 11-026 As required

Chemical Conversion Coating Yellow

Aluminium

Mat. No. 13-002 As required

Polyurethane Primer Mat. No. 16-001C As required

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 38

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A310

SERVICE BULLETIN

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

MAT No.

NOTE(*) Alternative to varnish 07-001C. Operators are advised that the use of the

alternative material 07-001B may be banned in some countries or states.

(2) Components

Center Fuel Tank

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

EN6115T7X-18 1 Screw

EN6115T7Y-18 1 Screw

EN6115V5X-12 3 Screw

EN6115V5X-14 2 Screw

EN6115V5X-18 1 Screw

EN6115V5Y-12 3 Screw

EN6115V5Y-14 2 Screw

EN6115V5X-20 1 Screw

EN6115V5Y-20 1 Screw

EN6115V5Y-18 1 Screw

NSA5061-4 1 Washer

NSA5112-03 3 Washer

NSA5112-04 1 Washer

ASNA2529-5 5 Nut

ASNA2531-5 2 Nut

ASNA2531-7 1 Nut

NAS1726-3E 16 Nut

NAS1726-4E 18 Nut

NAS1726-5E 1 Nut

NSA5050-4 5 Nut

NSA5050-3 23 Nut

NSA5050-5 2 Nut

NSA5182-3 2 Nut

ASNA2050DCJ3215 46 Rivet

ASNA2050DEJ4020 4 Rivet

ADDITIONAL WORK (Introduced by revision 03)

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

169 NSA5470-4K7 4 Nut

NOTE : The Nut, Item 169 will be from the operators own stock.

E. PARTS TO BE RE-IDENTIFIED BY THE OPERATOR

None

F. TOOLING - PRICE AND AVAILABILITY

None

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 39

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A310

SERVICE BULLETIN

G. SPECIAL TOOLS

None

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 40

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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 : BEFORE YOU DO ANY WORK ON THE FUEL SYSTEM OBEY THE SAFETY

PRECAUTIONS (REFER TO AMM 28-00-00, Page block 301).

WARNING : DO NOT DO ANY WORK IN THE FUEL TANKS UNTIL THE VAPOR

CONCENTRATION IS BELOW 20% OF THE LOWER EXPLOSION LIMIT.

WARNING : OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE SEALANTS

AND CLEANING AGENTS IN THE FUEL TANKS.

WARNING : MAKE SURE THAT ALL THE FLIGHT CONTROLS GROUND SAFETY LOCKS

AND WARNINGS NOTICES ARE IN POSITION BEFORE YOU START THIS

MODIFICATION.

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, CLOTH, ETC; AS

NECESSARY, ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL METAL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION FROM THE MODIFICATION AREA.

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

block 301).

WARNING : MAKE SURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF THE

TRAVEL RANGES OF THE SLATS/FLAPS.

(b) Fully extend the slats/flaps (Refer to AMM 27-80-00, Page block 301).

(c) Put access platforms in position as required.

(d) Defuel the center fuel tanks and the wing fuel tanks (Refer to AMM 28-25-00, Page

block 301 and AMM 28-10-00, Page block 301).

(e) Remove additional wing manhole covers as required (Refer to AMM 28-11-22,

Page block 401).

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 41

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SERVICE BULLETIN

NOTE : The center tank manhole covers, 147AZ and 148AZ, are removed

during the ventilation process.

(f) Ventilate the center fuel tanks and the wing fuel tanks (Refer to AMM 28-25-00, Page

block 301 and AMM 28-10-00, Page block 301).

(g) Make sure that the circuit breakers of all systems that you will work on are open, in

safety and tagged and warning notices are in position.

(h) For access to the slat-track canisters and screwjack canisters (and the removal of

the applicable heat shields for access to the modification areas) (Refer to AMM

57-23-11, Page block 401).

(i) For some Track Cans/Jack Cans it may be difficult to get access to the modification

areas due to the small work area. If necessary these Track Cans/Jack Cans

can be temporarily removed to allow access for bonding preparation. For the

removal/installation of Track Cans/Jack Cans (Refer to AMM 57-23-11, Page

block 401).

(j) Refer to AMM 06-41-57 for the wings access panels/doors.

(2) Standard Practices

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

(b) For fastener hole and drill information, refer to SRM 51-40-40.

(c) For alternative and substitute fasteners, refer to SRM 51-40-30.

(d) Cut rivets to the necessary length.

(e) For the applicable torque value of fasteners, refer to SRM 51-43-00.

(f) For the specification of the material numbers (Mat. No.), refer to the CML.

(g) For general sealant repair, refer to SRM 51-76-10.

(h) For the repair of integral tank sealing, refer to SRM 51-76-20.

(i) For the repair of paint coatings, refer to SRM 51-75-10.

(j) Clean the modification areas with cleaning agent (Mat. No. 11-026), as necessary.

(k) For the installation of the new bonding leads and the new bonding items in the wings

and center fuel tanks, refer to AMM 20-28-11, Page block 001 for:

- the preparation procedures of the new bonding positions.

- the installation procedures of new bonding leads, clamps and bonding bolts.

- the electrical-bonding resistance checks of the bonding positions.

- the application of protective coating to the bonding items.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 42

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A310

SERVICE BULLETIN

B. MODIFICATION

NOTE : For the worksteps for the Center Fuel Tank refer to paragraphs (1) thru (5), Figure 1

thru Figure 17.

For the worksteps for the Wings Fuel Tanks refer to paragraphs (6) to (28), Figure 18

thru Figure 46.

Additional work is detailed in paragraph (29) (introduced at revision 01).

Additional work is detailed in paragraph (30) and (31).

(1) Kit 282142A01R05, Kit 282142A02R02, Kit 282142A03R02 and Kit 282142A04R00

(a) Check the bonding points in the center tank.

NOTE : In fuel center tank, the modification consists in :

- Checking the bonding points identified as potentially non conform, refer to

Figure 1.

For each point identified check the presence of blue coat :

- If blue coat present, no further action.

- If no blue coat then :

Measure the electrical resistance between part and the structure (Refer

to AMM 20-28-11, Page block 001).

- If the ohmic resistance <10mohm, apply the blue coat.

- If the ohmic resistance >10mohm, do the bonding.

1 Check the bonding points Items 1 thru 27 at FR47.

Refer to Figure 1, Sheet 1 (General location)

Refer to Figure 2, Sheet 1 thru 18 (Detailed location)

Refer to Figure 3, Sheet 1 (Result table)

2 Check the bonding points Items 28 thru 32 at the Rib 1 (LH side).

Refer to Figure 1, Sheet 1 (General location)

Refer to Figure 4, Sheet 1 thru 5 (Detailed location)

Refer to Figure 5, Sheet 1 (Result table)

3 Check the bonding points Items 33 thru 48 at the panel intrados.

Refer to Figure 1, Sheet 1 (General location)

Refer to Figure 6, Sheet 1 thru 11 (Detailed location)

Refer to Figure 7, Sheet 1 (Result table)

4 Check the bonding points Items 51 thru 56 at the Rib 1 (RH side).

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 43

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A310

SERVICE BULLETIN

Refer to Figure 1, Sheet 1 (General location)

Refer to Figure 8, Sheet 1 thru 6 (Detailed location)

Refer to Figure 9, Sheet 1 (Result table)

5 Check the bonding points Items 57 thru 73 at the panel extrados.

Refer to Figure 1, Sheet 1 (General location)

Refer to Figure 10, Sheet 1 thru 10 (Detailed location)

Refer to Figure 11, Sheet 1 (Result table)

(2) Kit 282142A01R05

(a) Modify or install the bonding points.

1 Modify the tube item (528) from feed pipes on LH side between FR46 and FR47.

Refer to Figure 12 Sheets 1 and 2

a Remove :

1 bolt Item (2) Retain

1 nut Item (5) Discard

b On the tube item (528), do a stripping to the dimensions given in the

Figure 12 sheet 2.

c Install :

1 Bonding Lead E0088-10-160 Item 16

1 Clamp NSA5519-2B Item 26

2 Nut NSA5050-3 Item 5

1 Bolt NAS1303-2 Item 2

1 bolt Item (2)

NOTE : Item (2) was retained at removal.

2 Modify the tube item (529) from feed pipes on RH side between FR46 and FR47.

Refer to Figure 12 Sheets 1 and 2

a Remove :

1 bolt Item (2) Retain

1 nut Item (5) Discard

b On the tube item (529), do a stripping to the dimensions given in the

Figure 12 sheet 2.

c Install :

1 Bonding Lead E0088-10-160 Item 16

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 44

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SERVICE BULLETIN

1 Clamp NSA5519-2B Item 26

2 Nut NSA5050-3 Item 5

1 Bolt NAS1303-2 Item 2

1 bolt Item (2)

NOTE : Item (2) was retained at removal.

3 Modify the tube item (557) from the water scavenge pipes on LH side between

FR44 and FR47 :

Refer to Figure 13 Sheets 1, 2 and 5

a Remove :

1 screw Item (574) Discard

1 washer Item (3) Discard

b On the tube item (557), do a stripping to the dimensions given in the

Figure 13 sheet 2.

NOTE : Each datum point corresponds to an angle on the tube.

c Install :

1 Nut NSA5050-3 Item 5

1 Bonding Lead E0088-10-80 Item 15

1 Bolt NAS6603-1 Item 18

1 Clamp NSA5519-4 Item 17

1 Washer NAS1149F0332P Item 3

1 Screw NAS1801-3-10 Item 24

4 Modify the tube item (559) from the water scavenge pipes on LH side between

FR44 and FR47 :

Refer to Figure 13 Sheets 1, 2 and 6

a Remove :

1 screw Item (220) Discard

1 nut Item (4) Discard

b On the tube item (559), do a stripping to the dimensions given in the

Figure 13 sheet 2.

NOTE : Each datum point corresponds to an angle on the tube.

c Install :

1 Nut NSA5050-3 Item 5

1 Bolt NAS6603-1 Item 18

1 Clamp NSA5519-2B Item 26

1 Bonding Lead E0088-41-125 Item 23

1 Bolt NAS6604-3 Item 9

1 Nut NAS1726-4E Item 4

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 45

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A310

SERVICE BULLETIN

5 Modify the tube item (560) from the water scavenge pipes on LH side between

FR44 and FR47 :

Refer to Figure 13 Sheets 1, 3 and 6

a Remove :

1 screw Item (220) Discard

1 nut Item (4) Discard

b On the tube item (560), do a stripping to the dimensions given in the

Figure 13 sheet 3.

NOTE : Each datum point corresponds to an angle on the tube.

c Install :

1 Nut NSA5050-3 Item 5

1 Bolt NAS6603-1 Item 18

1 Clamp NSA5519-2B Item 26

1 Bonding Lead E0088-41-125 Item 23

1 Bolt NAS6604-3 Item 9

1 Nut NAS1726-4E Item 4

6 Modify the tube item (563) from the water scavenge pipes on LH side between

FR44 and FR47 :

Refer to Figure 13 Sheets 1, 3 and 5

a Remove :

1 screw Item (574) Discard

1 washer Item (3) Discard

b On the tube item (563), do a stripping to the dimensions given in the

Figure 13 sheet 3.

NOTE : Each datum point corresponds to an angle on the tube.

c Install :

1 Nut NSA5050-3 Item 5

1 Bolt NAS6603-2 Item 1

1 Bonding Lead E0088-10-80 Item 15

1 Clamp NSA5519-11 Item 20

1 Washer NAS1149F0332P Item 3

1 Screw NAS1801-3-10 Item 24

7 Modify the tube item (565) from the water scavenge pipes on LH side between

FR44 and FR47 :

Refer to Figure 13 Sheets 1, 4 and 5

a Remove :

1 screw Item (574) Discard

1 washer Item (3) Discard

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 46

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

b On the tube item (565), do a stripping to the dimensions given in the

Figure 13 sheet 4.

NOTE : Each datum point corresponds to an angle on the tube.

c Install :

1 Nut NSA5050-3 Item 5

1 Bolt NAS6603-2 Item 1

1 Bonding Lead E0088-10-80 Item 15

1 Clamp NSA5519-11 Item 20

1 Washer NAS1149F0332P Item 3

1 Screw NAS1801-3-10 Item 24

8 Modify the tube item (567) from the water scavenge pipes on LH side between

FR44 and FR47 :

Refer to Figure 13 Sheets 1, 4 and 5

a Remove :

1 screw Item (574) Discard

1 washer Item (3) Discard

b On the tube item (567), do a stripping to the dimensions given in the

Figure 13 sheet 4.

NOTE : Each datum point corresponds to an angle on the tube.

c Install :

1 Nut NSA5050-3 Item 5

1 Bolt NAS6603-2 Item 1

1 Bonding Lead E0088-10-80 Item 15

1 Clamp NSA5519-11 Item 20

1 Washer NAS1149F0332P Item 3

1 Screw NAS1801-3-10 Item 24

9 Modify the tubes item (563) and (561) from the water scavenge pipes on LH side

between FR44 and FR47 :

Refer to Figure 13 Sheets 1 and 5

a Remove :

1 screw Item (574) Discard

1 washer Item (3) Discard

b On the tube item (561), do a stripping to the dimensions given in the

Figure 13 sheet 5.

NOTE : This datum point corresponds to the nut of the tube item (561).

c On the tube item (563), do a stripping to the dimensions given in the

Figure 13 sheet 5.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 47

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

NOTE : Do this stripping close to the stripping done on the tube item

(561).

d Install :

2 Nut NSA5050-3 Item 5

2 Bolt NAS6603-2 Item 1

2 Bonding Lead E0088-10-80 Item 15

2 Clamp NSA5519-11 Item 20

1 Washer NAS1149F0332P Item 3

1 Screw NAS1801-3-11 Item 25

10 Modify the tube item (558) from the water scavenge pipes on RH side between

FR44 and FR47 :

Refer to Figure 13 Sheets 1, 2 and 5

a Remove :

1 screw Item (574) Discard

1 washer Item (3) Discard

b On the tube item (558), do a stripping to the dimensions given in the

Figure 13 sheet 2.

NOTE : Each datum point corresponds to an angle on the tube.

c Install :

1 Nut NSA5050-3 Item 5

1 Bonding Lead E0088-10-80 Item 15

1 Bolt NAS6603-1 Item 18

1 Clamp NSA5519-4 Item 17

1 Washer NAS1149F0332P Item 3

1 Screw NAS1801-3-10 Item 24

11 Modify the tube item (560) from the water scavenge pipes on RH side between

FR44 and FR47 :

Refer to Figure 13 Sheets 1, 2 and 6

a Remove :

1 screw Item (220) Discard

1 nut Item (4) Discard

b On the tube item (560), do a stripping to the dimensions given in the

Figure 13 sheet 2.

NOTE : Each datum point corresponds to an angle on the tube.

c Install :

1 Nut NSA5050-3 Item 5

1 Bolt NAS6603-1 Item 18

1 Clamp NSA5519-2B Item 26

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 48

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A310

SERVICE BULLETIN

1 Bonding Lead E0088-41-125 Item 23

1 Bolt NAS6604-3 Item 9

1 Nut NAS1726-4E Item 4

12 Modify the tube item (559) from the water scavenge pipes on RH side between

FR44 and FR47 :

Refer to Figure 13 Sheets 1, 3 and 6

a Remove :

1 screw Item (220) Discard

1 nut Item (4) Discard

b On the tube item (559), do a stripping to the dimensions given in the

Figure 13 sheet 3.

NOTE : Each datum point corresponds to an angle on the tube.

c Install :

1 Nut NSA5050-3 Item 5

1 Bolt NAS6603-1 Item 18

1 Clamp NSA5519-2B Item 26

1 Bonding Lead E0088-41-125 Item 23

1 Bolt NAS6604-3 Item 9

1 Nut NAS1726-4E Item 4

13 Modify the tube item (564) from the water scavenge pipes on RH side between

FR44 and FR47 :

Refer to Figure 13 Sheets 1, 3 and 5

a Remove :

1 screw Item (574) Discard

1 washer Item (3) Discard

b On the tube item (564), do a stripping to the dimensions given in the

Figure 13 sheet 3.

NOTE : Each datum point corresponds to an angle on the tube.

c Install :

1 Nut NSA5050-3 Item 5

1 Bolt NAS6603-2 Item 1

1 Bonding Lead E0088-10-80 Item 15

1 Clamp NSA5519-11 Item 20

1 Washer NAS1149F0332P Item 3

1 Screw NAS1801-3-10 Item 24

14 Modify the tube item (566) from the water scavenge pipes on RH side between

FR44 and FR47 :

Refer to Figure 13 Sheets 1, 4 and 5

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 49

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

a Remove :

1 screw Item (574) Discard

1 washer Item (3) Discard

b On the tube item (566), do a stripping to the dimensions given in the

Figure 13 sheet 4.

NOTE : Each datum point corresponds to an angle on the tube.

c Install :

1 Nut NSA5050-3 Item 5

1 Bolt NAS6603-2 Item 1

1 Bonding Lead E0088-10-80 Item 15

1 Clamp NSA5519-11 Item 20

1 Washer NAS1149F0332P Item 3

1 Screw NAS1801-3-10 Item 24

15 Modify the tube item (568) from the water scavenge pipes on RH side between

FR44 and FR47 :

Refer to Figure 13 Sheets 1, 4 and 5

a Remove :

1 screw Item (574) Discard

1 washer Item (3) Discard

b On the tube item (568), do a stripping to the dimensions given in the

Figure 13 sheet 4.

NOTE : Each datum point corresponds to an angle on the tube.

c Install :

1 Nut NSA5050-3 Item 5

1 Bolt NAS6603-2 Item 1

1 Bonding Lead E0088-10-80 Item 15

1 Clamp NSA5519-11 Item 20

1 Washer NAS1149F0332P Item 3

1 Screw NAS1801-3-10 Item 24

16 Modify the tubes item (564) and (562) from the water scavenge pipes on RH side

between FR44 and FR47 :

Refer to Figure 13 Sheets 1 and 5

a Remove :

1 screw Item (574) Discard

1 washer Item (3) Discard

b On the tube item (562), do a stripping to the dimensions given in the

Figure 13 sheet 5.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 50

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

NOTE : This datum point corresponds to the nut of the tube item (562).

c On the tube item (564), do a stripping to the dimensions given in the

Figure 13 sheet 5.

NOTE : Do this stripping close to the stripping done on the tube item

(562).

d Install :

2 Nut NSA5050-3 Item 5

2 Bolt NAS6603-2 Item 1

2 Bonding Lead E0088-10-80 Item 15

2 Clamp NSA5519-11 Item 20

1 Washer NAS1149F0332P Item 3

1 Screw NAS1801-3-11 Item 25

17 Modify the tube item (555) from the water drain pipes on LH side between

FR44 and FR47 :

Refer to Figure 14 Sheets 1 and 2

a On the tube item (555), do a stripping to the dimensions given in the

Figure 14 sheet 2.

b Install :

1 Nut NSA5050-3 Item 5

1 Washer NAS1149F0332P Item 3

1 Bolt NAS6603-3 Item 21

1 Clamp NSA5519-4B Item 6

1 Bonding Lead E0088-10-100 Item 19

c On bench :

- Drill two holes on the angle item 10 as per SRM 51-47-00 and at diameter

given in the Figure 14 sheet 1 and 2.

d Temporarily install the bonding lead item 19 on the angle item 10.

e Temporarily install the angle item 10 on the structure as shown in the

Figure 14 sheet 1 and 2.

f Drill the structure to match the holes of the angle item 10 at the dimensions

given in the Figure 14 sheet 2.

g Install :

1 Angle A9242127720000 Item 10

with

2 Rivet ASNA2050DCJ3215 Item 11

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 51

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A310

SERVICE BULLETIN

h Install the bonding lead item 19 on the angle item 10 with :

1 Washer NAS1149F0332P Item 3

1 Bolt NAS6603-3 Item 21

1 Nut NSA5050-3 Item 5

18 Modify the tube item (555) from the water drain pipes on RH side between

FR44 and FR47 :

Refer to Figure 14 Sheets 1 and 2

a On the tube item (555), do a stripping to the dimensions given in the

Figure 14 sheet 2.

b Install :

1 Nut NSA5050-3 Item 5

1 Washer NAS1149F0332P Item 3

1 Bolt NAS6603-3 Item 21

1 Clamp NSA5519-4B Item 6

1 Bonding Lead E0088-10-100 Item 19

c On bench :

- Drill two holes on the angle item 10 as per SRM 51-47-00 and at diameter

given in the Figure 14 sheet 1 and 2.

d Temporarily install the bonding lead item 19 on the angle item 10.

e Temporarily install the angle item 10 on the structure as shown in the

Figure 14 sheet 1 and 2.

f Drill the structure to match the holes of the angle item 10 at the dimensions

given in the Figure 14 sheet 2.

g Install :

1 Angle A9242127720000 Item 10

with

2 Rivet ASNA2050DCJ3215 Item 11

h Install the bonding lead item 19 on the angle item 10 with :

1 Washer NAS1149F0332P Item 3

1 Bolt NAS6603-3 Item 21

1 Nut NSA5050-3 Item 5

(3) Kit 282142A02R02

(a) Modify or install the bonding points.

1 Modify the sleeves item (268) :

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 52

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A310

SERVICE BULLETIN

Refer to Figure 15 Sheets 1 thru 4

a Remove :

Refer to Figure 15 Sheet 2

2 screw Item (2) Retain

2 washer Item (3) Retain

1 screw Item (269) Retain

1 nut Item (4) Discard

- Disengage the bonding lead item (16).

b On the sleeves item (268), do strippings to the dimensions given in the

Figure 15 sheet 4.

c Install on the sleeves item (268) :

Refer to Figure 15 Sheet 4

2 Bonding Lead E0088-41-160 Item 27

2 Clamp AN735D40 Item 13

2 Nut NSA5050-3 Item 5

2 Screw NAS1801-3-8 Item 14

d Put the bonding leads item 16 in position on the tee pipe.

Refer to Figure 15 Sheet 3

e Install :

2 screw Item (2)

2 washer Item (3)

1 screw Item (269)

1 Nut NAS1726-4E Item 4

NOTE : Items (2), (3) and (269) were retained at removal.

2 Modify the sleeve item (268) from TTS pipes.

Refer to Figure 15 Sheets 1 and 5

a Remove :

1 screw Item (220) Retain

1 nut Item (4) Discard

b On the sleeve item (268), do a stripping to the dimensions given in the

Figure 15 sheet 5

c Install on the sleeve item (268) :

1 Bonding Lead E0088-41-125 Item 23

1 Nut NSA5050-3 Item 5

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 53

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A310

SERVICE BULLETIN

1 Clamp AN735D40 Item 13

1 Screw NAS1801-3-8 Item 14

d Install :

1 screw Item (220)

1 Nut NAS1726-4E Item 4

NOTE : Item (220) was retained at removal.

(4) Kit 282142A03R02

(a) Modify or install the bonding points.

1 Install new bonding lead on the cross feed pipe between FR46 and FR47.

Refer to Figure 16 Sheets 1 and 2

a Remove :

1 screw Item (2) Retain

1 washer Item (208) Retain

b On the tube item (549), do a stripping to the dimensions given in the

Figure 16 sheet 2.

c Install :

1 Nut NSA5050-3 Item 5

1 Bolt NAS1303-2 Item 2

1 Bonding Lead E0088-10-250 Item 22

1 Clamp NSA5519-2B Item 26

1 screw Item (2) Retain

1 washer Item (208) Retain

NOTE : Items (2) and (208) were retained at removal.

(5) Kit 282142A04R00

(a) Modify or install the bonding points.

1 Install new bonding lead on the cross feed pipe between FR46 and FR47.

Refer to Figure 17 Sheets 1 and 2

a Remove :

1 screw Item (9) Retain

1 washer Item (12) Discard

b On the tube item (549), do a stripping to the dimensions given in the

Figure 17 sheet 2.

c Install :

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 54

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

1 Nut NSA5050-3 Item 5

1 Bolt NAS1303-2 Item 2

1 Bonding Lead E0088-10-250 Item 22

1 Clamp NSA5519-2B Item 26

1 screw Item (9)

1 Washer NSA5355-4CA Item 12

NOTE : Item (9) retained at removal.

(6) Wings Fuel Tanks

(a) The table that follows lists all the equipment in the wings fuel tanks that are to be

modified for electrical bonding. The work is listed by rib bay. The detailed worksteps

for each rib bay is given in paragraphs (6) thru (28).

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

RIB BAY EQUIPMENT TO

BE ELECTRICALLY

BONDED

REFERENCE Figure APPLICABLE KIT

Rib Bay 1-2 Fuel Feed Pipe.

MLI.

Fuel Pressure Switches

and Pipes.

Fuel Booster Pumps

Canisters.

Fuel Drain Valve and

Pipe (Config. 02)

Fuel Level Sensor.

Water Drain Valve and

Pipe.

Water Scavenge System

(Config. 04)

Figure 18, Sheet 1

Figure 19, Sheet 2

Figure 20, Sheet 1

Figure 21, Sheet 1

Figure 22, Sheet 1

Figure 23, Sheet 1

Figure 24, Sheet 1

Figure 25, Sheet 1

Figure 26, Sheet 1

B01R04 All Aircraft.

B23R02 Config. 02

Aircraft.

B25R02 Config. 04

Aircraft.

Rib Bay 2-3 Slat Track Canister 1.

Diffuser.

Calibration Sensor

(Config. 03).

Figure 27, Sheet 1

Figure 28, Sheet 1

Figure 24, Sheet 1

Kit B03R03 all aircraft.

Kit B24R01 Config. 03

aircraft.

Rib Bay 4-5 Slat Track Canister 2. Figure 29, Sheet 1 and 2 Kit B04R02 all aircraft.

Kit B02R02 or B26R01

Config. 01 aircraft.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 55

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A310

SERVICE BULLETIN

RIB BAY EQUIPMENT TO

BE ELECTRICALLY

BONDED

REFERENCE Figure APPLICABLE KIT

Rib Bay 6-7 Slat Track Canister 3.

MLI.

Diffuser.

Figure 30, Sheet 1

Figure 29, Sheet 2

Figure 19, Sheet 2

Figure 28, Sheet 1

Kit B05R05 all aircraft.

Kit B02R02 or B26R01

Config. 01 aircraft.

Rib Bay 9-10 Slat Track Canister 4. Figure 31, Sheet 1

Figure 29, Sheet 2

Kit B06R02 all aircraft.

Kit B02R02 or B26R01

Config. 01 aircraft.

Rib Bay 10-11 Screwjack Canister 3.

Fuel Drain Valve and

Pipe (Config. 02).

Figure 32, Sheet 1 and 2

Figure 23, Sheet 2

Kit B07R03 all aircraft.

Kit B02R02 or B26R01

Config 01 aircraft.

Kit B23R02 Config. 02

aircraft.

Rib Bay 11-12 MLI.

Cadensicon and Pipe

(RH wing only).

Figure 19, Sheet 2

Figure 33, Sheet 1 and 2

Kit B09R04 all aircraft.

Kit B08R03 all aircraft.

Rib Bay 12-13 Slat Track Canister 5.

Fuel Level Sensor.

Figure 34, Sheet 1

Figure 29, Sheet 2

Figure 24, Sheet 1

Kit B09R04 all aircraft.

Kit B02R02 or B26R01

Config 01 aircraft.

Rib Bay 13-14 Overpressure Protector.

Overwing Refueling

Caps.

MLI.

Figure 35, Sheet 1

Figure 36, Sheet 1,

Sheet 2 and 4

Figure 19, Sheet 2

Kit B10R03 all aircraft.

Rib Bay 14-15 Slat Track Canister 6.

Fuel Pressure Switches

and Pipes.

Fuel Booster Pumps.

Water Drain Valve and

Pipe.

Figure 37, Sheet 1

Figure 29, Sheet 2

Figure 38, Sheet 1

Figure 21, Sheet 1

Figure 25, Sheet 1

Kit B11R03 all aircraft.

Kit B02R02 or B26R01

Config 01 aircraft.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 56

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

RIB BAY EQUIPMENT TO

BE ELECTRICALLY

BONDED

REFERENCE Figure APPLICABLE KIT

Rib Bay 15-16 High Level Sensor.

Low Level Sensor.

Water Drain Valve and

Pipe.

Diffuser.

Figure 24, Sheet 1

Figure 25, Sheet 1

Figure 28, Sheet 2

Kit B12R05 all aircraft.

Rib Bay 16-17 Screwjack Canister 4. Figure 39, Sheet 1

Figure 32, Sheet 2

Kit B13R03 all aircraft.

Kit B02R02 or B26R01

Config 01 aircraft.

Rib Bay 17-18 Slat Track Canister 7. Figure 40, Sheet 1

Figure 29, Sheet 2

Kit B14R04 all aircraft.

Kit B02R02 or B26R01

all aircraft.

Rib Bay 20-21 Slat Track Canister 8. Figure 42, Sheet 1

Figure 29, Sheet 2

Kit B15R03 all aircraft.

Kit B02R02 or B26R01

Config 01 aircraft.

Rib Bay 21-22 Screwjack Canister 5.

MLI.

Fuel Underfull Sensors.

Figure 41, Sheet 1

Figure 32, Sheet 2

Figure 19, Sheet 2

Figure 24, Sheet 2

Kit B16R03 all aircraft.

Kit B02R02 or B26R01

all aircraft.

Rib Bay 23-24 Slat Track Canister 9 Figure 43, Sheet 1

Figure 29, Sheet 2

Kit B17R03 all aircraft.

Kit B02R02 or B26R01

all aircraft.

Rib Bay 24-25 MLI Figure 19, Sheet 2 Kit B19R02 all aircraft.

Rib Bay 25-26 Fuel Level Sensor. Figure 24, Sheet 1 Kit B19R02 all aircraft.

Rib Bay 26-27 Slat Track Canister 10 Figure 44, Sheet 1

Figure 29, Sheet 2

Kit B20R03 all aircraft.

Kit B02R02 or B26R01

all aircraft.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 57

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A310

SERVICE BULLETIN

RIB BAY EQUIPMENT TO

BE ELECTRICALLY

BONDED

REFERENCE Figure APPLICABLE KIT

Rib Bay 27-28 Screwjack Canister 6.

MLI.

Overwing Refueling

Caps.

Figure 45, Sheet 1

Figure 32, Sheet 2

Figure 19, Sheet 2

Figure 36, Sheet 1,

Sheet 3 and 5

Kit B21R04 all aircraft.

Kit B02R02 or B26R01

all aircraft.

Rib Bay 28-29 Water Drain Valve.

Overpressure Protector.

Fuel Overflow Sensor.

Figure 25, Sheet 1

Figure 35, Sheet 2

Figure 24, Sheet 2

Kit B22R03 all aircraft.

Rib Bay 29-30 Slat Track Canister 11. Figure 46, Sheet 1

Figure 29, Sheet 2

Kit B18R04 all aircraft.

Kit B02R02 (LH) and

B26R01 (RH) all aircraft.

CAUTION: DO NOT USE SELF SEALING NUTS AT ANY OF THE BONDING POSITIONS.

(7) Rib Bay 1-2

Kit 282142B01R04

Kit 282142B23R02 Config. 02 Aircraft

Kit 282142B25R02 Config. 04 Aircraft

(a) Fuel Feed Pipe Support-Bracket

Kit 282142B01R04 All Aircraft

Refer to Figure 18, Sheet 1

1 At the fuel pipe support-bracket (Refer to Detail B), remove:

- one nut, Item (93), discard.

- one bolt, Item (95), discard.

- one washer, Item (94), discard.

- one nut, Item (91), discard.

- one bolt, Item (46), discard.

- one washer, Item (96), retain.

At the bracket-rear spar attachment, remove:

- one nut, Item (93), discard.

- one bolt (Pre Mod.06597), Item (98), discard.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 58

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A310

SERVICE BULLETIN

or one bolt (Post Mod.06597) Item (99), discard.

2 At the fuel pipe support-bracket, prepare the bonding areas and install:

1 Bolt NSA5041VBV3-4 Item 95

1 Washer AN960KD10L Item 94

1 Nut NSA5474-3K7 Item 93

1 Bolt NSA5041VBV4-7 Item 46

1 Nut NSA5474-4K7 Item 91

1 Washer Item (96)

3 At the bracket-rear spar attachment, prepare the bonding area and install:

1 Bolt NSA5041VBV3-9 Item 98

or, if applicable:

1 Bolt NSA5041VBV3-12 Item 99

and:

1 Nut NSA5474-3K7 Item 93

(b) MLI

Kit 282142B01R04 All Aircraft

Refer to Figure 19, Sheets 1, Detail A

1 At the base of the MLI, remove:

- one nut, Item (91), discard.

- one bolt, Item (90), retain.

2 At the base of the MLI prepare the bonding area. For the bolt through the wing

skin prepare the countersink. Install:

1 Bolt Item (90)

1 Nut NSA5474-4K7 Item 91

(c) Fuel Pressure Switches and Pipes

Kit 282142B01R04 All Aircraft

Refer to Figure 20, Sheet 1

1 At each pressure switch attachment to the rear spar, remove:

- one nut, Item (93), discard.

- one bolt, Item (101), discard.

2 At the pressure switches pipes prepare the bonding areas and install:

2 Clamp AN742D4 Item 103

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 59

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A310

SERVICE BULLETIN

or

2 Clamp AN742D3 Item 170

2 Lead E0088-10-160 Item 102

2 Bolt NAS1133-2 Item 104

2 Nut NSA5474-3K7 Item 93

3 At the pressure switches attachment to the rear spar prepare the bonding areas

and attach the two bonding leads, Item 102, with:

2 Bolt NSA5041VBV3-13 Item 101

2 Nut NSA5474-3K7 Item 93

4 Torque tighten the nuts, Item 93, to between 0.34-0.40 mdaN (30-35 lbf.in.).

(d) Fuel Booster Pumps Canisters

Kit 282142B01R04 All Aircraft

Refer to Figure 21, Sheet 1

CAUTION : SCREWS THAT GO THROUGH THE FAIRING MUST NOT BE USED

AS ELECTRICAL BONDING POSITIONS.

1 At each of the inboard canisters remove:

- two screws, Item (125), discard.

2 At the inboard canisters prepare the bonding areas at the countersink in the

wing skin only.

Install:

4 Screw NAS1154-21 Item 125

3 At each of the canisters at the fuel outlet flange where the existing bonding

lead, Item (22), is attached, remove:

- one nut, Item (91), discard.

- one bolt, Item (90), retain.

- one end of the bonding lead, Item (22).

4 On the pressure switches pipes prepare the bonding areas and install:

2 Clamp AN742D4 Item 103

2 Lead E0088-41-125 Item 23

2 Bolt NAS1133-2 Item 104

2 Nut NSA5474-3K7 Item 93

5 Torque tighten the nut, Item (93), to between 0.34-0.40 mdaN (30-35 lbf.in.).

6 At the canisters fuel outlet flanges prepare the bonding areas and install:

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 60

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A310

SERVICE BULLETIN

- two retained bolt, Item (90)

- the other end of bonding lead, Item 23

- the other end of bonding lead, Item (22)

2 Nut NSA5474-4K7 Item 91

(e) Fuel Drain Valve and Pipes Config. 02 Aircraft

Kit 282142B23R02

Refer to Figure 22, Sheet 1 and Figure 23, Sheet 1

1 Fuel Drain Valve Pipe to Fuel Booster Pump, Refer to Figure 22, Sheet 1

a At the outer of the two canisters at the clamp, Item (135), remove:

- one end of the bonding lead, Item (134)

- one nut, Item (132), retain.

- one bolt, Item (133), retain.

b Prepare the bonding area at the clamp Item (135) and remove the residual

sealant from the end of the lead, Item (134).

c At the outlet from the canister remove:

- one screw, Item (130), retain.

d Prepare the bonding area and install:

1 Lead E0088-10-100 Item 131

- one retained screw, Item (130)

e Install on the clamp, Item (135)

- the other end of the bonding lead, Item 131

- the other end of the bonding lead, Item (134)

- one retained bolt, Item (133)

- one retained nut, Item (132)

f Torque tighten the nut, Item (132), to between 0.34-0.40 mdaN (30-35 lbf.in.).

2 Fuel Drain Valves and Pipes, Refer to Figure 23, Sheet 1.

a At the valve attachment to the support bracket, remove:

- one nut, Item (93), discard.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

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A310

SERVICE BULLETIN

- one bolt, Item (136), discard.

b At the support bracket attachment to the structure, remove:

- one nut, Item (91), discard.

- one bolt Item (138), discard.

c At the support bracket attachment to the structure prepare the bonding

area and install:

1 Bolt NSA5476VBV-4-11 Item 138

1 Nut NSA5474-4K7 Item 91

d At the valve attachment to the support bracket prepare the bonding area

and install:

1 Lead E0088-10-100 Item 131

1 Bolt NAS1303-8 Item 136

1 Nut NSA5474-3K7 Item 93

e At the valve pipe prepare the bonding area and install:

1 Clamp MS21103D6 Item 140

1 Bolt NAS1096-3-6 Item 141

1 Nut NSA5474-3K7 Item 93

- the other end of the bonding lead, Item 131.

(f) Fuel Level Sensor

Kit 282142B01R04 All Aircraft

Refer to Figure 24, Sheet 1, Detail A

NOTE : It is not necessary to disconnect the fuel level sensors for this

modification.

1 At the support bracket attachment to the structure, remove:

- one nut, Item (160), discard.

- one bolt, Item (157), retain.

2 At the sensor bracket, remove:

- one bolt, Item (154), discard.

- one nut, Item (93), discard.

3 At the support bracket attachment to the structure prepare the bonding area

and install:

- 1 retained bolt, Item (157).

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 62

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

1 Nut NSA5472-5K7 Item 160

4 At the sensor bracket prepare the bonding area and install:

1 Bolt NSA5041VBV3-3 Item 154

1 Nut NSA5474-3K7 Item 93

(g) Water Drain Valve and Pipes

Kit 282142B01R04 All Aircraft

Refer to Figure 25, Sheet 1, Detail A

1 At the water drain valve, remove:

- one nut, Item (91), discard.

- one bolt, Item (73), retain.

2 At the water drain valve-pipe prepare the bonding area and install:

1 Clamp AN742D6 Item 75

1 Lead E0088-41-160 Item 74

1 Bolt NAS1133-1 Item 76

1 Nut NSA5474-3K7 Item 93

3 At the base of the water drain valve prepare the bonding area. For the bolt

through the wing skin prepare the countersink.

Install:

- 1 retained bolt, Item (73).

- the other end of bonding lead, Item 74.

1 Nut NSA5474-4K7 Item 91

(h) Water Scavenge System Config. 04 Aircraft

Kit 282142B25R02

Refer to Figure 26, Sheet 1

1 At each of the two drain pipe clamps (Refer to Detail B), remove:

- one nut, Item (93), discard.

- one bolt, Item (79), discard.

2 At each of the clamp support brackets, remove:

- one nut, Item (93), discard.

- one bolt, Item (136), discard.

3 At the two clamp support brackets prepare the bonding areas and install:

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 63

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

2 Bolt NAS1303-8 Item 136

2 Nut NSA5474-3K7 Item 93

4 At the two drain pipe clamps prepare the bonding area and install:

2 Bolt NAS1303-4 Item 79

2 Nut NSA5474-3K7 Item 93

(8) Rib Bay 2-3

Kit 282142B03R03 All Aircraft

Kit 282142B24R01 Config. 03 Aircraft

(a) Slat Track Canister 1

Kit 282142B03R03 All Aircraft

Refer to Figure 27, Sheet 1

1 At the canister support bracket (Refer to Detail A and B), remove:

- six nuts, Item (93), discard.

- two bolts, Item (154), discard.

- two bolts, Item (3), discard.

- two bolts, Item (4), discard.

2 At the canister support bracket prepare the bonding areas and install:

2 Bolt NSA5041VBV3-3 Item 154

2 Washer AN960C10L Item 5

2 Bolt NSA5041VBV3-5 Item 3

2 Bolt NSA5041VBV3-2 Item 4

6 Nut NSA5474-3K7 Item 93

(b) Diffuser

Kit 282142B03R03 All Aircraft

Refer to Figure 28, Sheet 1, Detail A

1 At the diffuser, remove:

- one bolt, Item (115), discard.

- one washer, Item (116), discard.

2 At the two diffuser support bracket attachment to the structure, remove:

- two nut, Item (160), discard.

NOTE : The bolts attaching the support brackets to the structure are an

interference fit in the wing skin and are therefore bonded. Do

not remove.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 64

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

3 At the two diffuser support brackets attachments to the structure prepare the

bonding areas around the bolt hole in the brackets only and install:

2 Nut NSA5472-5K7 Item 160

4 At the diffuser prepare the bonding area and install:

1 Bolt NAS1304-3 Item 115

1 Washer AN960KD416L Item 116

(c) Calibration Sensor Config. 03 Aircraft

Kit 282142B24R01

Refer to Figure 24, Sheet 3

1 At the sensor bracket attachment to the structure, remove:

- one nut, Item (93), discard.

- one bolt, Item (154), discard.

2 At the sensor attachment to the bracket, remove:

- one nut, Item (93), discard.

- one bolt, Item (154), discard.

3 At the sensor bracket attachment to the structure prepare the bonding area

and install:

1 Bolt NSA5041VBV3-3 Item 154

1 Nut NSA5474-3K7 Item 93

4 At the sensor attachment to the bracket prepare the bonding area and install:

1 Bolt NSA5041VBV3-3 Item 154

1 Nut NSA5474-3K7 Item 93

(9) Rib Bay 4-5

Kit 282142B04R02 All Aircraft

Kit 282142B02R02 or Kit 282142B26R01 Config. 01 Aircraft

(a) Slat Track Canister 2

Kit 282142B04R02

Refer to Figure 29, Sheet 1

1 At the canister bracket attachment to the structure, remove:

- one nut, Item (93), discard.

- one bolt, Item (24), discard.

retain any packing you may find.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 65

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

2 At the canister attachment to the bracket, remove:

- one nut, Item (93), discard.

- one bolt, Item (95), discard.

retain any packing you may find.

3 At the canister bracket attachment to the structure prepare the bonding area and

install (together with any retained packing):

1 Bolt NSA5041VBV3-6 Item 24

1 Nut NSA5474-3K7 Item 93

4 At the canister attachment to the bracket prepare the bonding area and install

(together with any retained packing):

1 Bolt NSA5041VBV3-4 Item 95

1 Nut NSA5474-3K7 Item 93

(b) Canister Drain Config. 01 Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH)

Refer to Figure 29, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (11), discard.

- the two piece retaining plates, Item (7), discard.

- four bolts, Item (13), retain.

2 At the canister drain install the one piece plate, Item 7 LH or Item 8 RH,

as applicable:

1 Plate LH A5715206420000 Item 7

or:

1 Plate RH A5715206420100 Item 8

with:

- 3 retained bolts, Item (13).

3 Nut NSA5472-4K7 Item 11

NOTE : If Service Bulletin A310-57-2053 has been embodied, increase

the bolt hole diameters in the new plate, Item 7 or Item 8, to

between 7.142-7.193mm (0.2812-0.2832in.) for the retained

second oversize bolts, Item (13).

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 66

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

3 Prepare the bonding area. For the bolt hole through the wing skin prepare

the countersink.

Install:

- 1 retained bolt, Item (13).

1 Washer AN960-416 Item 12

1 Nut NSA5472-4K7 Item 11

4 Apply a fillet of Fuel Tank Sealant Polysulfide (Mat. No. 09-001) around the edge

of the new plate to seal Item 7 or Item 8, and over the three nuts, Item 11.

(10) Rib Bay 6-7

Kit 282142B05R05 All Aircraft

Kit 282142B02R02 or Kit 282142B26R01 Config. 01 Aircraft

(a) Slat Track Canister 3

Kit 282142B05R05

Refer to Figure 30, Sheet 1

1 At the canister bracket lower attachment to the structure, remove:

- one nut, Item (93), discard.

- one bolt, Item (154), discard.

retain any packing you may find.

2 At the bracket attachment to the canister, remove:

- one nut, Item (93), discard.

- one bolt, Item (95), discard.

- one washer, Item (5), discard.

retain any packing you may find.

3 At the canister bracket lower attachment to the structure prepare the bonding

area and install (together with any retained packing):

1 Bolt NSA5041VBV3-3 Item 154

1 Nut NSA5474-3K7 Item 93

4 At the bracket attachment to the canister prepare the bonding area and install

(together with any retained packing):

1 Bolt NSA5041VBV3-4 Item 95

1 Washer AN960C10L Item 5

1 Nut NSA5474-3K7 Item 93

(b) Canister Drain Config. 01 Aircraft

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 67

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Kit 282142B02R02 or Kit 282142B26R01 (RH)

Refer to Figure 29, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (11), discard.

- the two piece retaining plates, Item (7), discard.

- four bolts, Item (13), retain.

2 At the canister drain install the one piece plate, Item 7 LH or Item 8 RH,

as applicable:

1 Plate LH A5715206420000 Item 7

or:

1 Plate RH A5715206420100 Item 8

with:

- 3 retained bolts, Item (13).

3 Nut NSA5472-4K7 Item 11

NOTE : If Service Bulletin A310-57-2053 has been embodied, increase the

bolt hole diameters in the new plate, Item 7 or Item 8, to between

7.142-7.193mm (0.2812-0.2832in.) for the retained second oversize

bolts, Item (13).

3 Prepare the bonding area. For the bolt through the wing skin prepare the

countersink.

Install:

- 1 retained bolt, Item (13).

1 Washer AN960-416 Item 12

1 Nut NSA5472-4K7 Item 11

4 Apply a fillet of Fuel Tank Sealant Polysulfide (Mat. No. 09-001) around the edge

of the new plate, Item 7 or Item 8, to seal and over the three nuts, Item 11.

(c) MLI

Kit 282142B05R05

Refer to Figure 19, Sheet 1, Detail A

1 At the base of the MLI, remove:

- one nut, Item (91), discard.

- one bolt, Item (90), retain.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 68

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

2 At the base of the MLI prepare the bonding area. For the bolt through the

wing skin prepare the countersink.

Install:

1 Bolt Item (90)

1 Nut NSA5474-4K7 Item 91

(d) Diffuser

Kit 282142B05R05

Refer to Figure 28, Sheet 1, Detail B

NOTE : To be able to do the bonding at the rear attachment bracket of the

diffuser it may be necessary to remove the diffuser.

1 Removal of the diffuser (Refer to AMM 28-25-15, Page block 401)

Remove:

- One Nut, Item (171), retain.

- One bolt, Item (172), retain.

- Disconnect the bonding lead, Item (174).

- Four Bolt, Item (115), retain.

- Four Washer, Item (116), retain.

- Two Nut, Item (91), discard.

- Two Washer, Item (12), retain.

- One O-ring, Item (173), discard.

- One diffuser, Item (169), retain.

2 At the diffuser support bracket attachments to the structure, remove:

- Four nut, Item (160), discard.

NOTE : The bolts attaching the support brackets to the structure are an

interference fit in the wing skin and are therefore bonded. Do

not remove.

3 At the diffuser support brackets attachments to the structure prepare the bonding

areas around the bolt hole in the brackets only and prepare the bonding at the

two positions for the diffuser and brackets.

4 Install:

4 Nut NSA5474-5K7 Item 160

1 Diffuser Item (169)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 69

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

1 O-Ring NSA8203-226 Item 173

4 Bolt Item (115)

4 Washer Item (116)

2 Nut NSA5474-4K7 Item 91

2 Washer Item (12)

Connect the bonding lead, Item (174) with:

1 Nut Item (171)

1 Bolt Item (172)

(11) Rib Bay 9-10

Kit 282142B06R02 All Aircraft

Kit 282142B02R02 or Kit 282142B26R01 Config. 01 Aircraft

(a) Slat Track Canister 4

Refer to Figure 31, Sheet 1

1 At one of the canister support bracket attachment to the structure (Refer to

Detail C), remove:

- one nut, Item (11), discard.

- two nuts, Item (93), discard.

- two bolts, Item (4), discard.

retain any packing you may find.

NOTE : At the canister bracket to the stringer position the bolt is an

interference fit in the wing skin and is therefore bonded. Do not

remove.

2 At the same support bracket attachment to the canister, remove:

- one nut, Item (93), discard.

- one bolt, Item (4), discard.

retain any packing you may find.

3 At the canister bracket to the stringer position prepare the bonding area around

the bolt hole in the bracket only

Install:

1 Nut NSA5472-4K7 Item 11

4 At the canister support bracket lower attachment prepare the bonding area and

install (together with any retained packing):

2 Bolt NSA5041VBV3-2 Item 4

2 Nut NSA5474-3K7 Item 93

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 70

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

5 At the support bracket attachment to the canister prepare the bonding area and

install (together with any retained packing):

1 Bolt NSA5041VBV3-2 Item 4

1 Washer AN960C10L Item 5

1 Nut NSA5474-3K7 Item 93

(b) Canister Drain Config. 01 Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH)

Refer to Figure 29, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (11), discard.

- the two piece retaining plates, Item (7), discard.

- four bolts, Item (13), retain.

2 At the canister drain install the one piece plate, Item 7 LH or Item 8 RH,

as applicable:

1 Plate LH A5715206420000 Item 7

or:

1 Plate RH A5715206420100 Item 8

with:

- 3 retained bolts, Item (13).

3 Nut NSA5472-4K7 Item 11

NOTE : If Service Bulletin A310-57-2053 has been embodied, increase

the bolt hole diameters in the new plate, Item 7 or Item 8, to

between 7.142-7.193mm (0.2812-0.2832in.) for the retained

second oversize bolts, Item (13).

3 Prepare the bonding area. For the bolt through the wing skin prepare the

countersink.

Install:

- 1 retained bolt, Item (13).

1 Washer AN960-416 Item 12

1 Nut NSA5472-4K7 Item 11

4 Apply a fillet of Fuel Tank Sealant Polysulfide (Mat. No. 09-001) around the

edges of the new plate, Item 7 or Item 8 to seal and over the three nuts, Item 11.

(12) Rib Bay 10-11

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 71

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Kit 282142B07R03 All Aircraft

Kit 282142B02R02 or Kit 282142B26R01 Config. 01 Aircraft

Kit 282142B23R02 Config. 02 Aircraft

(a) Screwjack Canister 3

Kit 282142B07R03

Refer to Figure 32, Sheet 1

1 At the canister flange (Refer to Detail C), remove:

- one nut, Item (42), discard.

- one bolt, Item (41), discard.

2 At the rib adjacent to the canister flange, remove:

- one nut, Item (42), discard.

- one bolt, Item (47), discard.

3 At the canister flange prepare the bonding area and install:

1 Lead E0088-40-100 Item 40

1 Bolt ABS0114-4-10 Item 41

1 Nut NSA5475-4K7 Item 42

4 Overseal the nut, Item 42 and the bolt, Item 41 with Fuel Tank Sealant

Polysulfide (Mat. No. 09-001) and refer to AMM 20-28-11, Page block 001.

5 At the rib adjacent to the flange prepare the bonding area and attach the

bonding lead, Item 40, with:

1 Bolt NSA5041VBV4-8 Item 47

1 Nut NSA5475-4K7 Item 42

6 Torque tighten the bonding lead nuts, Item 42, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

7 Overseal the nut, Item 42 and the bolt, Item 47 with Fuel Tank Sealant

Polysulfide (Mat. No. 09-001) and refer to AMM 20-28-11, Page block 001.

8 At one of the canister support bracket attachments to the structure (Refer to

Detail D), remove:

- one nut, Item (11), discard.

- three nuts, Item (93), discard.

- three bolts, Item (4), discard.

retain any packing you may find.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 72

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

NOTE : The bolt associated with the nut, Item (11), attaching the support

bracket to the structure is an interference fit and is therefore bonded.

Do not remove.

9 At the canister support bracket attachment to the structure prepare the bonding

areas. For the bolt through the wing skin prepare the countersink.

Install: (with any related packing)

3 Bolt NSA5041VBV3-2 Item 4

3 Nut NSA5474-3K7 Item 93

1 Nut NSA5472-4K7 Item 11

(b) Canister Drain Config. 01 Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH)

Refer to Figure 32, Sheet 2, Detail B

1 At the canister drain, remove:

- four nuts, Item (11), discard.

- the two piece retaining plate, Item (7), discard.

- four bolts, Item (13), retain.

2 At the canister drain install the one piece plate, Item 7 LH or Item 8 RH,

as applicable:

1 Plate LH A5715206420000 Item 7

or:

1 Plate RH A5715206420100 Item 8

with:

- 3 retained bolts, Item (13).

3 Nut NSA5472-4K7 Item 11

NOTE : If Service Bulletin A310-57-2053 has been embodied, increase

the bolt hole diameters in the new plate, Item 7 or Item 8, to

between 7.142-7.193mm (0.2812-0.2832in.) for the retained

second oversize bolts, Item (13).

3 Prepare the bonding area and install:

- 1 retained bolt, Item (13).

1 Washer AN960-416 Item 12

1 Nut NSA5472-4K7 Item 11

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 73

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

4 Apply a fillet of Fuel Tank Sealant Polysulfide (Mat. No. 09-001) around the

edges of the new plate, Item 7 or Item 8, to seal, over the three nuts, Item 11

and bolt, Item (13).

(c) Fuel Drain Valve and Pipe Config. 02 Aircraft

Kit 282142B23R02

Refer to Figure 23, Sheet 2

1 At the drain valve support-bracket attachment to the structure at Rib 11, remove:

- one nut, Item (93), discard.

- one bolt, Item (144), discard.

2 At the drain valve support-bracket attachment to the structure at Rib 11 prepare

the bonding area and install:

1 Bolt NSA5041VBV3-7 Item 144

1 Nut NSA5474-3K7 Item 93

3 At the drain valve flange, remove:

- one nut, Item (93), discard.

- one bolt, Item (136), discard.

4 At the drain valve pipe prepare the bonding area and install:

1 Clamp MS21103D6 Item 140

1 Lead E0088-10-160 Item 102

1 Bolt NAS1096-3-6 Item 141

1 Nut NSA5474-3K7 Item 93

5 At the drain valve flange prepare the bonding area.

Install:

1 Bolt NAS1303-8 Item 136

1 Nut NSA5474-3K7 Item 93

- the other end of lead, Item 102

6 Torque tighten the bonding lead nut, Item 93, to between 0.34-0.40 mdaN

(30-35 lbf.in.).

(13) Rib Bay 11-12

Kit 282142B08R03 All Aircraft

Kit 282142B09R04 All Aircraft

(a) MLI

Kit 282142B09R04

Refer to Figure 19, Sheets 1 and 2

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 74

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

1 Remove the fuel pipe to gain access (Refer to Figure 19, Sheet 2 and AMM

28-00-00, Page block 401).

Remove:

8 Bolt Item (176) Discard

4 O-ring Item (165) Discard

8 Nut Item (175) Discard

1 Pipe A2825012600400 Item (168) Retain

2 At the base of the MLI, remove (Refer to Figure 19, Sheet 1, Detail A):

- one nut, Item (91), discard.

- one bolt, Item (90), retain.

3 At the base of the MLI prepare the bonding area. For the bolt through the wing

skin prepare the countersink (Refer to Figure 19, Sheet 1, Detail A).

Install:

- 1 retained bolt, Item (90).

1 Nut NSA5474-4K7 Item 91

4 Reinstall the fuel pipe (Figure 19, Sheet 2).

Refer to AMM 28-00-00, Page block 401

Install:

1 Pipe A2825012600400 Item (168)

with

4 O-Ring NSA8203-234 Item 165

8 Nut NAS1291C06M Item 175

8 Bolt NAS1096-1-4 Item 176

(b) Cadensicon and Pipe - RH Wing only

Kit 282142B08R03

Refer to Figure 33, Sheets 1 and 2

1 At the cadensicon sensor (Refer to Sheet 1, Detail A) remove:

- one nut, Item (93), discard.

- one bolt, Item (118), discard.

2 At the cadensicon sensor prepare the bonding area and install:

1 Bolt NAS1303-6 Item 118

1 Nut NSA5474-3K7 Item 93

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 75

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

3 At the cadensicon attachment to the front spar (Refer to Detail B), remove:

- one nut, Item (91), discard.

- one bolt (Post Mod.03522), Item (120), discard.

- or one bolt (Pre Mod.03522), (130), discard.

4 On the cadensicon pipe adjacent to the cadensicon prepare the bonding area

and install:

1 Clamp AN742D8 Item 122

1 Lead E0088-41-160 Item 74

1 Bolt NAS1100-3-7 Item 123

1 Nut NSA5472-3K7 Item 124

5 At the cadensicon attachment to the front spar prepare the bonding area and

attach the bonding lead, Item 74, with:

Post Mod.03522 bolt:

1 Bolt NAS1304-11 Item 120

or Pre Mod.03522 bolt:

1 Bolt NAS1304-9 Item 130

and:

1 Nut NSA5474-4K7 Item 91

6 At the other end of the pipe (Refer to Figure 33, Sheet 2) prepare the bonding

area and install:

1 Clamp AN742D8 Item 122

1 Lead E0088-10-125 Item 114

1 Bolt NAS1100-3-7 Item 123

1 Nut NSA5472-3K7 Item 124

7 At the existing bonding lead lug on the adjacent refuel pipe, remove:

- one nut, Item (124), discard.

- one bolt, Item (123), discard.

- one end of the bonding lead, Item (121).

- one end of the bonding lead, Item (127).

8 Prepare the bonding area on the lug and remove any residual sealant from the

bonding leads, Items (121) and (127).

Install:

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 76

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

1 Bolt NAS1100-3-7 Item 123

1 Nut NSA5472-3K7 Item 124

- one end of lead, Item (121).

- one end of lead, Item (127).

- one end of lead, Item 128.

9 Torque tighten the bonding lead nuts, Item 124 to between 0.34-0.35 mdaN

(30-35 lbf.in.).

(14) Rib Bay 12-13

Kit 282142B09R04 All Aircraft

Kit 282142B02R02 or Kit 282142B26R01 Config. 01 Aircraft

(a) Slat Track Canister 5

Kit 282142B09R04

Refer to Figure 34, Sheet 1

1 At the canister flange (Refer to Detail C), remove:

- one nut, Item (91), discard.

- one bolt, Item (41), discard.

2 At the rib adjacent to the canister flange, remove:

- one nut, Item (42), discard.

- one bolt, Item (161), discard.

3 At the canister flange prepare the bonding area and install:

1 Lead E0088-40-200 Item 162

1 Bolt ABS0114-4-10 Item 41

1 Nut NSA5474-4K7 Item 91

4 At the rib adjacent to the canister flange prepare the bonding area and attach

the bonding lead, Item 162, with:

1 Bolt NSA5041VBV4-10 Item 161

1 Nut NSA5475-4K7 Item 42

5 Torque tighten the bonding lead nuts, Item 42, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

6 At the canister support bracket attachment to the structure, remove:

- one nut, Item (93), discard.

- one bolt, Item (3), discard.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 77

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

retain any packing you may find.

7 At the support bracket attachment to the canister, remove:

- one nut, Item (93), discard.

- one bolt, Item (95), discard.

8 At the canister support bracket attachment to the structure prepare the bonding

area and install:

1 Bolt NSA5041VBV3-5 Item 3

1 Nut NSA5474-3K7 Item 93

9 At the support bracket attachment to the canister prepare the bonding area

and install:

1 Bolt NSA5041VBV3-4 Item 95

1 Nut NSA5474-3K7 Item 93

(b) Canister Drain Config. 01 Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH)

Refer to Figure 29, Sheet 2, Detail B

1 At the canister drain, remove:

- four nuts, Item (11), discard.

- the two piece retaining plate, Item (7), discard.

- four bolts, Item (13), retain.

2 At the canister drain install the one piece plate, Item 7 LH or Item 8 RH,

as applicable:

1 Plate LH A5715206420000 Item 7

or:

1 Plate RH A5715206420100 Item 8

with;

- 3 retained bolts, Item (13).

3 Nut NSA5472-4K7 Item 11

NOTE : If Service Bulletin A310-57-2053 has been embodied, increase

the bolt hole diameters in the new plate, Item 7 or Item 8, to

between 7.142-7.193mm (0.2812-0.2832in.) for the retained

second oversize bolts, Item (13).

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 78

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

3 Prepare the bonding area. For the bolt through the wing skin prepare the

countersink.

Install:

- 1 retained bolt, Item (13).

1 Washer AN960-416 Item 12

1 Nut NSA5472-4K7 Item 11

4 Apply a fillet of Fuel Tank Sealant Polysulfide (Mat. No. 09-001) around the

edges of the new plate, Item 7 or Item 8, to seal and over the three nuts, Item 11.

(c) Fuel Level Sensor

Kit 282142B09R04

Refer to Figure 24, Sheet 1, Detail C

1 At the sensor support bracket attachment to the structure, remove:

- one nut, Item (93), discard.

- one bolt, Item (24), discard.

2 At the sensor attachment to the support bracket, remove:

- one bolt, Item (153), discard.

3 At the sensor support bracket attachment to the structure prepare the bonding

area and install:

1 Bolt NSA5041VBV3-6 Item 24

1 Nut NSA5474-3K7 Item 93

4 At the sensor attachment to the support bracket prepare the bonding area

and install:

1 Bolt NAS1303-3 Item 153

(15) Rib Bay 13-14

Kit 282142B10R03 All Aircraft

(a) Overpressure Protector

Refer to Figure 35, Sheet 1

1 At the attachment of the overpressure protector to the manhole cover, remove:

- one nut, Item (91), discard.

- one bolt, Item (168), discard.

2 At the attachment of the overpressure protector to the manhole cover prepare

the bonding area and install:

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 79

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

1 Bolt NAS1304-10 Item 168

1 Nut NSA5474-4K7 Item 91

(b) MLI

Refer to Figure 19, Sheet 1, Detail A

1 At the base of the MLI, remove:

- one nut, Item (91), discard.

- one bolt, Item (90), retain.

2 At the base of the MLI prepare the bonding area. For the bolt through the

wing skin prepare the countersink.

Install:

- 1 retained bolt, Item (90).

1 Nut NSA5474-4K7 Item 91

(c) Overwing Refuel Caps Config. 06 Config. 07

Refer to Figure 36, Sheet 1, View A

1 Remove the overwing refuel adaptor (Refer to AMM 28-11-28, Page block 401).

2 Put protective material or masking tape on the top surface of the wing skin,

around the overwing refuel adaptor hole.

3 Clean the contact surfaces of the overwing refuel adaptor and the wing skin

opening with Cleaning agent (Mat. No. 11-026).

4 Apply Alodine (Mat. No. 13-002) to the overwing refuel adaptor.

5 Apply low adhesive Sealant (Mat. No. 09-018) to the interface of the adaptor

and the wing surface and also on the threads of the adaptor. Do not use Mat No.

09-001 as listed in AMM 28-11-28, Page block 401).

6 Install the overwing refuel adaptor (Refer to AMM 28-11-28, Page block 401).

7 Remove any unwanted sealant.

8 Remove the protective material that you put around the opening.

(d) Config. 05 Overwing Refuel Caps

Refer to Figure 36, Sheet 2, View D and Sheet 4, View F

1 Do a resistance check between the flange face of the refuel insert and the wing.

If the resistance is <10mohm, no further action is necessary. If the resistance is

>10mohm then do the steps that follow:

2 Remove from the refuel adaptor the items that follow:

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 80

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

1 Nut NSA5470-4K7 Item (169) Discard

1 Bolt-Hi Lok,Csk Head NSA5476BV4-18 Item (575) Retain

3 Prepare for electrical bonding.

4 Install:

1 Bolt-Hi Lok,Csk Head NSA5476BV4-18 Item (575) Retained

1 Nut NSA5470-4K7 Item 169

5 Over seal the nut, Item 169.

6 Do a bonding check and make sure the resistance is <10mohm.

(16) Rib Bay 14-15

Kit 282142B11R03 All Aircraft

Kit 282142B02R02 or Kit 282142B26R01 Config. 01 Aircraft

(a) Slat Track Canister 6

Kit 282142B11R03

Refer to Figure 37, Sheet 1

1 At the canister flange, remove:

- one nut, Item (42), discard.

- one bolt, Item (41), discard.

2 At the rib adjacent to the canister flange, remove:

- one nut, Item (42), discard.

- one bolt, Item (161), discard.

3 At the canister flange prepare the bonding area and install:

1 Lead E0088-40-200 Item 162

1 Bolt ABS0114-4-10 Item 41

1 Nut NSA5475-4K7 Item 42

4 Overseal the nut, Item 41 and the bolt, Item 42 with Fuel Tank Sealant

Polysulfide (Mat. No. 09-001) and refer to AMM 20-28-11, Page block 001.

5 At the rib adjacent to the canister flange prepare the bonding area and attach

the bonding lead, Item 162, with:

1 Bolt NSA5041VBV4-10 Item 161

1 Nut NSA5475-4K7 Item 42

6 Torque tighten the bonding lead nuts, Item 42, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

7 At the lower support bracket attachment (Refer to Detail E) remove:

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 81

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

- one nut, Item (11), discard.

NOTE : The bolt attaching the support bracket to the structure is an interference

fit in the wing skin and is therefore bonded. Do not remove.

8 At the lower support bracket attachment prepare the bonding area around the

bolt hole in the bracket only.

Install:

1 Nut NSA5472-4K7 Item 11

9 At the support bracket attachment (Refer to Detail D) drill out one rivet and

increase the diameter of the hole to 4.826-4.877mm (0.190-0.192in.) to allow

for the installation of a bolt.

10 At the canister support bracket (Refer to Detail D) remove:

- one nut, Item (93), discard.

- one bolt, Item (4), discard.

retain any packing you may find.

11 At the bracket lower attachment prepare the bonding area and install (together

with any retained packing):

1 Bolt NAS1303-2 Item 19

1 Nut NSA5472-3K7 Item 124

1 Bolt NSA5041VBV3-2 Item 4

1 Nut NSA5474-3K7 Item 93

(b) Canister Drain Config. 01 Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH)

Refer to Figure 29, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (11), discard.

- the two piece retaining plate, Item (7), discard.

- four bolts, Item (13), retain.

2 At the canister drain install the one piece plate, Item 7 or Item 8, as applicable:

1 Plate LH A5715206420000 Item 7

or:

1 Plate RH A5715206420100 Item 8

with:

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 82

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

- 3 retained bolts, Item (13).

3 Nut NSA5472-4K7 Item 11

NOTE : If Service Bulletin A310-57-2053 has been embodied, increase

the bolt hole diameters in the new plate, Item 7 or Item 8, to

between 7.142-7.193mm (0.2812-0.2832in.) for the retained

second oversize bolts, Item (13).

3 Prepare the bonding area. For the bolt through the wing skin prepare the

countersink.

Install:

- 1 retained bolt, Item (13).

1 Washer AN960-416 Item 12

1 Nut NSA5472-4K7 Item 11

4 Apply a fillet of Fuel Tank Sealant Polysulfide (Mat. No. 09-001) around the

edges of the new plate, Item 7 or Item 8, to seal and over the three nuts, Item 11.

(c) Fuel Pressure Switches and Pipes

Kit 282142B11R03

Refer to Figure 38, Sheet 1 and Sheet 2

1 At each pressure switch attachment to the rear spar, remove:

- one nut, Item (93), discard.

- one bolt, Item (144), discard.

2 On the pressure switch pipes, prepare the bonding areas and install:

2 Clamp AN742D4 Item 103

2 Lead E0088-10-100 Item 131

2 Bolt NAS1100-3-7 Item 123

2 Nut NSA5474-3K7 Item 93

3 Torque tighten the bonding lead nuts, Item 93, to between 0.34-0.40 mdaN

(30-35 lbf.in.).

4 At the pressure switches attachment to the rear spar prepare the bonding areas.

Install:

2 Bolt NSA5041VBV3-7 Item 144

2 Nut NSA5474-3K7 Item 93

- the other end of the bonding lead, Item 131.

5 At the pipes support bracket on rib 15 (Refer to Figure 38, Sheet 2, Detail

C) remove:

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 83

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

- one nut, Item (93), discard.

- one bolt, Item (24), discard.

6 On the two pressure switches pipes prepare the bonding area and install:

2 Clamp AN742D4 Item 103

1 Lead E0088-10-100 Item 131

1 Lead E0088-10-125 Item 114

2 Bolt NAS1100-3-6 Item 110

2 Nut NSA5474-3K7 Item 93

7 At the pipes support brackets prepare the bonding areas and install:

1 Bolt NSA5041VBV3-6 Item 24

1 Nut NSA5474-3K7 Item 93

- the other end of the lead, Item 114.

8 Torque tighten the bonding lead nuts, Item 93, to between 0.34-0.40 mdaN

(30-35 lbf.in.).

(d) Fuel Booster Pumps Canisters

Kit 282142B11R03

Refer to Figure 21, Sheet 2

1 At each of the canisters, remove:

- two screws, Item (126), discard.

CAUTION : SCREWS THAT GO THROUGH THE FAIRING ARE NOT TO BE

USED FOR BONDING.

2 At the canisters prepare the bonding areas at the countersink in the wing

skin only.

Install:

4 Screw NAS1154-10 Item 166

(e) Water Drain Valve and Pipe

Kit 282142B11R03

Refer to Figure 25, Sheet 1, Detail A

1 At the water drain valve, remove:

- one nut, Item (91), discard.

- one bolt, Item (73), retain.

2 At the water drain valve-pipe prepare the bonding area and install:

1 Clamp AN742D6 Item 75

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 84

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

1 Lead E0088-41-160 Item 74

1 Bolt NAS1133-1 Item 76

1 Nut NAS5474-3K7 Item 93

3 At the base of the water drain valve prepare the bonding areas. For the bolt

through the wing skin prepare the countersink.

Install:

- 1 retained bolt, Item (73).

- the other end of the bonding lead, Item 74.

1 Nut NSA5474-4K7 Item 91

(17) Rib Bay 15-16

Kit 282142B12R05 All Aircraft

(a) Fuel Level Sensors

Refer to Figure 24, Sheet 1

1 At the high level sensor bracket (Refer to Detail C) attachment to the structure

remove:

- one nut, Item (93), discard

- one bolt, Item (3), discard.

2 At the high level sensor attachment to the bracket, remove:

- one nut, Item (93), discard.

- one bolt, Item (154), discard.

3 At the bracket attachment to the structure, prepare the bonding area and install:

1 Bolt NSA5041VBV3-5 Item 3

1 Nut NSA5474-3K7 Item 93

4 At the high level sensor attachment to the bracket prepare the bonding area

and install:

1 Bolt NSA5041VBV3-3 Item 154

1 Nut NSA5474-3K7 Item 93

5 At the low level sensor (Refer to Detail A), bracket attachment to the structure,

remove:

- one bolt, Item (3), discard.

- one nut, Item (93), discard.

6 At the sensor attachment to the bracket, remove:

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 85

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

- one nut, Item (93), discard.

- one bolt, Item (154), discard.

7 At the low level sensor bracket attachment to the structure prepare the bonding

area and install:

1 Bolt NSA5041VBV3-5 Item 3

1 Nut NSA5474-3K7 Item 93

8 At the sensor attachment to the bracket prepare the bonding area and install:

1 Bolt NSA5041VBV3-3 Item 154

1 Nut NSA5474-3K7 Item 93

(b) Water Drain Valve and Pipe

Refer to Figure 25, Sheet 1, Detail A

1 At the water drain valve, remove:

- one nut, Item (91), discard.

- one bolt, Item (73), retain.

2 At the water drain valve-pipe prepare the bonding area and install:

1 Clamp AN742D6 Item 75

1 Lead E0088-41-160 Item 74

1 Bolt NAS1133-1 Item 76

1 Nut NSA5474-3K7 Item 93

3 At the base of the water drain valve prepare the bonding area. For the bolt

through the wing skin prepare the countersink only.

Install:

- 1 retained bolt, Item (73).

- the other end of bonding lead, Item 74.

1 Nut NSA5474-4K7 Item 91

(c) Diffuser

Refer to Figure 28, Sheet 2

1 At the diffuser, remove:

- one bolt, Item (19), discard.

- one nut, Item (93), discard.

2 At each of the support brackets attachment to the structure, remove:

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 86

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

- one nut, Item (11) or (160), discard.

NOTE : The bolt attaching the support bracket to the structure are an

interference fit in the wing skin and is therefore bonded. Do not remove:

3 At the diffuser support brackets attachments to the structure prepare the bonding

area around the bolt hole in the brackets only.

Install:

2 Nut NSA5472-4K7 Item 11

or

2 Nut NSA5472-5K7 Item 160

4 At the diffuser prepare the bonding area and install:

1 Bolt NAS1303-2 Item 19

1 Nut NSA5474-3K7 Item 93

(18) Rib Bay 16-17

Kit 282142B13R03 All Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH) Config. 01 Aircraft

(a) Screwjack Canister 4

Kit 282142B13R03

Refer to Figure 39, Sheet 1

1 At the canister flange, remove:

- one nut, Item (42), discard.

- one bolt, Item (48), discard.

2 At the rib adjacent to the canister flange, remove:

- one nut, Item (42), discard.

- one bolt, Item (161), discard.

3 At the canister flange prepare the bonding area and install:

1 Lead E0088-40-100 Item 40

1 Bolt ABSO114-4-11 Item 48

1 Nut NSA5475-4K7 Item 42

4 At the rib adjacent to the canister flange prepare the bonding area and attach

the bonding lead, Item 40, with:

1 Bolt NSA5041VBV4-10 Item 161

1 Nut NSA5475-4K7 Item 42

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 87

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

5 Torque tighten the bonding lead nuts, Item 42, to between 0.68-0.70 mdaN

(60-70 lbf.in.).

6 At the canister attachment bracket to the structure, remove:

- one nut, Item (93), discard.

- one bolt, Item (4), discard.

- one nut, Item (11), discard.

retain any packing you may find.

NOTE : The bolt attaching the support bracket to the structure is an interference

fit in the wing skin and is therefore bonded. Do not remove.

7 At the lower support bracket to the structure prepare the bonding area around

the bolt hole in the bracket only.

Install:

1 Nut NSA5472-4K7 Item 11

8 At the intermediate support bracket attachment drill out one rivet and increase

the diameter of the hole to 4.826-4.877mm (0.190-0.192in.) to allow for the

installation of a bolt.

9 At the canister attachment bracket prepare the bonding area and install (together

with any retained packing):

1 Bolt NSA5041VBV3-2 Item 4

1 Nut NSA5474-3K7 Item 93

10 At the support bracket, at the hole that you have drilled, prepare the bonding

area and install:

1 Bolt NAS1303-3 Item 153

1 Nut NSA5472-3K7 Item 124

(b) Canister Drain Config. 01 Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH)

Refer to Figure 32, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (11), discard.

- the two piece retaining plate, Item (7), discard.

- four bolts, Item (13), retain.

2 At the canister drain install the one piece plate, Item 7 or Item 8, as applicable:

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 88

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

1 Plate LH A5715206420000 Item 7

or:

1 Plate RH A5715206420100 Item 8

with:

- 3 retained bolts, Item (13).

3 Nut NSA5472-4K7 Item 11

NOTE : If Service Bulletin A310-57-2053 has been embodied, increase

the bolt hole diameters in the new plate, Item 7 or Item 8, to

between 7.142-7.193mm (0.2812-0.2832in.) for the retained

second oversize bolts, Item (13).

3 Prepare the bonding area. For the bolt through the wing skin prepare the

countersink only.

Install:

- 1 retained bolt, Item (13).

1 Washer AN960-416 Item 12

1 Nut NSA5472-4K7 Item 11

4 Apply a fillet of Fuel Tank Sealant Polysulfide (Mat. No. 09-001) around the

edges of the new plate, Item 7 or Item 8, to seal and over the three nuts, Item 11.

(19) Rib Bay 17-18

Kit 282142B14R04 All Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH) All Aircraft

(a) Slat Track Canister 7

Kit 282142B14R04

Refer to Figure 40, Sheet 1

1 At the canister flange, remove:

- one nut, Item (42), discard.

- one bolt, Item (163), discard.

2 At the rib adjacent to the canister flange, remove:

- one nut, Item (42), discard.

- one bolt, Item (161), discard.

3 At the canister flange prepare the bonding area and install:

1 Lead-Bonding E0088-40-125 Item 164

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 89

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

1 Bolt ABS0114-4-11 Item 163

1 Nut NSA5475-4K7 Item 42

4 At the rib adjacent to the canister flange prepare the bonding area and attach

the bonding lead, Item 164, with:

1 Bolt NSA5041VBV4-10 Item 161

1 Nut NSA5475-4K7 Item 42

5 Torque tighten the bonding lead nut, Item 42, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

6 At the canister support bracket attachment to the structure (Refer to Detail

D), remove:

- two nuts, Item (93), discard

- two bolts, Item (4), discard.

- one nut, Item (11), discard.

retain any packing you may find.

NOTE : The bolt attaching the support bracket to the structure is an interference

fit and is therefore bonded. Do not remove.

7 At the lower support bracket to the structure prepare the bonding area around

the bolt hole in the bracket only.

1 Nut NSA5472-4K7 Item 11

8 At the intermediate canister support bracket attachment prepare the bonding

area and install (together with any retained packing):

2 Bolt NSA5041VBV3-2 Item 4

2 Nut NSA5474-3K7 Item 93

(b) Canister Drain - All Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH)

Refer to Figure 29, Sheet 2

1 At the canister drain (Refer to Detail B), remove:

- four nuts, Item (11), discard.

- the two piece retaining plate, Item (7), discard.

- four bolts, Item (13), retain.

2 At the canister drain install the one piece plate, Item 7 or Item 8, as applicable:

1 Plate LH A5715206420000 Item 7

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 90

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

or:

1 Plate RH A5715206420100 Item 8

with:

- 3 retained Bolts, Item (13).

3 Nut NSA5472-4K7 Item 11

NOTE : If Service Bulletin A310-57-2053 has been embodied, increase

the bolt hole diameters in the new plate, Item 7 or Item 8, to

between 7.142-7.193mm (0.2812-0.2832in.) for the retained

second oversize bolts, Item (13).

3 At the canister drain prepare the bonding area. For the bolt through the wing

skin prepare the countersink only.

Install:

- 1 retained Bolt, Item (13).

1 Washer AN960-416 Item 12

1 Nut NSA5472-4K7 Item 11

4 Apply a fillet of Fuel Tank Sealant Polysulfide (Mat. No. 09-001) around the

edges of the new plate, Item 7 or Item 8, to seal and over the three nuts, Item 11.

(20) Rib Bay 20-21

Kit 282142B15R03 All Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH) Config. 01 Aircraft

(a) Slat Track Canister 8

Kit 282142B15R03 All Aircraft

Refer to Figure 42, Sheet 1

1 At the canister flange (Refer to Detail C), remove:

- one nut, Item (42), discard.

- one bolt, Item (34), discard.

2 At the rib adjacent to the canister flange, remove:

- one bolt, Item (161), discard.

- one nut, Item (42), discard.

3 At the canister flange prepare the bonding area and install:

1 Lead E0088-40-100 Item 40

1 Bolt ABS0114-4-9 Item 34

1 Nut NSA5475-4K7 Item 42

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 91

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

4 At the rib adjacent to the canister flange prepare the bonding area and attach

the bonding lead, Item 40, with:

1 Bolt NSA5041VBV4-10 Item 161

1 Nut NSA5475-4K7 Item 42

5 Torque tighten the bonding lead nuts, Item 42, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

6 At the canister attachment bracket, remove:

- two nuts, Item (93), discard.

- one bolt, Item (3), discard.

- one bolt, Item (95), discard.

7 At the canister attachment bracket prepare the bonding area and install:

1 Bolt NSA5041VBV3-4 Item 95

1 Bolt NSA5041VBV3-5 Item 3

2 Nut NSA5474-3K7 Item 93

(b) Canister Drain

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH) Config. 01 Aircraft

Refer to Figure 29, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (11), discard.

- the two piece retaining plate, Item (7), discard.

- four bolts, Item (13), retain.

2 At the canister drain install the one piece plate, Item 7 or Item 8, as applicable:

1 Plate LH A5715206420000 Item 7

or:

1 Plate RH A5715206420100 Item 8

with:

- 3 retained bolts, Item (13).

3 Nut NSA5472-4K7 Item 11

NOTE : If Service Bulletin A310-57-2053 has been embodied, increase

the bolt hole diameters in the new plate, Item 7 or Item 8, to

between 7.142-7.193mm (0.2812-0.2832in.) for the retained

second oversize bolts, Item (13).

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 92

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

3 At the canister drain prepare the bonding area. For the bolt through the wing

skin prepare the countersink.

Install:

- 1 retained bolt, Item (13).

1 Washer AN960-416 Item 12

1 Nut NSA5472-4K7 Item 11

4 Apply a fillet of Fuel Tank Sealant Polysulfide (Mat. No. 09-001) around the

edges of the new plate, Item 7 or Item 8, to seal and over the three nuts, Item 11.

(21) Rib Bay 21-22

Kit 282142B16R03 All Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH) All Aircraft

(a) Screwjack Canister 5

Kit 282142B16R03

Refer to Figure 41, Sheet 1

1 At the canister flange (Refer to Detail C), remove:

- one nut, Item (42), discard.

- one bolt, Item (34), discard.

2 At the rib adjacent to the canister flange, remove:

- one nut, Item (42), discard.

- one bolt, Item (47), discard.

3 At the canister flange prepare the bonding area and install:

1 Lead E0088-40-100 Item 40

1 Bolt ABS0114-4-9 Item 34

1 Nut NSA5475-4K7 Item 42

4 At the rib adjacent to the canister flange prepare the bonding area and attach

the bonding lead, Item 40, with:

1 Bolt NSA5041VBV4-8 Item 47

1 Nut NSA5475-4K7 Item 42

5 Torque tighten the bonding lead nuts, Item 42, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

6 At the canister attachment bracket, remove:

- one bolt, Item (35), discard.

- one bolt, Item (3), discard.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 93

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

- one nut, Item (93), discard.

7 At the canister attachment bracket prepare the bonding area and install:

1 Bolt NSA5041VBV3-5 Item 3

1 Nut NSA5474-3K7 Item 93

1 Bolt ABS0114-3-4 Item 35

(b) Canister Drain - All Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH) All Aircraft

Refer to Figure 32, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (11), discard.

- the two piece retaining plate, Item (7)

- four bolts, Item, Item (13), retain.

2 At the canister drain install the one piece plate, Item 7 LH or Item 8 RH,

as applicable:

1 Plate LH A5715206420000 Item 7

or:

1 Plate RH A5715206420100 Item 8

with:

- 3 retained bolts, Item (13).

3 Nut NSA5472-4K7 Item 11

NOTE : If Service Bulletin A310-57-2053 has been embodied, increase

the bolt hole diameters in the new plate, Item 7 or Item 8, to

between 7.142-7.193mm (0.2812-0.2832in.) for the retained

second oversize bolts, Item (13).

3 Prepare the bonding area. For the bolt through the wing skin prepare the

countersink only.

Install:

- 1 retained bolt, Item (13).

1 Washer AN960-416 Item 12

1 Nut NSA5472-4K7 Item 11

4 Apply a fillet of Fuel Tank Sealant Polysulfide (Mat. No. 09-001) around the

edges of the new plate, Item 7 or Item 8, to seal and over the three nuts, Item 11.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 94

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

(c) Fuel Underfull Sensors

Refer to Figure 24, Sheet 2, Detail D

1 At each of the sensors attachment to the bracket, remove:

- one nut, Item (93), discard.

- one bolt, Item (154), discard.

2 At the bracket attachment to the structure, remove:

- one nut, Item (93), discard.

- one bolt, Item (4), discard.

3 At the bracket attachment to the structure prepare the bonding area and install:

1 Bolt NSA5041VBV3-2 Item 4

1 Nut NSA5474-3K7 Item 93

4 At the sensors attachment to the bracket prepare the bonding areas and install:

2 Bolt NSA5041VBV3-3 Item 154

2 Nut NSA5474-3K7 Item 93

(d) MLI

Refer to Figure 19, Sheet 1 Detail A

1 At the base of the MLI, remove:

- one nut, Item (91), discard.

- one bolt, Item (90), retain.

2 At the base of the MLI prepare the bonding area. For the bolt through the wing

skin prepare the countersink only.

Install:

- 1 retained bolt, Item (90).

1 Nut NSA5474-4K7 Item 91

(22) Rib Bay 23-24

Kit 282142B17R03 All Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH) All Aircraft

(a) Slat Track Canister 9

Kit 282142B17R03

Refer to Figure 43, Sheet 1

1 At the canister flange (Refer to Detail C), remove:

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

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A310

SERVICE BULLETIN

- one nut, Item (42), discard.

- one bolt, Item (45), discard.

2 At the rib adjacent to the canister flange, remove:

- one nut, Item (42), discard.

- one bolt, Item (161), discard.

3 At the canister flange prepare the bonding area and install:

1 Lead E0088-40-100 Item 40

1 Bolt ABS0114-4-8 Item 45

1 Nut NSA5475-4K7 Item 42

4 At the rib adjacent to the canister flange prepare the bonding area and attach

the bonding lead, Item 40, with:

1 Bolt NSA5041VBV4-10 Item 161

1 Nut NSA5475-4K7 Item 42

5 Torque tighten the bonding lead nuts, Item 42, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

6 At the canister attachment bracket remove:

(Post Mod.07597)

- one nut, Item (93), discard.

- one bolt, Item (95), discard.

- one nut, Item (124), discard.

- two bolts, Item (37), discard.

retain any packing you may find.

or Pre Mod.07597:

- two nuts, Item (93), discard.

- one bolt, Item (3), discard.

- one bolt, Item (95), discard.

retain any packing you may find.

7 At the canister attachment bracket prepare the bonding area and install (together

with any retained packing):

Post Mod. 07597:

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 96

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A310

SERVICE BULLETIN

1 Bolt NSA5041VBV3-4 Item 95

1 Nut NSA5474-3K7 Item 93

2 Bolt ABS0114-3-2 Item 37

1 Nut NSA5472-3K7 Item 124

or Pre Mod. 07597:

1 Bolt NSA5041VBV3-4 Item 95

1 Bolt NSA5041VBV3-5 Item 3

2 Nut NSA5474-3K7 Item 93

(b) Canister Drain - All Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH)

Refer to Figure 29, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (11), discard.

- the two piece retaining plate, Item (7), discard.

- four bolts, Item (13), retain.

2 At the canister drain install the one piece plate, Item 7 LH or Item 8 RH,

as applicable:

1 Plate LH A5715206420000 Item 7

or:

1 Plate RH A5715206420100 Item 8

with:

- 3 retained bolts, Item (13).

3 Nut NSA5472-4K7 Item 11

NOTE : If Service Bulletin A310-57-2053 has been embodied, increase

the bolt hole diameters in the new plate, Item 7 or Item 8, to

between 7.142-7.193mm (0.2812-0.2832in.) for the retained

second oversize bolts, Item (13).

3 Prepare the bonding area. For thew bolt through the wing skin prepare the

countersink only.

Install:

- 1 retained bolt, Item (13).

1 Washer AN960-416 Item 12

1 Nut NSA5472-4K7 Item 11

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

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A310

SERVICE BULLETIN

4 Apply a fillet of Fuel Tank Sealant Polysulfide (Mat. No. 09-001) around the

edges of the new plate, Item 7 or Item 8, to seal and over the three nuts, Item 11.

(23) Rib Bay 24-25

Kit 282142B19R02 All Aircraft

(a) MLI

Refer to Figure 19, Sheet 1, Detail A

1 At the base of the MLI, remove:

- one nut, Item (91), discard.

- one bolt, Item (90), retain.

2 At the base of the MLI prepare the bonding area. For the bolt through the wing

skin prepare the countersink only.

Install:

- 1 retained bolt, Item (90).

1 Nut NSA5474-4K7 Item 91

(24) Rib Bay 25-26

Kit 282142B19R02 All Aircraft

(a) Fuel Level Sensor

Refer to Figure 24, Sheet 1, Detail C

1 At the bracket attachment to the structure, remove:

- one nut, Item (93), discard.

- one bolt, Item (4), discard.

2 At the sensor attachment to the bracket, remove:

- one nut, Item (93), discard.

- one bolt, Item (154), discard.

3 At the bracket attachment to the structure prepare the bonding area and install:

1 Bolt NSA5041VBV3-2 Item 4

1 Nut NSA5474-3K7 Item 93

4 At the sensor attachment to the bracket prepare the bonding area and install:

1 Bolt NSA5041VBV3-3 Item 154

1 Nut NSA5474-3K7 Item 93

(25) Rib Bay 26-27

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

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Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Kit 282142B20R03 All Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH) All Aircraft

(a) Slat Track Canister 10

Refer to Figure 44, Sheet 1

1 At the canister flange (Refer to Detail C), remove:

- one nut, Item (42), discard.

- one bolt, Item (49), discard.

2 At the rib adjacent to the canister flange, remove:

- one nut, Item (42), discard.

- one bolt, Item (46), discard.

3 At the canister flange prepare the bonding area and install:

1 Lead E0088-40-100 Item 40

1 Bolt ABS0114-4-7 Item 49

1 Nut NSA5475-4K7 Item 42

4 At the rib adjacent to the canister flange prepare the bonding area and attach

the bonding lead, Item 40, with:

1 Bolt NSA5041VBV4-7 Item 46

1 Nut NSA5475-4K7 Item 42

5 Torque tighten the nuts, Item 42, to between 0.68-0.79 mdaN (60-70lbf.in.).

6 At the canister attachment bracket, remove:

- two nuts, Item (93), discard.

- one bolt, Item (95), discard.

- one bolt, Item (4), discard.

retain any packing you may find.

7 At the canister attachment bracket prepare the bonding area and install (together

with any retained packing):

1 Bolt NSA5041VBV3-4 Item 95

1 Bolt NSA5041VBV3-2 Item 4

2 Nut NSA5474-3K7 Item 93

(b) Canister Drain - All Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH)

Refer to Figure 29, Sheet 2

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 99

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A310

SERVICE BULLETIN

1 At the canister drain, remove:

- four nuts, Item (11), retain.

- the two piece retaining plate, Item (7), discard.

- four bolts, Item (13), retain.

2 At the canister drain install the one piece plate, Item 7 or Item 8, as applicable:

1 Plate LH A5715206420000 Item 7

or:

1 Plate RH A5715206420100 Item 8

with:

- 3 retained bolts, Item (13).

3 Nut NSA5472-4K7 Item 11

NOTE : If Service Bulletin A310-57-2053 has been embodied, increase

the bolt hole diameters in the new plate, Item 7 or Item 8, to

between 7.142-7.193mm (0.2812-0.2832in.) for the retained

second oversize bolts, Item (13).

3 Prepare the bonding area. For the bolt through the wing skin prepare the

countersink only.

Install:

- 1 retained bolt, Item (13).

1 Washer AN960-416 Item 12

1 Nut NSA5472-4K7 Item 11

4 Apply a fillet of Fuel Tank Sealant Polysulfide (Mat. No. 09-001) around the

edges of the new plate, Item 7 or Item 8, to seal and over the three nuts, Item 11.

(26) Rib Bay 27-28

Kit 282142B21R04 All Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH) All Aircraft

(a) Screwjack Canister 6

Kit 282142B21R04

Refer to Figure 45, Sheet 1

1 At the canister flange (Refer to Detail C), remove:

- one nut, Item (42), discard.

- one bolt, Item (50), discard.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 100

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A310

SERVICE BULLETIN

2 At the rib adjacent to the canister flange, remove:

- one nut, Item (42), discard.

- one bolt, Item (43), discard.

3 At the canister flange prepare the bonding area and install:

1 Lead E0088-40-100 Item 40

1 Bolt ABS0114-4-5 Item 50

1 Nut NSA5475-4K7 Item 42

4 At the rib adjacent to the canister flange prepare the bonding area and attach

the bonding lead, Item 40, with:

1 Bolt NSA5041VBV4-5 Item 43

1 Nut NSA5475-4K7 Item 42

5 Torque tighten the nuts, Item 42, to between 0.68-0.79 mdaN (60-70lbf.in.).

6 At the canister support bracket attachment (Refer to Detail A) drill out one rivet

and increase the diameter of the hole to 4.826-4.877mm (0.190-0.192in.)

to allow for the installation of a bolt.

7 At the canister support bracket attachments, remove:

- one bolt, Item (37), discard.

- one nut, Item (36), discard.

- one bolt, Item (154), discard.

- one nut, Item (93), discard.

8 At the hole that you have drilled in the support bracket prepare the bonding

area and install:

1 Bolt NAS1303-3 Item 153

1 Nut NSA5472-3K7 Item 124

9 At the canister support bracket attachments prepare the bonding areas and

install:

1 Washer AN960-10L Item 36

1 Bolt ABS0114-3-2 Item 37

1 Bolt NSA5041VBV3-3 Item 154

1 Nut NSA5474-3K7 Item 93

(b) Canister Drain - All Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH)

Refer to Figure 32, Sheet 2

1 At the canister drain, remove:

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

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A310

SERVICE BULLETIN

- four nuts, Item (11), discard.

- the two piece retaining plate, Item (7), discard.

- four bolts, Item (13), retain.

2 At the canister drain install the one piece plate, Item 7 LH or Item 8 RH,

as applicable:

1 Plate LH A5715206420000 Item 7

or:

1 Plate RH A5715206420100 Item 8

with:

- 3 retained bolts, Item (13).

3 Nut NSA5472-4K7 Item 11

NOTE : If Service Bulletin A310-57-2053 has been embodied, increase

the bolt hole diameters in the new plate, Item 7 or Item 8, to

between 7.142-7.193mm (0.2812-0.2832in.) for the retained

second oversize bolts, Item (13).

3 Prepare the bonding area. For the bolt through the wing skin prepare the

countersink only.

Install:

- 1 retained bolt, Item (13).

1 Washer AN960-416 Item 12

1 Nut NSA5472-4K7 Item 11

4 Apply a fillet of Fuel Tank Sealant Polysulfide (Mat. No. 09-001) around the

edges of the new plate, Item 7 or Item 8, to seal and over the three nuts, Item 11.

(c) MLI

Kit 282142B21R04 All Aircraft

Refer to Figure 19, Sheet 1, Detail A

1 At the MLI that is installed on the manhole cover 550/650PB, remove from the

support tube:

- six nuts, Item (93), discard.

- four bolts, Item (4), retain.

- two bolts, Item (4), discard.

retain the tube.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

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A310

SERVICE BULLETIN

2 On the base of the MLI, remove:

- one nut, Item (91), discard.

- one bolt, Item (90), retain.

3 On the base of the MLI prepare the bonding area. For the bolt through the wing

skin prepare the countersink only.

Install:

- one retained bolt, Item (90).

1 Nut NSA5474-4K7 Item 91

4 Prepare the bonding area and put the retained support tube over the MLI

and install:

2 Bolt NSA5041VBV3-2 Item 4

2 Nut NSA5474-3K7 Item 93

and:

- 4 retained bolts, Item (4).

4 Nut NSA5474-3K7 Item 93

(d) Config. 07 Overwing Refuel Caps

Refer to Figure 36, Sheet 1, View B

1 Remove the overwing refuel adaptor (Refer to AMM 28-11-28, Page block 401).

2 Put protective material or masking tape on the top surface of the wing skin,

around the overwing refuel adaptor hole.

3 Clean the contact surfaces of the overwing refuel adaptor and the wing skin

opening with Cleaning agent (Mat. No. 11-026).

4 Apply Alodine (Mat. No. 13-002) to the overwing refuel adaptor.

5 Apply low adhesive Sealant (Mat. No. 09-018) to the interface of the adaptor

and the wing surface and also on the threads of the adaptor. Do not use Mat No.

09-001 as listed in AMM 28-11-28, Page block 401).

6 Install the overwing refuel adaptor (Refer to AMM 28-11-28, Page block 401).

7 Remove any unwanted sealant.

8 Remove the protective material that you put around the opening.

(e) Config. 05 Overwing Refuel Caps

Refer to Figure 36, Sheet 3, View E and Sheet 5, View G

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 103

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A310

SERVICE BULLETIN

1 Do a resistance check between the flange face of the refuel insert and the wing.

If the resistance is <10mohm, no further action is necessary. If the resistance is

>10mohm then do the steps that follow.

2 Remove from the refuel adaptor the items that follow:

1 Nut NSA5470-4K7 Item (169) Discard

1 Bolt-Hi Lok NSA5476BV4-9 Item (576) Retain

3 Prepare for electrical bonding.

4 Install:

1 Bolt-Hi Lok NSA5476BV4-9 Item (576) Retained

1 Nut NSA5470-4K7 Item 169

5 Over seal the nut, Item 169.

6 Do a bonding check and make sure the resistance is <10mohm.

(f) Config. 06 Overwing Refuel Caps

Refer to Figure 36, Sheet 3, View E and Sheet 5 View G

1 Do a resistance check between the flange face of the refuel insert and the wing.

If the resistance is <10mohm, no further action is necessary. If the resistance is

>10mohm then do the steps that follow:

2 Remove from the refuel adaptor the items that follow:

1 Nut NSA5470-4K7 Item (169) Discard

1 Screw NAS1154V16P Item (577) Retain

3 Prepare for electrical bonding.

4 Install:

1 Screw NAS1154V16P Item (577) Retained

1 Nut NSA5470-4K7 Item 169

5 Over seal the nut, Item 169.

6 Do a bonding check and make sure the resistance is <10mohm.

(27) Rib Bay 28-29

Kit 282142B22R03 All Aircraft

(a) Fuel Overflow Sensor

Refer to Figure 24, Sheet 2, Detail E

1 At the flange of the overflow sensor, remove:

- one bolt, Item (160), discard.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

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A310

SERVICE BULLETIN

2 At the flange of the overflow sensor prepare the bonding area and install:

1 Bolt NAS6403-5 Item 160

(b) Water Drain Valve

Refer to Figure 25, Sheet 1, Detail B

1 At the water drain valve attachment to the structure, remove:

- one nut, Item (91), discard.

- one bolt, Item (73), retain.

2 At the base of the water drain valve attachment to the structure prepare the

bonding area. For the bolt through the wing skin prepare the countersink only.

Install:

- 1 retained bolt, Item (73).

1 Nut NSA5474-4K7 Item 91

(c) Overpressure Protector

Refer to Figure 35, Sheet 2

1 At the flange of the overpressure protector, remove:

- two nuts, Item (91), discard.

- two bolts, item (162), discard.

2 At the flange of the overpressure protector prepare the bonding area. For the

bolt through the wing skin prepare the countersink only.

Install:

2 Bolt NAS1154-12 Item 162

2 Nut NSA5470-4K7 Item 169

(28) Rib Bay 29-30

Kit 282142B18R04 All Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH) All Aircraft

(a) Slat Track Canister 11

Kit 282142B18R04

Refer to Figure 46, Sheet 1

NOTE : Worksteps 1 thru 3 are not necessary on some aircraft because anchor

nuts are installed on the canister flange and the drain is welded to

the canister.

1 At the canister flange, remove:

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

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A310

SERVICE BULLETIN

- one nut, Item (42), discard.

- one bolt, Item (31), discard.

2 At the canister flange prepare the bonding area and install:

1 Lead E0088-40-250 Item 163

1 Bolt ABS0114-4-4 Item 31

1 Nut NSA5475-4K7 Item 42

3 Torque tighten the bonding lead nut, Item 42, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

4 At the canister attachment bracket, remove:

- one bolt, Item (3), discard.

- one nut, Item (93), discard.

- one bolt, Item (29), discard.

retain any packing you may find

At the canister attachment bracket, prepare the bonding area and install

(together with any retained packing):

1 Bolt NSA5041VBV3-5 Item 3

1 Nut NSA5474-3K7 Item 93

1 Bolt ABS0114-3-3 Item 29

NOTE : The attachment of the bonding lead, Item 163, to the canister drain is done in

the worksteps that follow.

(b) Canister Drain - All Aircraft

Kit 282142B02R02 (LH) or Kit 282142B26R01 (RH)

Refer to Figure 29, Sheet 2

1 At the canister drain (Refer to Figure 29, Sheet 2), remove:

- four nuts, Item (11), discard.

- the two piece retaining plate, Item (7), discard.

- four bolts, Item (13), retain.

2 At the canister drain install the one piece plate Item 7 LH or Item 8 RH, as

applicable:

1 Plate LH A5715206420000 Item 7

or:

1 Plate RH A5715206420100 Item 8

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 106

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A310

SERVICE BULLETIN

with:

- 3 retained bolts, Item (13).

3 Nut NSA5472-4K7 Item 11

NOTE : If Service Bulletin A310-57-2053 has been embodied, increase

the bolt hole diameters in the new plate, Item 7 or Item 8, to

between 7.142-7.193mm (0.2812-0.2832in.) for the retained

second oversize bolts, Item (13).

3 At the canister drain prepare the bonding area. For the bolt through the wing

skin prepare the countersink only.

Install:

- the other end of bonding lead, Item 163.

- 1 retained bolt, Item (13).

1 Washer AN960-416 Item 12

1 Nut NSA5472-4K7 Item 11

4 Apply a fillet of Fuel Tank Sealant Polysulfide (Mat. No. 09-001) around the edge

of the new plate, Item 7 or Item 8, to seal and over the three nuts, Item 11.

(29) ADDITIONAL WORK (Introduced at revision 01)

Rib Bay 29-30

Kit 282142B29R00

NOTE : If this Service Bulletin has been accomplished before revision 01, it is

necessary to do the additional work. Aircraft modified per revision 01 or later

revisions are not affected by the additional work described in this paragraph.

NOTE : The worksteps that follow are applicable to the LH and RH wings.

(a) Preparation

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

Page block 301).

WARNING : MAKE SURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR

OF THE TRAVEL RANGES OF THE SLATS/FLAPS.

2 Put access platforms in position as required.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

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A310

SERVICE BULLETIN

3 Defuel and ventilate the wing outer fuel tanks (Refer to AMM 28-25-00, Page

block 301 and AMM 28-10-00, Page block 301).

4 Remove wing manhole covers 560BB (660BB) (Refer to AMM 28-11-22, Page

block 401).

5 Make sure that the circuit breakers of all systems that you will work on are open,

in safety and tagged and warning notices are in position.

6 For the wings access panels/doors (Refer to AMM 06-41-57).

(b) Modification

Refer to Figure 46, Sheet 1

1 At the canister attachment bracket, remove:

- one bolt, Item (3), discard.

- one nut, Item (93), discard.

- one bolt, Item (29), discard.

retain any packing you may find

At the canister attachment bracket, prepare the bonding area and install

(together with any retained packing):

1 Bolt NSA5041VBV3-5 Item 3

1 Nut NSA5474-3K7 Item 93

1 Bolt ABS0114-3-3 Item 29

(c) Close up

1 Make sure that the work areas are clean and clear of tools and other items

of equipment.

2 Install the wings manhole covers and access panels (Refer to AMM 28-11-22,

Page block 301 and AMM 06-41-57).

3 Do a leak test of the fuel tanks (Refer to AMM 28-11-00, Page block 501).

NOTE : Leaks are not permitted.

4 Remove all access platforms.

5 Put the aircraft and the systems in a normal operating condition.

(30) Config. 05 ADDITIONAL WORK (For operators who have accomplished any previous

revision of this Service Bulletin).

Refer to Figure 36, Sheet 2 thru Sheet 5

NOTE : The worksteps that follow are applicable to the LH and RH wings.

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 108

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A310

SERVICE BULLETIN

(a) Preparation

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

Page block 301).

2 Put access platforms in position as necessary.

3 Defuel and vent the inner and outer wing fuel tanks (Refer to AMM 28-25-00,

Page block 301 and AMM 28-10-00, Page block 301).

NOTE : Only necessary if the resistance values are not achieved.

4 Remove additional manhole covers as necessary (Refer to AMM 28-11-22,

Page block 401).

NOTE : Only necessary if the resistance values are not achieved.

(b) Modification

1 Do a resistance check between the flange face of the refuel insert and the wing.

If the resistance is <10mohm, no further action is necessary, replace the filler

cap. If the resistance is >10mohm then do the steps that follow:

2 Remove wing manhole covers 540HB and (640HB) at rib bay 13-14 and 550PB

and (650PB) at rib bay 27-28 (Refer to AMM 28-11-22, Page block 401).

3

NOTE : At the inboard location remove the items that follow:

1 Nut NSA5470-4K7 Item (169) Discard

1 Bolt-Hi Lok,Csk Head NSA5476BV4-18 Item (575) Retain

4 At the outboard location remove the items that follow:

1 Nut NSA5470-4K7 Item (169) Discard

1 Bolt-Hi Lok NSA5476BV4-9 Item (576) Retain

5 Prepare for electrical bonding.

6 At the inboard location install:

1 Bolt-Hi Lok,Csk Head NSA5476BV4-18 Item (575) Retained

1 Nut NSA5470-4K7 Item 169

NOTE : The Nut, Item 169 will be from the operators own stock.

7 Over seal the nut, Item 169.

8 At the outboard location install:

1 Bolt-Hi Lok NSA5476BV4-9 Item (576) Retained

1 Nut NSA5470-4K7 Item 169

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 109

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A310

SERVICE BULLETIN

NOTE : The Nut, Item 169 will be from the operators own stock.

9 Over seal the nut, Item 169.

10 Do a bonding check and make sure that the resistance is <10mohm.

(c) Close up

1 Make sure that the work areas are clean and clear of tools and other items

of equipment.

2 Install the wings manhole covers 540HB and (640HB) at rib bay 13-14 and

550PB and (650PB) at rib bay 27-28 (Refer to AMM 28-11-22, Page block 401).

NOTE : Only necessary if the resistance values are not achieved.

3 Remove all access platforms.

4 Refuel the fuel tanks (Refer to AMM 28-25-00, Page block 301).

NOTE : Only necessary if the resistance values are not achieved.

5 Do a leak test of the fuel tanks (Refer to AMM 28-11-00, Page block 501).

NOTE : Leaks are not permitted.

NOTE : Only necessary if the resistance values are not achieved.

6 Put the aircraft and the systems in a normal operating condition.

(31) Config. 06 ADDITIONAL WORK (Introduced by revision 03) (For operators who have

accomplished any previous revision of this Service Bulletin).

Refer to Figure 36, Sheet 1 View A, Sheet 3 and Sheet 5

NOTE : The worksteps that follow are applicable to the LH and RH wings.

(a) Preparation

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

Page block 301).

2 Put access platforms in position as necessary.

3 Defuel and vent the outer wing fuel tanks (Refer AMM 28-10-00, Page block 301).

NOTE : Only necessary if the resistance values are not achieved.

4 Remove additional manhole covers as necessary (Refer to AMM 28-11-22,

Page block 401).

NOTE : Only necessary if the resistance values are not achieved.

(b) Modification

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 110

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

1 Do a resistance check between the flange face of the refuel insert and the wing.

If the resistance is <10mohm, no further action is necessary, replace the filler

cap. If the resistance is >10mohm then do the steps that follow:

2 Remove wing manhole covers 540HB and (640HB) at rib bay 27-28 (Refer

to AMM 28-11-22, Page block 401).

3 At the outboard location remove the items that follow:

1 Nut NSA5470-4K7 Item (169) Discard

1 Screw NAS1154V7P Item (578) Retain

4 Prepare for electrical bonding.

5 At the outboard location install:

1 Screw NAS1154V7P Item (578) Retained

1 Nut NSA5470-4K7 Item 169

NOTE : The Nut, Item 169 will be from the operators own stock.

6 Over seal the nut, Item 169.

7 Do a bonding check and make sure that the resistance is <10mohm.

(c) Close up

1 Make sure that the work areas are clean and clear of tools and other items

of equipment.

2 Install the wings manhole covers 550PB and (650PB) at rib bay 27-28 (Refer

to AMM 28-11-22, Page block 401).

NOTE : Only necessary if the resistance values are not achieved.

3 Remove all access platforms.

4 Refuel the fuel tanks (Refer to AMM 28-25-00, Page block 301).

NOTE : Only necessary if the resistance values are not achieved.

5 Do a leak test of the fuel tanks (Refer to AMM 28-11-00, Page block 501).

NOTE : Leaks are not permitted.

NOTE : Only necessary if the resistance values are not achieved.

6 Put the aircraft and the systems in a normal operating condition.

C. TEST

(1) Wings Fuel tanks

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 111

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

(a) Make sure that all the work areas and the fuel tanks are clean and clear of tools

and other items of equipment.

(b) Install the heat shields (Refer to AMM 57-23-11, Page block 401).

(c) Install the wings manhole covers and access panels (Refer to AMM 28-11-22,

Page block 301 and AMM 06-41-57).

(d) Refuel the fuel tanks (Refer to AMM 28-25-00, Page block 301).

(e) Do a leak test of the fuel tanks (Refer to AMM 28-11-00, Page block 501).

NOTE : Leaks are not permitted.

(2) Center Fuel Tank

(a) Preparation

1 Make sure that the work areas are clean and clear of tools and other items

of equipment.

2 Close the access doors 147AZ and 148AZ (Refer to AMM 28-11-29, Page

block 401)

(b) Test

1 Do the test after the removal/installation of the access doors 147AZ and 148AZ

(Refer to AMM 28-11-29, Page block 401).

D. CLOSE UP

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

(2) Remove all access platforms.

(3) 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 : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 112

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 1, Sheet 1

Decomposition of the Center Tank DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 113

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 1

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 114

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 2

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 115

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 3

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 116

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 4

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 117

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 5

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 118

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 6

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 119

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 7

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 120

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 8

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 121

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 9

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 122

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 10

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 123

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 11

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 124

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 12

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 125

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 13

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 126

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 14

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 127

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 15

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 128

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 16

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 129

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 17

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 130

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 2, Sheet 18

Location of the Bonding Points at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 131

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 3, Sheet 1

Bonding Points to Check at FR47

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 132

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 4, Sheet 1

Location of the Bonding Points on the Rib 1 (LH side)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 133

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 4, Sheet 2

Location of the Bonding Points on the Rib 1 (LH side)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 134

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 4, Sheet 3

Location of the Bonding Points on the Rib 1 (LH side)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 135

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 4, Sheet 4

Location of the Bonding Points on the Rib 1 (LH side)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 136

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 4, Sheet 5

Location of the Bonding Points on the Rib 1 (LH side)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 137

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 5, Sheet 1

Bonding Points to Check at the Rib 1 (LH side)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 138

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 6, Sheet 1

Location of the Bonding Points on the Intrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 139

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 6, Sheet 2

Location of the Bonding Points on the Intrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 140

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 6, Sheet 3

Location of the Bonding Points on the Intrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 141

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 6, Sheet 4

Location of the Bonding Points on the Intrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 142

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 6, Sheet 5

Location of the Bonding Points on the Intrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 143

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 6, Sheet 6

Location of the Bonding Points on the Intrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 144

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 6, Sheet 7

Location of the Bonding Points on the Intrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 145

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 6, Sheet 8

Location of the Bonding Points on the Intrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 146

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 6, Sheet 9

Location of the Bonding Points on the Intrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 147

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 6, Sheet 10

Location of the Bonding Points on the Intrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 148

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 6, Sheet 11

Location of the Bonding Points on the Intrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 149

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 7, Sheet 1

Bonding Points to Check at the Intrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 150

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 8, Sheet 1

Location of the Bonding Points on the Rib 1 (RH side)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 151

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 8, Sheet 2

Location of the Bonding Points on the Rib 1 (RH side)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 152

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 8, Sheet 3

Location of the Bonding Points on the Rib 1 (RH side)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 153

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 8, Sheet 4

Location of the Bonding Points on the Rib 1 (RH side)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 154

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 8, Sheet 5

Location of the Bonding Points on the Rib 1 (RH side)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 155

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 8, Sheet 6

Location of the Bonding Points on the Rib 1 (RH side)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 156

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 9, Sheet 1

Bonding Points to Check at the Rib 1 (RH side)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 157

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 10, Sheet 1

Location of the Bonding Points on the Extrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 158

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 10, Sheet 2

Location of the Bonding Points on the Extrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 159

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 10, Sheet 3

Location of the Bonding Points on the Extrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 160

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 10, Sheet 4

Location of the Bonding Points on the Extrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 161

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 10, Sheet 5

Location of the Bonding Points on the Extrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 162

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 10, Sheet 6

Location of the Bonding Points on the Extrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 163

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 10, Sheet 7

Location of the Bonding Points on the Extrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 164

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 10, Sheet 8

Location of the Bonding Points on the Extrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 165

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 10, Sheet 9

Location of the Bonding Points on the Extrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 166

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 10, Sheet 10

Location of the Bonding Points on the Extrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 167

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 11, Sheet 1

Bonding Points to Check at the Extrados Panel

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 168

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 12, Sheet 1

Modification of the Feed Pipes (Kit 282142A01R05)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 169

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 12, Sheet 2

Modification of the Feed Pipes (Kit 282142A01R05)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 170

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 13, Sheet 1

Modification of Water Scavenge Pipes (Kit 282142A01R05)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 171

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 13, Sheet 2

Modification of Water Scavenge Pipes (Kit 282142A01R05)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 172

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 13, Sheet 3

Modification of Water Scavenge Pipes (Kit 282142A01R05)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 173

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 13, Sheet 4

Modification of Water Scavenge Pipes (Kit 282142A01R05)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 174

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 13, Sheet 5

Modification of Water Scavenge Pipes (Kit 282142A01R05)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 175

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 13, Sheet 6

Modification of Water Scavenge Pipes (Kit 282142A01R05)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 176

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 14, Sheet 1

Modification of Water Drain Pipes (Kit 282142A01R05)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 177

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 14, Sheet 2

Modification of Water Drain Pipes (Kit 282142A01R05)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 178

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 15, Sheet 1

Modification of the TTS Pipes (Kit 282142A02R02)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 179

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 15, Sheet 2

Modification of the TTS Pipes (Kit 282142A02R02)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 180

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 15, Sheet 3

Modification of the TTS Pipes (Kit 282142A02R02)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 181

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 15, Sheet 4

Modification of the TTS Pipes (Kit 282142A02R02)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 182

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 15, Sheet 5

Modification of the TTS Pipes (Kit 282142A02R02)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 183

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 16, Sheet 1

Modification of the Cross Feed Pipe (Kit 282142A03R02)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 184

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 16, Sheet 2

Modification of the Cross Feed Pipe (Kit 282142A03R02)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 185

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 17, Sheet 1

Modification of the Cross Feed Pipe (Kit 282142A04R00)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 186

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 17, Sheet 2

Modification of the Cross Feed Pipe (Kit 282142A04R00)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 187

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 18, Sheet 1

Wings - Fuel Feed Pipe - Support Bracket

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 188

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 19, Sheet 1

Magnetic Level Indicators (MLI)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 189

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 19, Sheet 2

Magnetic Level Indicators (MLI)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 190

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 20, Sheet 1

Inner Tank - Fuel Pressure Switches

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 191

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 21, Sheet 1

Fuel Booster Pumps Canisters

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 192

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 21, Sheet 2

Fuel Booster Pumps Canisters

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 193

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 22, Sheet 1

Fuel Booster Pump Canister - Drain Valve Pipe (Config 02 Aircraft)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 194

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 23, Sheet 1

Fuel Gallery - Fuel Drain Valves (Config.02 Aircraft)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 195

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 23, Sheet 2

Fuel Gallery - Fuel Drain Valves (Config.02 Aircraft)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 196

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 24, Sheet 1

Fuel Level Sensors

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 197

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A310

SERVICE BULLETIN

Figure 24, Sheet 2

Fuel Level Sensors

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 198

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 24, Sheet 3

Fuel Level Sensors

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 199

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A310

SERVICE BULLETIN

Figure 25, Sheet 1

Water Drain Valves and Water Drains

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 200

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 26, Sheet 1

Water Scavenge System (Config. 04 Aircraft)

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 201

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 27, Sheet 1

Slat Track Canister 1

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 202

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 28, Sheet 1

Fuel Diffusers - Inner Tank

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 203

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 28, Sheet 2

Fuel Diffusers - Inner Tank

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 204

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 29, Sheet 1

Slat Track Canister 2 and Typical Canisters Drain Bonding

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 205

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 29, Sheet 2

Slat Track Canister 2 and Typical Canisters Drain Bonding

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 206

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 30, Sheet 1

Slat Track Canister 3

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 207

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 31, Sheet 1

Slat Track Canister 4

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 208

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 32, Sheet 1

Screwjack Canister 3 and Typical Canisters Drain Bonding

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 209

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 32, Sheet 2

Screwjack Canister 3 and Typical Canisters Drain Bonding

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 210

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 33, Sheet 1

Cadensicon and Refuel/Defuel Valve - RH Wing only

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 211

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 33, Sheet 2

Cadensicon and Refuel/Defuel Valve - RH Wing only

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 212

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 34, Sheet 1

Slat Track Canister 5

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 213

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 35, Sheet 1

Overpressure Protector

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 214

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A310

SERVICE BULLETIN

Figure 35, Sheet 2

Overpressure Protector

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 215

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A310

SERVICE BULLETIN

Figure 36, Sheet 1

Overwing Refueling Cap

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 216

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A310

SERVICE BULLETIN

Figure 36, Sheet 2

Overwing Refueling Cap

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 217

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A310

SERVICE BULLETIN

Figure 36, Sheet 3

Overwing Refueling Cap

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 218

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A310

SERVICE BULLETIN

Figure 36, Sheet 4

Overwing Refueling Cap

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 219

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 36, Sheet 5

Overwing Refueling Cap

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 220

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 37, Sheet 1

Slat Track Canister 6

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 221

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 38, Sheet 1

Fuel Pressure Switches - Outer Tank

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 222

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A310

SERVICE BULLETIN

Figure 38, Sheet 2

Fuel Pressure Switches - Outer Tank

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 223

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 39, Sheet 1

Screwjack Canister 4

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 224

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 40, Sheet 1

Slat Track Canister 7

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 225

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 41, Sheet 1

Screwjack Canister 5

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 226

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 42, Sheet 1

Slat Track Canister 8

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 227

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 43, Sheet 1

Slat Track Canister 9

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 228

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 44, Sheet 1

Slat Track Canister 10

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 229

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 45, Sheet 1

Screwjack Canister 6

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 230

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

Figure 46, Sheet 1

Slat Track Canister 11

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 231

Printed in France © AIRBUS 2008 All rights reserved
A310

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 232

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A310

SERVICE BULLETIN

REPORTING SHEET

TITLE : FUEL - GENERAL - MODIFY THE EQUIPMENT IN THE FUEL TANKS FOR ADDITIONAL

ELECTRICAL BONDING

MODIFICATION No. : 12256H5502, 13495H5721

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 : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 1 of 1

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A310

SERVICE BULLETIN

REPORTING QUALITY

TITLE : FUEL - GENERAL - MODIFY THE EQUIPMENT IN THE FUEL TANKS FOR ADDITIONAL

ELECTRICAL BONDING

MODIFICATION No. : 12256H5502, 13495H5721

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 : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

REVISION No. : 04 - Nov 30/10 Page : 1 of 1

Printed in France © AIRBUS 2008 All rights reserved