# 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** M A N DA TO RY M A N DA TO RY M A N DA TO RY M A N DA TO RY **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 A D D I T I O N A L WO R K 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. R E AS O N 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. C H A N G E S 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

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# 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

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# A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

. Figure 6, Sheet 6 updated. - Figure 19

. Item numbers have been updated. F I L I N G I N ST R U CT I O N S 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. H I STO RY O F P R E V I O U S R E V I S I O N S 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. R E V I S I O N S E Q U E N C E 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 M A N DA TO RY M A N DA TO RY M A N DA TO RY M A N DA TO RY **ATA SYSTEM : 28 TITLE : FUEL - GENERAL - MODIFY THE EQUIPMENT IN THE FUEL TANKS FOR ADDITIONAL**  **ELECTRICAL BONDING MODIFICATION No. :**  12256H5502, 13495H5721 R E AS O N/D E S C R I PT I O N/O P E RA T I O N A L C O N S E Q U E N C E S 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

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# 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. **E F**  **F E**  **C T** **I V**  **I T** **Y** 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. C O N C U R R E N T R E Q U I R E M E N TS None R E F E R E N C E S/ R E P E R C U S S I O N S 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

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# A310 SERVICE BULLETIN SUMMARY

OTHERS : None N A T U R E O F T H E WO R K AIRCRAFT : Yes EQUIPMENT : No HARD : No SOFT : No OBRM : No M A N P OW E R 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

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# 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**  M A T E R I A L I N FO R M A T I O N 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. A P P E N D I C E S 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** M A N DA TO RY M A N DA TO RY M A N DA TO RY M A N DA TO RY **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. P L** **A N**  **N I**  **N G**  **I N**  **F O**  **R M**  **A T** **I O**  **N A. E**  **F F**  **E C** **T I**  **V I**  **T Y**  (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

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# 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

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# 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

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# 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

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# 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

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# 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

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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

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# 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

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# 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. C O**  **N C**  **U R**  **R E**  **N T**  **R E**  **Q U**  **I R**  **E M**  **E N**  **T S**  None **C. R E** **A S**  **O N**  (1) History DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

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# 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. D E**  **S C**  **R I**  **P T** **I O**  **N** 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

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# 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. C O**  **M P**  **L I**  **A N**  **C E**  (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. A P**  **P R** **O V**  **A L**  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. M A**  **N P**  **O W**  **E R**  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

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# 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. W E**  **I G**  **H T**  **A N**  **D B** **A L** **A N**  **C E**  Not changed **I. E L**  **E C** **T R**  **I C** **A L**  **L O** **A D**  **D A**  **T**

**A** Not changed **J. R E**  **F E**  **R E**  **N C**  **E S**  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

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# 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. P U**  **B L**  **I C** **A T** **I O**  **N S**  **A F**  **F E**  **C T**  **E D**  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. I N**  **T E**  **R C**  **H A**  **N G**  **E A**  **B I**  **L I**  **T Y**  **/ M**  **I X** **A B**  **I L**  **I T** **Y** None

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

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# A310 SERVICE BULLETIN

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

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# A310 SERVICE BULLETIN

**2. M A**  **T E**  **R I**  **A L**  **I N**  **F O**  **R M**  **A T** **I O**  **N A. M**  **A T**  **E R**  **I A**  **L -**  **P R**  **I C**  **E A**  **N D**  **A V** 

**A I**  **L A**  **B I**  **L I**  **T Y**  (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

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# 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

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# 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

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# 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

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# 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

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# 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. I N**  **D U**  **S T**  **R Y**  **S U**  **P P**  **O R** **T I**  **N F**  **O R**  **M A**  **T I**  **O N**  AIRBUS will not provide industry support for accomplishment of this Service Bulletin. **C. L I**  **S T**  **O F**  **C O**  **M P**  **O N**  **E N**  **T S**  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

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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

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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

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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

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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

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# 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

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# 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

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# 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

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# 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. L I**  **S T**  **O F**  **M A**  **T E**  **R I**  **A L** **S -**  **O P**  **E R** **A T** **O R**  **S U**  **P P**  **L I**  **E D**  (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

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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. P A**  **R T** **S T** **O B**  **E R**  **E -**  **I D**  **E N**  **T I**  **F I**  **E D**  **B Y**  **T H**  **E O**  **P E**  **R A**  **T O**  **R** None **F. T O**  **O L**  **I N**  **G -**  **P R**  **I C**  **E A**  **N D**  **A V** 

**A I**  **L A**  **B I**  **L I**  **T Y**  None DATE : Aug 26/05 SERVICE BULLETIN No. : A310-28-2142

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# A310 SERVICE BULLETIN

**G. S P**  **E C**  **I A**  **L T** **O O**  **L S**  None

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

REVISION No. : 04 - Nov 30/10 Page : 40 Printed in France © AIRBUS 2008 All rights reserved

# A310 SERVICE BULLETIN

**3. A C**  **C O**  **M P**  **L I**  **S H**  **M E**  **N T**  **I N**  **S T**  **R U**  **C T**  **I O**  **N S**  **A. G E**  **N E**  **R A**  **L** 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

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# A310 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

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# A310 SERVICE BULLETIN

**B. M O**  **D I**  **F I**  **C A**  **T I**  **O N**  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

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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

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# A310 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

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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

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# 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

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# 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 1 0 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 1 1 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

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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 1 2 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 1 3 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 1 4 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

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# 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 1 5 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 1 6 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

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# 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 1 7 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

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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 1 8 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

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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

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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

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# 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

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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

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# 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

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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

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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

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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

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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

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# 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

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# 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

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# 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

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# 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

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# 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

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# 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

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# 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

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# 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

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# 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

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# 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

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# 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

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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, 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

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# 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

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# 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

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# 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

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# 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

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# 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

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# 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

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# 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

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# 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. 1 0 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. 1 1 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

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# 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

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# 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

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# 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

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# 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

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# 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

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# 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 1 0 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

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# 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

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# 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

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# 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

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# 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

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# 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

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# 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

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# 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

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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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# 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

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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

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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

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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

REVISION No. : 04 - Nov 30/10 Page : 104 Printed in France © AIRBUS 2008 All rights reserved

# 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

REVISION No. : 04 - Nov 30/10 Page : 105 Printed in France © AIRBUS 2008 All rights reserved

# 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 Printed in France © AIRBUS 2008 All rights reserved

# 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

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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

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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. 1 0 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. T E**  **S T**  (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. C L**  **O S**  **E U**  **P** (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. D O**  **C U**  **M E**  **N T**  **A**

**T I**  **O N**  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 Printed in France © AIRBUS 2008 All rights reserved

# 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 Printed in France © AIRBUS 2008 All rights reserved

# 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 Printed in France © AIRBUS 2008 All rights reserved

# 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 Printed in France © AIRBUS 2008 All rights reserved

# 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 Printed in France © AIRBUS 2008 All rights reserved

# 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 Printed in France © AIRBUS 2008 All rights reserved

# 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 Printed in France © AIRBUS 2008 All rights reserved

# 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 Printed in France © AIRBUS 2008 All rights reserved

# 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 Printed in France © AIRBUS 2008 All rights reserved

# A310 SERVICE BULLETIN REPORTING SHEET

**TITLE : FUEL - GENERAL - MODIFY THE EQUIPMENT IN THE FUEL TANKS FOR ADDITIONAL ELECTRICAL BONDING**  **MODIFICATION No. :** 12256H5502, 13495H5721 P l e as e co m p l ete t h e a p p ro p r i ate i te m (A o r B ) : A - SB W I L L B E 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 H AS B E E N embodied on aircraft: ............................................................................................................

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

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

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

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

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

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

...................................... Signature:..................... Date: ..................................................... I f o p e rat i o n a l d o c u m e n tat i o n i s affe cte d (s e e Pa rag ra p h 1

. K of t h i s S B ) : 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 I m p o rta n t I n fo r m at i o n : 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. P l e as e ret u r n t h i s co m p l ete d s h e et 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 Printed in France © AIRBUS 2008 All rights reserved

# 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 C o m m e n ts :

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