# @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. 

# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 28 

### TITLE: FUEL SYSTEM - INTRODUCE GROUND FAULT INTERRUPTER (GFI) **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR 13382H5685 MINOR None NOTE: 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. REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES The European Aviation Safety Agency (EASA) has requested that Ground Fault Interrupters (GFI) are installed into the electrical supply circuits of A300-600/600R and A310-200/300 fuel pumps where inlets become uncovered during normal operation. This is in response to SFAR88 - Fuel Tank Safety. This Service Bulletin introduces Ground Fault Interrupters (GFI) and related bases into the electrical supply circuits of the A310-200/300 aircraft, inner center and trim (where fitted) tank pumps. These GFIs have the same ’footprint’ as the existing relay/micro-contactors and physically replace them on the electrical panel. For aircraft that have already installed a GFI in the RH Inner Tank Pump 2 circuit via Service Bulletin A310-28-2172 this Service Bulletin installs GFIs at the remaining required positions. The new GFI sockets are fool-proofed to prevent incorrectly installing normal relay/micro-contactors. These GFIs will replace the existing 3-phase relay/micro-contactors. The function of the GFI is to electrically isolate the pump if a ground fault condition occurs downstream of the GFI. The GFI gives additional earth leakage protection to the downstream circuit. Accomplishment of this Service Bulletin will not change the characteristics of the aircraft.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 1 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN SUMMARY GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD NO 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 NOTE (1): Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 282170A01R00 1 13,310.00 GFI, contacts **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 282170A01R00 1 13,310.00 GFI, contacts **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 282170A01R00 1 13,310.00 GFI, contacts **CONF 004 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 282170A02R00 1 17,680.00 GFI, contacts **CONF 005 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 282170A02R00 1 17,680.00 GFI, contacts

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 2 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN SUMMARY **CONF 006 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 282170A03R00 1 15,450.00 GFI, contacts EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

18T 19U 46T 52X 58X 82Z 83V 85W 85Z 99Y AFG AIB AIC AMV BAF BBC C9L CFC DAH DGA F2I FDX G2X G8E GAF HFY IRA IRM IYE JAB JAV K1P KAC KZU MGL PCA PIA QAF R1T RJA ROT RZO SBI SGX THY TSC UBD UZB WHT WTJ CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 282170-831-895-001: MODIFICATION TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 3 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN SUMMARY **CONF 002 Task 282170-831-895-001: MODIFICATION TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 003 Task 282170-831-895-001: MODIFICATION TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 004 Task 282170-831-895-001: MODIFICATION TOTAL MANHOURS 5.50 ELAPSED TIME (HOURS) 5.50 **CONF 005 Task 282170-831-895-001: MODIFICATION TOTAL MANHOURS 5.50 ELAPSED TIME (HOURS) 5.50 **CONF 006 Task 282170-831-895-001: MODIFICATION TOTAL MANHOURS 5.25 ELAPSED TIME (HOURS) 5.25 APPENDICES **CONF ALL None

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 4 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN SUMMARY

**CONF ALL

B_SB_282170_5_SAAA_01_00 AND THE WIRING IN THE 107VU MODIFICATION OF THE EQUIPMENT

FR20

FR1 Z120

Figure A-FSAAA - Sheet 01

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 5 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN SUMMARY

This Page Intentionally Left Blank

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 6 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. 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



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 28 

### TITLE: FUEL SYSTEM - INTRODUCE GROUND FAULT INTERRUPTER (GFI) MODIFICATION No.: 13382H5685 This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY (1) Models 310-203 310-204 310-221 310-222 310-304 310-308 310-322 310-324 310-325 (2) Effectivity by 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 0389-0390 0392 0394 0397 0399-0400 0406-0407 0410 0413 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 0480-0485 0487-0492 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 0642 0644 0646-0654 0656 0658 0660-0661 0663 0667 0669 0671-0672 0674 0676 0678 0682 0684 0686-0687 0689 0691 0693 0697 0700 0702 0704 0706

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 1 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (3) 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 18T 0473 19U 0399 46T 0413 52X 0410 58X 0431 82Z 0550 0551 83V 0427 85W 0684 0693 0697 85Z 0547 99Y 0489 AFG 0496 0497 AIB 0650 0686 AIC 0392 0406 0407 0428 0429 0538 0544 0654 0669 AMV 0437 BAF 0367 0372 BBC 0594 0642 0700 C9L 0652 CFC 0425 0441 0444 0446 0482 DAH 0291 0293 DGA 0418 0421 0422 F2I 0309 0487 FDX 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0297 0303 0313 0316 0318 0326 0331 0333 0335 0339 0342 0343 0345 0346 0353 0355 0356 0359 0360 0362 0364 0369 0378 0394 0397 0400 0439 0449 0452 0454 0456 0457 0458 0467 0492 0500 0534 0539 0542 0549 0552 0593 0638 G2X 0573 G8E 0475 GAF 0434 0484 0498 0499 0503 0522 0523 HFY 0495 0565 IRA 0338 0370 0375 0379 0389 0390 0436 0671 IRM 0488 0524 0537 0564 0567 0586 0595 0620 IYE 0568 0702 0704 JAB 0320 JAV 0357 0481 K1P 0648 KAC 0647 0649 0663 KZU 0592 0622 0646 MGL 0526
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 2 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

OPERATOR MSN PCA 0419 PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691 QAF 0667 R1T 0591 RJA 0445 0490 0491 0531 ROT 0636 0644 RZO 0571 0624 0651 0661 SBI 0520 SGX 0519 0562 THY 0476 0478 0480 0502 TSC 0447 0472 0483 0485 0527 0541 0545 0588 0597 0599 0600 0658 UBD 0672 0674 UZB 0574 0576 0706 WHT 0448 WTJ 0494 (4) Configuration by MSN MSN CONFIGURATION 0162 0191 0201 0230 0233 0237 0245 0254 0257 0264 0267 0273 0278 0291 0293 0297 0303 0309 0313 0316 0318 0320 0326 0331 0335 0353 0355 0359 0360 0362 0364 0369 0394 0397 0400 0419 0454 001

0217 0224 0241 0248 0251 0260 0281 0283 001 003 0288 0333 0338 0339 0342 0343 0345 0346 0356 0357 0367 0372 0375 0379 0389 0390 0427 0487 002 0370 001 002 0378 0437 0481 0519 0537 0539 0549 0594 0652 0654 0669 004 005 0392 0406 0407 0410 0413 0418 0421 0422 0425 0428 0429 0431 0434 0436 0439 0441 0444 0445 0446 0447 0448 0449 0452 0456 0457 0458 0467 0472 0473 0475 0476 0478 0480 0482 0483 0484 0485 0488 0489 0490 0491 0492 0494 0495 0496 0497 0498 0499 0500 0502 0503 0520 0522 0523 0524 0526 0527 0531 0534 0538 0541 0542 0544 0545 0547 0550 0551 0552 0562 0564 0565 0567 0568 0571 0573 0574 0576 0585 0586 0587 0588 0590 0591 0593 0595 0597 0599 0600 0620 0624 0636 0638 0642 0644 0647 0648 0649 0650 0651 0653 0656 0658 0660 0661 0663 0667 0671 0672 0674 0676 0678 0682 0684 0686 0687 0689 0691 0693 0697 0700 0702 0704 0706 005

0399 001 005 0592 0622 005 006 0646 006 (5) Configuration definition **CONF 001 Configuration 001 is valid on aircraft on which: - Mod. No. 04486S5837 (or Service Bulletin No. A310-28-2004) is embodied. DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 3 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
- Mod. No. 04801S5725 is not embodied. - Mod. No. 05910S6764 (or Service Bulletin No. A310-24-2014 or Service Bulletin No. A310-24-2099) is not embodied. - Mod. No. 10805D20835 (or Service Bulletin No. A310-31-2073) is not embodied. Or - Mod. No. 04486S5837 (or Service Bulletin No. A310-28-2004) is embodied. - Mod. No. 04801S5725 is embodied. - Mod. No. 05910S6764 (or Service Bulletin No. A310-24-2014 or Service Bulletin No. A310-24-2099) is not embodied. - Mod. No. 10805D20835 (or Service Bulletin No. A310-31-2073) is embodied. Service Bulletin No. A310-28-2172 (Mod. No. 13558H5727) is not embodied. **CONF 002 Configuration 002 is valid on aircraft on which: - Mod. No. 04486S5837 (or Service Bulletin No. A310-28-2004) is embodied. - Mod. No. 04801S5725 is not embodied. - Mod. No. 05910S6764 (or Service Bulletin No. A310-24-2014 or Service Bulletin No. A310-24-2099) is embodied. - Mod. No. 10805D20835 (or Service Bulletin No. A310-31-2073) is not embodied. Service Bulletin No. A310-28-2172 (Mod. No. 13558H5727) is not embodied. **CONF 003 Configuration 003 is valid on aircraft on which: - Mod. No. 04486S5837 (or Service Bulletin No. A310-28-2004) is not embodied. - Mod. No. 04801S5725 is not embodied. - Mod. No. 05910S6764 (or Service Bulletin No. A310-24-2014 or Service Bulletin No. A310-24-2099) is not embodied. - Mod. No. 10805D20835 (or Service Bulletin No. A310-31-2073) is not embodied. Service Bulletin No. A310-28-2172 (Mod. No. 13558H5727) is not embodied. **CONF 004 Configuration 004 is valid on aircraft on which: - Mod. No. 04486S5837 (or Service Bulletin No. A310-28-2004) is embodied. - Mod. No. 04801S5725 is embodied. - Mod. No. 05910S6764 (or Service Bulletin No. A310-24-2014 or Service Bulletin No. A310-24-2099) is embodied. - Mod. No. 10805D20835 (or Service Bulletin No. A310-31-2073) is not embodied. Service Bulletin No. A310-28-2172 (Mod. No. 13558H5727) is not embodied. **CONF 005 Configuration 005 is valid on aircraft on which: - Mod. No. 04486S5837 (or Service Bulletin No. A310-28-2004) is embodied. - Mod. No. 04801S5725 is embodied. - Mod. No. 05910S6764 (or Service Bulletin No. A310-24-2014 or Service Bulletin No. A310-24-2099) is embodied. - Mod. No. 10805D20835 (or Service Bulletin No. A310-31-2073) is embodied. Service Bulletin No. A310-28-2172 (Mod. No. 13558H5727) is not embodied. **CONF 006 Configuration 006 is valid on aircraft on which: - Mod. No. 04486S5837 (or Service Bulletin No. A310-28-2004) is embodied. - Mod. No. 04801S5725 is embodied.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 4 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN - Mod. No. 05910S6764 (or Service Bulletin No. A310-24-2014 or Service Bulletin No. A310-24-2099) is embodied. - Mod. No. 10805D20835 (or Service Bulletin No. A310-31-2073) is embodied. Service Bulletin No. A310-28-2172 (Mod. No. 13558H5727) is embodied. (6) Material Effectivity **CONF 001 thru 003 MATERIAL QTY PER A/C SEE NOTES Kit 282170A01R00 1 **CONF 004 thru 005 MATERIAL QTY PER A/C SEE NOTES Kit 282170A02R00 1 **CONF 006 MATERIAL QTY PER A/C SEE NOTES Kit 282170A03R00 1 **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON (1) History The European Aviation Safety Agency (EASA) has requested that Ground Fault Interrupters (GFI) are installed into the electrical supply circuits of A300-600/600R and A310-200/300 fuel pumps where inlets become uncovered during normal operation. This is in response to SFAR88 - Fuel Tank Safety. (2) Objective/Action This Service Bulletin introduces Ground Fault Interrupters (GFI) and related bases into the electrical supply circuits of the A310-200/300 aircraft, inner center and trim (wherefitted) tank pumps. These GFIs have the same ’footprint’ as the existing relay/microcontactors and physically replace them on the electrical panel. For aircraft that have already installed a GFI in the RH Inner Tank Pump 2 circuit via Service Bulletin A310-28-2172 this Service Bulletin installs GFIs at the remaining required positions.The new GFI sockets are fool-proofed to prevent incorrectly installing normal relay/microcontactors.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 5 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (3) Advantages These GFIs will replace the existing 3-phase relay/micro-contactors. The function of the GFI is to electrically isolate the pump if a ground fault condition occurs downstream of the GFI. The GFI gives additional earth leakage protection to the downstream circuit. Accomplishment of this Service Bulletin will not change the characteristics of the aircraft. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 282170-831-895-001: MODIFICATION (1) Modification of the Equipment and the Wiring in the LH Relay Box 107VU. **CONF 002 Task 282170-831-895-001: MODIFICATION (1) Modification of the Equipment and the Wiring in the LH Relay Box 107VU. **CONF 003 Task 282170-831-895-001: MODIFICATION (1) Modification of the Equipment and the Wiring in the LH Relay Box 107VU. **CONF 004 Task 282170-831-895-001: MODIFICATION (1) Modification of the Equipment and the Wiring in the LH Relay Box 107VU. **CONF 005 Task 282170-831-895-001: MODIFICATION (1) Modification of the Equipment and the Wiring in the LH Relay Box 107VU. **CONF 006 Task 282170-831-895-001: MODIFICATION (1) Modification of the Equipment and the Wiring in the LH Relay Box 107VU.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 6 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
**CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued to confirm this classification. The accomplishment timescale, which has not yet been defined, will be given in the AD. F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. **CONF 001 Task 282170-831-895-001: MODIFICATION Get Access 0.50 On Aircraft Modification of the Equipment and the Wiring in the LH Relay Box 107VU. 3.50 Tests 0.50 Close-Up 0.50 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 002 Task 282170-831-895-001: MODIFICATION Get Access 0.50 On Aircraft
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 7 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

Task 282170-831-895-001: MODIFICATION Modification of the Equipment and the Wiring in the LH Relay Box 107VU. 3.50 Tests 0.50 Close-Up 0.50 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 003 Task 282170-831-895-001: MODIFICATION Get Access 0.50 On Aircraft Modification of the Equipment and the Wiring in the LH Relay Box 107VU. 3.50 Tests 0.50 Close-Up 0.50 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 004 Task 282170-831-895-001: MODIFICATION Get Access 0.50 On Aircraft Modification of the Equipment and the Wiring in the LH Relay Box 107VU. 4.00 Tests 0.50 Close-Up 0.50 TOTAL MANHOURS 5.50 ELAPSED TIME (HOURS) 5.50 **CONF 005 Task 282170-831-895-001: MODIFICATION Get Access 0.50 On Aircraft Modification of the Equipment and the Wiring in the LH Relay Box 107VU. 4.00 Tests 0.50 Close-Up 0.50 TOTAL MANHOURS 5.50 ELAPSED TIME (HOURS) 5.50 **CONF 006 Task 282170-831-895-001: MODIFICATION Get Access 0.50 DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 8 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

Task 282170-831-895-001: MODIFICATION On Aircraft Modification of the Equipment and the Wiring in the LH Relay Box 107VU. 3.75 Tests 0.50 Close-Up 0.50 TOTAL MANHOURS 5.25 ELAPSED TIME (HOURS) 5.25 **CONF ALL H. WEIGHT AND BALANCE The weight and balance estimates given in this Service Bulletin are based on the Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of MEW and operator’s items, refer to Weight and Balance Manual (WBM) Chapter 1-00-07. **CONF 001 thru 003 Manufacturers Empty Weight -0.354 KG (-0.7804 LB) Effect on Balance -3.399 KGM (-24.585 LB.FT ) **CONF 004 thru 005 Manufacturers Empty Weight -0.472 KG (-1.0405 LB) Effect on Balance -4.533 KGM (-32.787 LB.FT ) **CONF 006 Manufacturers Empty Weight -0.413 KG (-0.9105 LB) Effect on Balance -3.966 KGM (-28.686 LB.FT ) **CONF ALL I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-00 06-41-52 12-11-28 20-21-12 24-00-00 24-50-20 24-50-40 28-21-12 28-21-36 52-30-00 ATA Common Support Data Dictionary (CSDD), Chapter 2 Elec. Std. Practices Manual (ESPM) 20-33-00 20-46-50 20-52-21 20-55-00

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 9 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
Service Bulletin (SB) A310-24-2014 A310-24-2099 A310-28-2004 A310-28-2172 A310-31-2073 Standards Manual (SM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 002 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-00 06-41-52 12-11-28 20-21-12 24-00-00 24-50-20 24-50-40 28-21-12 28-21-36 52-30-00 ATA Common Support Data Dictionary (CSDD), Chapter 2 Elec. Std. Practices Manual (ESPM) 20-33-00 20-46-50 20-52-21 20-55-00 Service Bulletin (SB) A310-24-2014 A310-24-2099 A310-28-2004 A310-28-2172 A310-31-2073 Standards Manual (SM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 003 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-00 06-41-52 12-11-28 20-21-12 24-00-00 24-50-20 24-50-40 28-21-12 28-21-36 52-30-00 ATA Common Support Data Dictionary (CSDD), Chapter 2 Elec. Std. Practices Manual (ESPM) 20-33-00 20-46-50 20-52-21 20-55-00 Service Bulletin (SB) A310-24-2014 A310-24-2099 A310-28-2004 A310-28-2172 A310-31-2073 Standards Manual (SM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 004 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-00 06-41-52 06-41-53 12-11-28 20-21-12 24-00-00 24-50-10 24-50-20 24-50-40 28-21-12 28-21-36 28-27-00 52-30-00 ATA Common Support Data Dictionary (CSDD), Chapter 2 DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 10 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
Elec. Std. Practices Manual (ESPM) 20-33-00 20-46-50 20-52-21 20-55-00 Service Bulletin (SB) A310-24-2014 A310-24-2099 A310-28-2004 A310-28-2172 A310-31-2073 Standards Manual (SM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 005 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-00 06-41-52 06-41-53 12-11-28 20-21-12 24-00-00 24-50-10 24-50-20 24-50-40 28-21-12 28-21-36 28-27-00 52-30-00 ATA Common Support Data Dictionary (CSDD), Chapter 2 Elec. Std. Practices Manual (ESPM) 20-33-00 20-46-50 20-52-21 20-55-00 Service Bulletin (SB) A310-24-2014 A310-24-2099 A310-28-2004 A310-28-2172 A310-31-2073 Standards Manual (SM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 006 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-00 06-41-52 06-41-53 12-11-28 20-21-12 24-00-00 24-50-10 24-50-20 24-50-40 28-21-12 28-21-36 28-27-00 52-30-00 ATA Common Support Data Dictionary (CSDD), Chapter 2 Elec. Std. Practices Manual (ESPM) 20-33-00 20-46-50 20-52-21 20-55-00 Service Bulletin (SB) A310-24-2014 A310-24-2099 A310-28-2004 A310-28-2172 A310-31-2073 Standards Manual (SM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF ALL K. PUBLICATION AFFECTED

Aircraft Schematic Manual (ASM) 28-21-00
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 11 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
Aircraft Wiring List (AWL) Aircraft Wiring Manual (AWM) 28-21-03 28-21-04 28-21-05 28-21-06 28-21-09 28-21-10 28-27-01 28-27-02 31-55-45 Illustrated Parts Catalog (IPC) 28-21-08 L. INTERCHANGEABILITY/MIXABILITY **CONF 001 DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE NOTES Base NSA932844AA E0673D0S 03 YES with Conditions (1) Relay NSA932843AA01 ABS1629-28A0 03 YES with Conditions (1)
NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. NOTE: Only the mixability configuration(s) and condition(s) stated in this Service Bulletin are approved. NOTE (1): Not interchangeable, but one way interchangeable with the following conditions. On embodiment existing socket and relay will be removed and replaced with the new "error-proofed" socket and GFI. Post mod only a GFI and associated socket can be fitted. **CONF 002 DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE NOTES Base NSA932844AA E0673D0S 03 YES with Conditions (1) Relay NSA932843AA01 ABS1629-28A0 03 YES with Conditions (1)
NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. NOTE: Only the mixability configuration(s) and condition(s) stated in this Service Bulletin are approved. NOTE (1): Not interchangeable, but one way interchangeable with the following conditions. On embodiment existing socket and relay will be removed and replaced with the new "error-proofed" socket and GFI. Post mod only a GFI and associated socket can be fitted.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 12 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
**CONF 003 DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE NOTES Base NSA932844AA E0673D0S 03 YES with Conditions (1) Relay NSA932843AA01 ABS1629-28A0 03 YES with Conditions (1)
NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. NOTE: Only the mixability configuration(s) and condition(s) stated in this Service Bulletin are approved. NOTE (1): Not interchangeable, but one way interchangeable with the following conditions. On embodiment existing socket and relay will be removed and replaced with the new "error-proofed" socket and GFI. Post mod only a GFI and associated socket can be fitted. **CONF 004 DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE NOTES Base NSA932844AA E0673D0S 03 YES with Conditions (1) Relay NSA932843AA01 ABS1629-28A0 03 YES with Conditions (1)
NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. NOTE: Only the mixability configuration(s) and condition(s) stated in this Service Bulletin are approved. NOTE (1): Not interchangeable, but one way interchangeable with the following conditions. On embodiment existing socket and relay will be removed and replaced with the new "error-proofed" socket and GFI. Post mod only a GFI and associated socket can be fitted. **CONF 005 DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE NOTES Base NSA932844AA E0673D0S 03 YES with Conditions (1) Relay NSA932843AA01 ABS1629-28A0 03 YES with Conditions (1)
NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 13 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
NOTE: Only the mixability configuration(s) and condition(s) stated in this Service Bulletin are approved. NOTE (1): Not interchangeable, but one way interchangeable with the following conditions. On embodiment existing socket and relay will be removed and replaced with the new "error-proofed" socket and GFI. Post mod only a GFI and associated socket can be fitted. **CONF 006 DESCRIPTION OLD PART N ̊ NEW PART N ̊ INT MIXABILITY SEE NOTES Base NSA932844AA E0673D0S 03 YES with Conditions (1) Relay NSA932843AA01 ABS1629-28A0 03 YES with Conditions (1)
NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. NOTE: Only the mixability configuration(s) and condition(s) stated in this Service Bulletin are approved. NOTE (1): Not interchangeable, but one way interchangeable with the following conditions. On embodiment existing socket and relay will be removed and replaced with the new "error-proofed" socket and GFI. Post mod only a GFI and associated socket can be fitted. **CONF ALL M. SPARES None

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 14 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Kit 282170A01R00 Kit 282170A02R00 Kit 282170A03R00 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 For ordering by E-mail: airbus.kit@airbus.com (2) Price and Availability

Kit 282170A01R00 Cost 13,310.00 USD Availability 120 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 282170A02R00 Cost 17,680.00 USD Availability 120 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 282170A03R00 Cost 15,450.00 USD Availability 120 calendar days from receipt of order

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 15 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. B. INDUSTRY SUPPORT INFORMATION This Service Bulletin is chargeable without any price reduction. C. LIST OF COMPONENTS Kit 282170A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 ABS1629-28A0 6 GFI (1) NSA932843AA01 03 2 E0673D0S 6 BASE (2) NSA932844AA 03 3 NAS1101-04-7 18 SCREW 4 ASNA2397-3L 18 WASHER 5 MS21042-04 18 NUT EN3155-017F1216 36 CONTACT EN3155-017F1620 30 CONTACT NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. NOTE: 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, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Kit 282170A02R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 ABS1629-28A0 8 GFI (1) NSA932843AA01 03 2 E0673D0S 8 BASE (2) NSA932844AA 03 3 NAS1101-04-7 24 SCREW 4 ASNA2397-3L 24 WASHER 5 MS21042-04 24 NUT EN3155-017F1216 48 CONTACT EN3155-017F1620 38 CONTACT NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. NOTE: 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, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 16 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
Kit 282170A03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 ABS1629-28A0 7 GFI (1) NSA932843AA01 03 2 E0673D0S 7 BASE (2) NSA932844AA 03 3 NAS1101-04-7 21 SCREW 4 ASNA2397-3L 21 WASHER 5 MS21042-04 21 NUT EN3155-017F1216 42 CONTACT EN3155-017F1620 33 CONTACT NOTE: For definitions of interchangeability codes in column INT., refer to ATA Common Support Data Dictionary (CSDD), Chapter 2. NOTE: 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, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. D. LIST OF MATERIALS - OPERATOR SUPPLIED None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 17 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 18 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 282170-831-895-001 - MODIFICATION WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: BEFORE POWER IS SUPPLIED TO THE AIRCRAFT MAKE SURE THAT THE ELECTRICAL CIRCUITS UPON WHICH WORK IS IN PROGRESS ARE ISOLATED. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC. AS NECESSARY ON WIRING AND COMPONENTS - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. Task Associated Data **CONF 001 Zone 120 121 Modified FIN 35QA 35QAA 36QA 36QAA 41QA 41QAA 42QA 42QAA 109QA 109QAA 110QA 110QAA Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 002 Modified FIN 35QA 35QAA 36QA 36QAA 41QA 41QAA 42QA 42QAA 109QA 109QAA 110QA 110QAA Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 19 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
**CONF 003 Modified FIN 35QA 35QAA 36QA 36QAA 41QA 41QAA 42QA 42QAA 109QA 109QAA 110QA 110QAA Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 004 Zone 121 Modified FIN 35QA 35QAA 36QA 36QAA 41QA 41QAA 42QA 42QAA 109QA 109QAA 110QA 110QAA 9QN 9QNA 10QN 10QNA Manpower TOTAL MANHOURS 5.50 ELAPSED TIME (HOURS) 5.50 **CONF 005 Zone 121 Modified FIN 35QA 35QAA 36QA 36QAA 41QA 41QAA 42QA 42QAA 109QA 109QAA 110QA 110QAA 9QN 9QNA 10QN 10QNA Manpower TOTAL MANHOURS 5.50 ELAPSED TIME (HOURS) 5.50 **CONF 006 Zone 121 Modified FIN 35QA 35QAA 36QA 36QAA 41QA 41QAA 109QA 109QAA 110QA 110QAA 9QN 9QNA 10QN 10QNA Manpower TOTAL MANHOURS 5.25 ELAPSED TIME (HOURS) 5.25

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 20 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
**CONF ALL A. GENERAL **CONF 001 (1) Subtask 282170-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Elec. Std. Practices Manual (ESPM) 20-33-00 20-46-50 20-52-21 (a) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001). (b) For the identification of access panels (Refer to AMM 06-41-00, Page Block 001). (c) For the installation of the relays, (Refer to ESPM 20-46-50). (d) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00). (e) To torque tighten the electrical component fasteners (Refer to AMM 20-21-12, Page Block 001). (f) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21). (g) For the installation of the relays (Refer to ESPM 20-46-50). (h) For the general wiring installation (Referto ESPM 20-33-00). (2) Subtask 282170-839-401-001 - ADMINISTRATIVE Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 282170-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 21 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Elec. Std. Practices Manual (ESPM) 20-33-00 20-46-50 20-52-21 (a) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001). (b) For the identification of access panels (Refer to AMM 06-41-00, Page Block 001). (c) For the installation of the relays, (Refer to ESPM 20-46-50). (d) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00). (e) To torque tighten the electrical component fasteners (Refer to AMM 20-21-12, Page Block 001). (f) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21). (g) For the installation of the relays (Refer to ESPM 20-46-50). (h) For the general wiring installation (Referto ESPM 20-33-00). (2) Subtask 282170-839-401-001 - ADMINISTRATIVE Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 003 (1) Subtask 282170-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Elec. Std. Practices Manual (ESPM) 20-33-00 20-46-50 20-52-21 (a) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001). (b) For the identification of access panels (Refer to AMM 06-41-00, Page Block 001). (c) For the installation of the relays, (Refer to ESPM 20-46-50). DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 22 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (d) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00). (e) To torque tighten the electrical component fasteners (Refer to AMM 20-21-12, Page Block 001). (f) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21). (g) For the installation of the relays (Refer to ESPM 20-46-50). (h) For the general wiring installation (Referto ESPM 20-33-00). (2) Subtask 282170-839-401-001 - ADMINISTRATIVE Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 004 (1) Subtask 282170-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Elec. Std. Practices Manual (ESPM) 20-33-00 20-46-50 20-52-21 (a) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001). (b) For the identification of access panels (Refer to AMM 06-41-00, Page Block 001). (c) For the installation of the relays, (Refer to ESPM 20-46-50). (d) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00). (e) To torque tighten the electrical component fasteners (Refer to AMM 20-21-12, Page Block 001). (f) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21). (g) For the installation of the relays (Refer to ESPM 20-46-50). (h) For the general wiring installation (Referto ESPM 20-33-00).

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 23 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (2) Subtask 282170-839-401-001 - ADMINISTRATIVE Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 005 (1) Subtask 282170-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Elec. Std. Practices Manual (ESPM) 20-33-00 20-46-50 20-52-21 (a) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001). (b) For the identification of access panels (Refer to AMM 06-41-00, Page Block 001). (c) For the installation of the relays, (Refer to ESPM 20-46-50). (d) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00). (e) To torque tighten the electrical component fasteners (Refer to AMM 20-21-12, Page Block 001). (f) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21). (g) For the installation of the relays (Refer to ESPM 20-46-50). (h) For the general wiring installation (Referto ESPM 20-33-00). (2) Subtask 282170-839-401-001 - ADMINISTRATIVE Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 24 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
**CONF 006 (1) Subtask 282170-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Elec. Std. Practices Manual (ESPM) 20-33-00 20-46-50 20-52-21 (a) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001). (b) For the identification of access panels (Refer to AMM 06-41-00, Page Block 001). (c) For the installation of the relays, (Refer to ESPM 20-46-50). (d) Obey the instructions for the general wiring installation (Refer to ESPM 20-33-00). (e) To torque tighten the electrical component fasteners (Refer to AMM 20-21-12, Page Block 001). (f) Do a continuity test of the new and modified wires (Refer to ESPM 20-52-21). (g) For the installation of the relays (Refer to ESPM 20-46-50). (h) For the general wiring installation (Referto ESPM 20-33-00). (2) Subtask 282170-839-401-001 - ADMINISTRATIVE Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 282170-941-002-001 - Job Set-up Manpower Resources Skills ELECTRICAL

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 25 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001 24-00-00, Page Block 301 24-50-20, Page Block 001 24-50-40, Page Block 001 52-30-00, Page Block 001 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (b) Put the access platform(s) in position at the level of door 831. (c) Open the FWD Cargo-compartment door 831 (Refer to AMM 52-30-00, Page Block 001 and AMM 06-41-52, Page Block 001). (d) Open the door 132AZ (Refer to AMM 06-41-52, Page Block 001). (e) Open, safety/lock and tag these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 128VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 128VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 128VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 128VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 128VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 128VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 128VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 128VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 128VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 128VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 128VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 128VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)

or DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 26 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 132VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 132VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 132VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 132VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 132VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 132VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 132VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 132VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 132VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 132VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 132VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 132VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)
NOTE (1): For the location of the circuit breakers, refer to AMM 24-50-20, Page Block 001 and AMM 24-50-40, Page Block 001. **CONF 002 (1) Subtask 282170-941-002-001 - Job Set-up Manpower Resources Skills ELECTRICAL References Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001 24-00-00, Page Block 301 24-50-20, Page Block 001 24-50-40, Page Block 001 52-30-00, Page Block 001 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301).
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 27 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (b) Put the access platform(s) in position at the level of door 831. (c) Open the FWD Cargo-compartment door 831 (Refer to AMM 52-30-00, Page Block 001 and AMM 06-41-52, Page Block 001). (d) Open the door 132AZ (Refer to AMM 06-41-52, Page Block 001). (e) Open, safety/lock and tag these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 128VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 128VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 128VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 128VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 128VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 128VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 128VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 128VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 128VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 128VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 128VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 128VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)

or PANEL DESIGNATION FIN LOCATION SEE NOTES 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1)

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 28 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 132VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 132VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 132VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 132VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 132VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 132VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 132VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 132VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 132VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 132VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 132VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 132VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)
NOTE (1): For the location of the circuit breakers, refer to AMM 24-50-20, Page Block 001 and AMM 24-50-40, Page Block 001. **CONF 003 (1) Subtask 282170-941-002-001 - Job Set-up Manpower Resources Skills ELECTRICAL References Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001 24-00-00, Page Block 301 24-50-20, Page Block 001 24-50-40, Page Block 001 52-30-00, Page Block 001 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (b) Put the access platform(s) in position at the level of door 831. (c) Open the FWD Cargo-compartment door 831 (Refer to AMM 52-30-00, Page Block 001 and AMM 06-41-52, Page Block 001).

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 29 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (d) Open the door 132AZ (Refer to AMM 06-41-52, Page Block 001). (e) Open, safety/lock and tag these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 128VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 128VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 128VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 128VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 128VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 128VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 128VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 128VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 128VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 128VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 128VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 128VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)

or PANEL DESIGNATION FIN LOCATION SEE NOTES 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1)

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 30 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 132VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 132VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 132VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 132VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 132VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 132VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 132VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 132VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 132VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 132VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 132VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 132VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)
NOTE (1): For the location of the circuit breakers, refer to AMM 24-50-20, Page Block 001 and AMM 24-50-40, Page Block 001. **CONF 004 (1) Subtask 282170-941-002-003 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001 06-41-53, Page Block 001 24-00-00, Page Block 301 24-50-10, Page Block 001 24-50-20, Page Block 001 24-50-40, Page Block 001 52-30-00, Page Block 001 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (b) Put the access platform(s) in position at the level of door 831. (c) Open the FWD Cargo-compartment door 831 (Refer to AMM 52-30-00, Page Block 001 and AMM 06-41-52, Page Block 001). (d) Open the door 132AZ (Refer to AMM 06-41-52, Page Block 001).

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 31 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (e) Open, safety/lock and tag these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/CTL 3QN (1) 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/WARN 5QN (1) 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 101VU FUEL/TRIM TANK/PUMP 1/SUPPLY 1QN (1) 101VU FUEL/TRIM TK/PUMP 2/SUPPLY 2QN (1) 128VU FUEL/TRIM TK/XFR PUMP 2/CTL 4QN (1) 128VU FUEL/TRIM TK/XFR PUMP 2/WARN 6QN (1) 128VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 128VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 128VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 128VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 128VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 128VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 128VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 128VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 128VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 128VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 128VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 128VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)

or

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 32 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/CTL 3QN (1) 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/WARN 5QN (1) 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 101VU FUEL/TRIM TANK/PUMP 1/SUPPLY 1QN (1) 101VU FUEL/TRIM TK/PUMP 2/SUPPLY 2QN (1) 132VU FUEL/TRIM TK/XFR PUMP 2/CTL 4QN (1) 132VU FUEL/TRIM TK/XFR PUMP 2/WARN 6QN (1) 132VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 132VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 132VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 132VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 132VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 132VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 132VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 132VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 132VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 132VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 132VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 132VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)
NOTE (1): For the location of the circuit breakers, refer to AMM 24-50-10, Page Block 001, AMM 24-50-20, Page Block 001 and AMM 24-50-40, Page Block 001.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 33 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
**CONF 005 (1) Subtask 282170-941-002-003 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001 06-41-53, Page Block 001 24-00-00, Page Block 301 24-50-10, Page Block 001 24-50-20, Page Block 001 24-50-40, Page Block 001 52-30-00, Page Block 001 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (b) Put the access platform(s) in position at the level of door 831. (c) Open the FWD Cargo-compartment door 831 (Refer to AMM 52-30-00, Page Block 001 and AMM 06-41-52, Page Block 001). (d) Open the door 132AZ (Refer to AMM 06-41-52, Page Block 001). (e) Open, safety/lock and tag these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/CTL 3QN (1) 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/WARN 5QN (1) 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 101VU FUEL/TRIM TANK/PUMP 1/SUPPLY 1QN (1) 101VU FUEL/TRIM TK/PUMP 2/SUPPLY 2QN (1) 128VU FUEL/TRIM TK/XFR PUMP 2/CTL 4QN (1)

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 34 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU FUEL/TRIM TK/XFR PUMP 2/WARN 6QN (1) 128VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 128VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 128VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 128VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 128VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 128VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 128VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 128VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 128VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 128VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 128VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 128VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)

or PANEL DESIGNATION FIN LOCATION SEE NOTES 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/CTL 3QN (1) 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/WARN 5QN (1) 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 101VU FUEL/TRIM TANK/PUMP 1/SUPPLY 1QN (1) 101VU FUEL/TRIM TK/PUMP 2/SUPPLY 2QN (1) 132VU FUEL/TRIM TK/XFR PUMP 2/CTL 4QN (1) 132VU FUEL/TRIM TK/XFR PUMP 2/WARN 6QN (1) 132VU FUEL/L INR TK/PUMP 2/WARN 11QA (1)

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 35 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 132VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 132VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 132VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 132VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 132VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 132VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 132VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 132VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 132VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 132VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 132VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)
NOTE (1): For the location of the circuit breakers, refer to AMM 24-50-10, Page Block 001, AMM 24-50-20, Page Block 001 and AMM 24-50-40, Page Block 001. **CONF 006 (1) Subtask 282170-941-002-003 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001 06-41-53, Page Block 001 24-00-00, Page Block 301 24-50-10, Page Block 001 24-50-20, Page Block 001 24-50-40, Page Block 001 52-30-00, Page Block 001 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (b) Put the access platform(s) in position at the level of door 831. (c) Open the FWD Cargo-compartment door 831 (Refer to AMM 52-30-00, Page Block 001 and AMM 06-41-52, Page Block 001). (d) Open the door 132AZ (Refer to AMM 06-41-52, Page Block 001).

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 36 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (e) Open, safety/lock and tag these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/CTL 3QN (1) 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/WARN 5QN (1) 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 101VU FUEL/TRIM TANK/PUMP 1/SUPPLY 1QN (1) 101VU FUEL/TRIM TK/PUMP 2/SUPPLY 2QN (1) 128VU FUEL/TRIM TK/XFR PUMP 2/CTL 4QN (1) 128VU FUEL/TRIM TK/XFR PUMP 2/WARN 6QN (1) 128VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 128VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 128VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 128VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 128VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 128VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 128VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 128VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 128VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 128VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 128VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 128VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)

or

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 37 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/CTL 3QN (1) 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/WARN 5QN (1) 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 101VU FUEL/TRIM TANK/PUMP 1/SUPPLY 1QN (1) 101VU FUEL/TRIM TK/PUMP 2/SUPPLY 2QN (1) 132VU FUEL/TRIM TK/XFR PUMP 2/CTL 4QN (1) 132VU FUEL/TRIM TK/XFR PUMP 2/WARN 6QN (1) 132VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 132VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 132VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 132VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 132VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 132VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 132VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 132VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 132VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 132VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 132VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 132VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)
NOTE (1): For the location of the circuit breakers, refer to AMM 24-50-10, Page Block 001, AMM 24-50-20, Page Block 001 and AMM 24-50-40, Page Block 001.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 38 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
**CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 282170-831-002-001 - Modification of the Equipment and the Wiring in the LH Relay Box 107VU. Work Zones and Access Panels Zone Access/Work location 120 Work location Electrical panel 107VU Manpower Resources Manhours 3.50 Minimum number of person 1 Subtask elapsed time 3.50 Skills ELECTRICAL Material necessary to do the job Kit 282170A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 ABS1629-28A0 6 GFI 2 E0673D0S 6 BASE 3 NAS1101-04-7 18 SCREW 4 ASNA2397-3L 18 WASHER 5 MS21042-04 18 NUT EN3155-017F1216 36 CONTACT EN3155-017F1620 30 CONTACT References Fig. A-FBAAA Location of the Modification Sheet 01 Fig. A-FBBAA Modification of the Equipment in the LH Relay Box 107VU. Sheet 01
Fig. A-FHAAA Hook-up Chart of the Modification of the Wiring of the Relay 35QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHBAA Hook-up Chart of the Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU. Sheet 01

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 39 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

References Fig. A-FHCAA Hook-up Chart of the Modification of the Wiring of the Relay 41QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHDAA Hook-up Chart of the Modification of the Wiring of the Relay 42QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHEAB Hook-up Chart of the Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHFAA Hook-up Chart of the Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FWAAA Modification of the Wiring of the Relay 35QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWBAA Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWCAA Modification of the Wiring of the Relay 41QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWDAA Modification of the Wiring of the Relay 42QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWEAB Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWFAA Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 (a) Remove the relay 35QA (Refer to Fig. A-FBBAA Sheet 01): FIN 35QA 1 Relay NSA932843AA01 Item (1) Discard FIN 35QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 40 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
3 Nut Item (5) Discard (b) Install the relay GFI 35QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 35QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWAAA Sheet 01 and Fig. A-FWAAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHAAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 35QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (c) Remove the relay 36QA (Refer to Fig. A-FBBAA Sheet 01): FIN 36QA 1 Relay NSA932843AA01 Item (1) Discard FIN 36QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 41 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
3 Washer Item (4) Discard 3 Nut Item (5) Discard (d) Install the relay GFI 36QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 36QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWBAA Sheet 01 and Fig. A-FWBAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHBAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 36QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (e) Remove the relay 41QA (Refer to Fig. A-FBBAA Sheet 01): FIN 41QA 1 Relay NSA932843AA01 Item (1) Discard FIN 41QAA 1 Base NSA932844AA Item (2) Discard Attached with:

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 42 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (f) Install the relay GFI 41QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 41QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWCAA Sheet 01 and Fig. A-FWCAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHCAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 41QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (g) Remove the relay 42QA (Refer to Fig. A-FBBAA Sheet 01): FIN 42QA 1 Relay NSA932843AA01 Item (1) Discard FIN 42QAA 1 Base NSA932844AA Item (2) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 43 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (h) Install the relay GFI 42QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 42QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWDAA Sheet 01 and Fig. A-FWDAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHDAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 42QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (i) Remove the relay 109QA (Refer to Fig. A-FBBAA Sheet 01): FIN 109QA 1 Relay NSA932843AA01 Item (1) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 44 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
FIN 109QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (j) Install the relay GFI 109QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 109QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWEAB Sheet 01 and Fig. A-FWEAB Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHEAB Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 109QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb).

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 45 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (k) Remove the relay 110QA (Refer to Fig. A-FBBAA Sheet 01): FIN 110QA 1 Relay NSA932843AA01 Item (1) Discard FIN 110QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (l) Install the relay GFI 110QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 110QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWFAA Sheet 01 and Fig. A-FWFAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHFAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 110QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 46 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
**CONF 002 (1) Subtask 282170-831-002-002 - Modification of the Equipment and the Wiring in the LH Relay Box 107VU. Manpower Resources Manhours 3.50 Minimum number of person 1 Subtask elapsed time 3.50 Skills ELECTRICAL Material necessary to do the job Kit 282170A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 ABS1629-28A0 6 GFI 2 E0673D0S 6 BASE 3 NAS1101-04-7 18 SCREW 4 ASNA2397-3L 18 WASHER 5 MS21042-04 18 NUT EN3155-017F1216 36 CONTACT EN3155-017F1620 30 CONTACT References Fig. A-FBAAA Location of the Modification Sheet 01 Fig. A-FBBAA Modification of the Equipment in the LH Relay Box 107VU. Sheet 01
Fig. A-FHAAA Hook-up Chart of the Modification of the Wiring of the Relay 35QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHBAB Hook-up Chart of the Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHCAA Hook-up Chart of the Modification of the Wiring of the Relay 41QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHDAA Hook-up Chart of the Modification of the Wiring of the Relay 42QA in the LH Relay Box 107VU. Sheet 01

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 47 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

References Fig. A-FHEAA Hook-up Chart of the Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHFAA Hook-up Chart of the Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FWAAA Modification of the Wiring of the Relay 35QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWBAB Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWCAA Modification of the Wiring of the Relay 41QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWDAA Modification of the Wiring of the Relay 42QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWEAA Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWFAA Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 (a) Remove the relay 35QA (Refer to Fig. A-FBBAA Sheet 01): FIN 35QA 1 Relay NSA932843AA01 Item (1) Discard FIN 35QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (b) Install the relay GFI 35QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 35QAA 1 Base E0673D0S Item 2 DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 48 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWAAA Sheet 01 and Fig. A-FWAAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHAAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 35QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (c) Remove the relay 36QA (Refer to Fig. A-FBBAA Sheet 01): FIN 36QA 1 Relay NSA932843AA01 Item (1) Discard FIN 36QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 49 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (d) Install the relay GFI 36QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 36QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWBAB Sheet 01 and Fig. A-FWBAB Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHBAB Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 36QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (e) Remove the relay 41QA (Refer to Fig. A-FBBAA Sheet 01): FIN 41QA 1 Relay NSA932843AA01 Item (1) Discard FIN 41QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 50 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
3 Nut Item (5) Discard (f) Install the relay GFI 41QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 41QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWCAA Sheet 01 and Fig. A-FWCAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHCAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 41QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (g) Remove the relay 42QA (Refer to Fig. A-FBBAA Sheet 01): FIN 42QA 1 Relay NSA932843AA01 Item (1) Discard FIN 42QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 51 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
3 Washer Item (4) Discard 3 Nut Item (5) Discard (h) Install the relay GFI 42QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 42QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWDAA Sheet 01 and Fig. A-FWDAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHDAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 42QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (i) Remove the relay 109QA (Refer to Fig. A-FBBAA Sheet 01): FIN 109QA 1 Relay NSA932843AA01 Item (1) Discard FIN 109QAA 1 Base NSA932844AA Item (2) Discard Attached with:

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 52 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (j) Install the relay GFI 109QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 109QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWEAA Sheet 01 and Fig. A-FWEAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHEAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 109QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (k) Remove the relay 110QA (Refer to Fig. A-FBBAA Sheet 01): FIN 110QA 1 Relay NSA932843AA01 Item (1) Discard FIN 110QAA 1 Base NSA932844AA Item (2) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 53 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (l) Install the relay GFI 110QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 110QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWFAA Sheet 01 and Fig. A-FWFAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHFAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 110QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb).

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 54 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
**CONF 003 (1) Subtask 282170-831-002-003 - Modification of the Equipment and the Wiring in the LH Relay Box 107VU. Manpower Resources Manhours 3.50 Minimum number of person 1 Subtask elapsed time 3.50 Skills ELECTRICAL Material necessary to do the job Kit 282170A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 ABS1629-28A0 6 GFI 2 E0673D0S 6 BASE 3 NAS1101-04-7 18 SCREW 4 ASNA2397-3L 18 WASHER 5 MS21042-04 18 NUT EN3155-017F1216 36 CONTACT EN3155-017F1620 30 CONTACT References Fig. A-FBAAA Location of the Modification Sheet 01 Fig. A-FBBAA Modification of the Equipment in the LH Relay Box 107VU. Sheet 01
Fig. A-FHAAA Hook-up Chart of the Modification of the Wiring of the Relay 35QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHBAA Hook-up Chart of the Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHCAA Hook-up Chart of the Modification of the Wiring of the Relay 41QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHDAA Hook-up Chart of the Modification of the Wiring of the Relay 42QA in the LH Relay Box 107VU. Sheet 01

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 55 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

References Fig. A-FHEAC Hook-up Chart of the Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHFAB Hook-up Chart of the Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FWAAA Modification of the Wiring of the Relay 35QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWBAA Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWCAA Modification of the Wiring of the Relay 41QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWDAA Modification of the Wiring of the Relay 42QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWEAC Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWFAB Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 (a) Remove the relay 35QA (Refer to Fig. A-FBBAA Sheet 01): FIN 35QA 1 Relay NSA932843AA01 Item (1) Discard FIN 35QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (b) Install the relay GFI 35QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 35QAA 1 Base E0673D0S Item 2 DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 56 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWAAA Sheet 01 and Fig. A-FWAAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHAAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 35QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (c) Remove the relay 36QA (Refer to Fig. A-FBBAA Sheet 01): FIN 36QA 1 Relay NSA932843AA01 Item (1) Discard FIN 36QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 57 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (d) Install the relay GFI 36QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 36QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWBAA Sheet 01 and Fig. A-FWBAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHBAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 36QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (e) Remove the relay 41QA (Refer to Fig. A-FBBAA Sheet 01): FIN 41QA 1 Relay NSA932843AA01 Item (1) Discard FIN 41QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 58 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
3 Nut Item (5) Discard (f) Install the relay GFI 41QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 41QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWCAA Sheet 01 and Fig. A-FWCAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHCAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 41QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (g) Remove the relay 42QA (Refer to Fig. A-FBBAA Sheet 01): FIN 42QA 1 Relay NSA932843AA01 Item (1) Discard FIN 42QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 59 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
3 Washer Item (4) Discard 3 Nut Item (5) Discard (h) Install the relay GFI 42QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 42QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWDAA Sheet 01 and Fig. A-FWDAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHDAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 42QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (i) Remove the relay 109QA (Refer to Fig. A-FBBAA Sheet 01): FIN 109QA 1 Relay NSA932843AA01 Item (1) Discard FIN 109QAA 1 Base NSA932844AA Item (2) Discard Attached with:

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 60 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (j) Install the relay GFI 109QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 109QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWEAC Sheet 01 and Fig. A-FWEAC Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHEAC Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 109QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (k) Remove the relay 110QA (Refer to Fig. A-FBBAA Sheet 01): FIN 110QA 1 Relay NSA932843AA01 Item (1) Discard FIN 110QAA 1 Base NSA932844AA Item (2) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 61 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (l) Install the relay GFI 110QA: 1 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 110QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWFAB Sheet 01 and Fig. A-FWFAB Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHFAB Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAA Sheet 01): FIN 110QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb).

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 62 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
**CONF 004 (1) Subtask 282170-831-002-004 - Modification of the Equipment and the Wiring in the LH Relay Box 107VU. Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills ELECTRICAL Material necessary to do the job Kit 282170A02R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 ABS1629-28A0 8 GFI 2 E0673D0S 8 BASE 3 NAS1101-04-7 24 SCREW 4 ASNA2397-3L 24 WASHER 5 MS21042-04 24 NUT EN3155-017F1216 48 CONTACT EN3155-017F1620 38 CONTACT References Fig. A-FBAAB Location of the Modification Sheet 01 Fig. A-FBBAB Modification of the Equipment in the LH Relay Box 107VU. Sheet 01
Fig. A-FHAAA Hook-up Chart of the Modification of the Wiring of the Relay 35QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHBAB Hook-up Chart of the Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHCAA Hook-up Chart of the Modification of the Wiring of the Relay 41QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHDAA Hook-up Chart of the Modification of the Wiring of the Relay 42QA in the LH Relay Box 107VU. Sheet 01

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 63 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

References Fig. A-FHEAA Hook-up Chart of the Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHFAA Hook-up Chart of the Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHGAB Hook-up Chart of the Modification of the Wiring of the Relay 9QN in the LH Relay Box 107VU. Sheet 01

Fig. A-FHHAB Hook-up Chart of the Modification of the Wiring of the Relay 10QN in the LH Relay Box 107VU. Sheet 01

Fig. A-FWAAA Modification of the Wiring of the Relay 35QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWBAB Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWCAA Modification of the Wiring of the Relay 41QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWDAA Modification of the Wiring of the Relay 42QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWEAA Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWFAA Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWGAB Modification of the Wiring of the Relay 9QN in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWHAB Modification of the Wiring of the Relay 10QN in the LH Relay Box 107VU. Sheet 01 Sheet 02 (a) Remove the relay 35QA (Refer to Fig. A-FBBAB Sheet 01): FIN 35QA 1 Relay NSA932843AA01 Item (1) Discard FIN 35QAA 1 Base NSA932844AA Item (2) Discard DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 64 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (b) Install the relay GFI 35QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 35QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWAAA Sheet 01 and Fig. A-FWAAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHAAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 35QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (c) Remove the relay 36QA (Refer to Fig. A-FBBAB Sheet 01): FIN 36QA 1 Relay NSA932843AA01 Item (1) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 65 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
FIN 36QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (d) Install the relay GFI 36QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 36QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWBAB Sheet 01 and Fig. A-FWBAB Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHBAB Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 36QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb).

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 66 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (e) Remove the relay 41QA (Refer to Fig. A-FBBAB Sheet 01): FIN 41QA 1 Relay NSA932843AA01 Item (1) Discard FIN 41QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (f) Install the relay GFI 41QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 41QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWCAA Sheet 01 and Fig. A-FWCAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHCAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 41QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 67 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (g) Remove the relay 42QA (Refer to Fig. A-FBBAB Sheet 01): FIN 42QA 1 Relay NSA932843AA01 Item (1) Discard FIN 42QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (h) Install the relay GFI 42QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 42QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWDAA Sheet 01 and Fig. A-FWDAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHDAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 42QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 68 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (i) Remove the relay 109QA (Refer to Fig. A-FBBAB Sheet 01): FIN 109QA 1 Relay NSA932843AA01 Item (1) Discard FIN 109QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (j) Install the relay GFI 109QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 109QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWEAA Sheet 01 and Fig. A-FWEAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHEAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 109QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 69 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (k) Remove the relay 110QA (Refer to Fig. A-FBBAB Sheet 01): FIN 110QA 1 Relay NSA932843AA01 Item (1) Discard FIN 110QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (l) Install the relay GFI 110QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 110QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWFAA Sheet 01 and Fig. A-FWFAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHFAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 110QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 70 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (m) Remove the relay 9QN (Refer to Fig. A-FBBAB Sheet 01): FIN 9QN 1 Relay NSA932843AA01 Item (1) Discard FIN 9QNA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (n) Install the relay GFI 9QN: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 9QNA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWGAB Sheet 01 and Fig. A-FWGAB Sheet 02 and as given in the hook-up chart lines: - 1 thru 20 (Refer to Fig. A-FHGAB Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 4 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 9QN 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 71 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (o) Remove the relay 10QN (Refer to Fig. A-FBBAB Sheet 01): FIN 10QN 1 Relay NSA932843AA01 Item (1) Discard FIN 10QNA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (p) Install the relay GFI 10QN: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 10QNA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWHAB Sheet 01 and Fig. A-FWHAB Sheet 02 and as given in the hook-up chart lines: - 1 thru 20 (Refer to Fig. A-FHHAB Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 4 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 10QN 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 72 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
**CONF 005 (1) Subtask 282170-831-002-005 - Modification of the Equipment and the Wiring in the LH Relay Box 107VU. Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills ELECTRICAL Material necessary to do the job Kit 282170A02R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 ABS1629-28A0 8 GFI 2 E0673D0S 8 BASE 3 NAS1101-04-7 24 SCREW 4 ASNA2397-3L 24 WASHER 5 MS21042-04 24 NUT EN3155-017F1216 48 CONTACT EN3155-017F1620 38 CONTACT References Fig. A-FBAAB Location of the Modification Sheet 01 Fig. A-FBBAB Modification of the Equipment in the LH Relay Box 107VU. Sheet 01
Fig. A-FHAAA Hook-up Chart of the Modification of the Wiring of the Relay 35QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHBAB Hook-up Chart of the Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHCAA Hook-up Chart of the Modification of the Wiring of the Relay 41QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHDAA Hook-up Chart of the Modification of the Wiring of the Relay 42QA in the LH Relay Box 107VU. Sheet 01

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 73 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

References Fig. A-FHEAA Hook-up Chart of the Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHFAA Hook-up Chart of the Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHGAA Hook-up Chart of the Modification of the Wiring of the Relay 9QN in the LH Relay Box 107VU. Sheet 01

Fig. A-FHHAA Hook-up Chart of the Modification of the Wiring of the Relay 10QN in the LH Relay Box 107VU. Sheet 01

Fig. A-FWAAA Modification of the Wiring of the Relay 35QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWBAB Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWCAA Modification of the Wiring of the Relay 41QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWDAA Modification of the Wiring of the Relay 42QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWEAA Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWFAA Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWGAA Modification of the Wiring of the Relay 9QN in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWHAA Modification of the Wiring of the Relay 10QN in the LH Relay Box 107VU. Sheet 01 Sheet 02 (a) Remove the relay 35QA (Refer to Fig. A-FBBAB Sheet 01): FIN 35QA 1 Relay NSA932843AA01 Item (1) Discard FIN 35QAA 1 Base NSA932844AA Item (2) Discard DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 74 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (b) Install the relay GFI 35QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 35QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWAAA Sheet 01 and Fig. A-FWAAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHAAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 35QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (c) Remove the relay 36QA (Refer to Fig. A-FBBAB Sheet 01): FIN 36QA 1 Relay NSA932843AA01 Item (1) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 75 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
FIN 36QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (d) Install the relay GFI 36QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 36QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWBAB Sheet 01 and Fig. A-FWBAB Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHBAB Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 36QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb).

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 76 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (e) Remove the relay 41QA (Refer to Fig. A-FBBAB Sheet 01): FIN 41QA 1 Relay NSA932843AA01 Item (1) Discard FIN 41QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (f) Install the relay GFI 41QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 41QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWCAA Sheet 01 and Fig. A-FWCAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHCAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 41QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 77 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (g) Remove the relay 42QA (Refer to Fig. A-FBBAB Sheet 01): FIN 42QA 1 Relay NSA932843AA01 Item (1) Discard FIN 42QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (h) Install the relay GFI 42QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 42QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWDAA Sheet 01 and Fig. A-FWDAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHDAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 42QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 78 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (i) Remove the relay 109QA (Refer to Fig. A-FBBAB Sheet 01): FIN 109QA 1 Relay NSA932843AA01 Item (1) Discard FIN 109QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (j) Install the relay GFI 109QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 109QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWEAA Sheet 01 and Fig. A-FWEAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHEAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 109QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 79 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (k) Remove the relay 110QA (Refer to Fig. A-FBBAB Sheet 01): FIN 110QA 1 Relay NSA932843AA01 Item (1) Discard FIN 110QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (l) Install the relay GFI 110QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 110QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWFAA Sheet 01 and Fig. A-FWFAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHFAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 110QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 80 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (m) Remove the relay 9QN (Refer to Fig. A-FBBAB Sheet 01): FIN 9QN 1 Relay NSA932843AA01 Item (1) Discard FIN 9QNA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (n) Install the relay GFI 9QN: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 9QNA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWGAA Sheet 01 and Fig. A-FWGAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 20 (Refer to Fig. A-FHGAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 4 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 9QN 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 81 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (o) Remove the relay 10QN (Refer to Fig. A-FBBAB Sheet 01): FIN 10QN 1 Relay NSA932843AA01 Item (1) Discard FIN 10QNA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (p) Install the relay GFI 10QN: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 10QNA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWHAA Sheet 01 and Fig. A-FWHAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 20 (Refer to Fig. A-FHHAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 4 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 10QN 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 82 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
**CONF 006 (1) Subtask 282170-831-002-006 - Modification of the Equipment and the Wiring in the LH Relay Box 107VU. Manpower Resources Manhours 3.75 Minimum number of person 1 Subtask elapsed time 3.75 Skills ELECTRICAL Material necessary to do the job Kit 282170A03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 ABS1629-28A0 7 GFI 2 E0673D0S 7 BASE 3 NAS1101-04-7 21 SCREW 4 ASNA2397-3L 21 WASHER 5 MS21042-04 21 NUT EN3155-017F1216 42 CONTACT EN3155-017F1620 33 CONTACT References Fig. A-FBBAB Modification of the Equipment in the LH Relay Box 107VU. Sheet 01
Fig. A-FHAAA Hook-up Chart of the Modification of the Wiring of the Relay 35QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHBAB Hook-up Chart of the Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHCAA Hook-up Chart of the Modification of the Wiring of the Relay 41QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHEAA Hook-up Chart of the Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU. Sheet 01

Fig. A-FHFAA Hook-up Chart of the Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU. Sheet 01

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 83 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

References Fig. A-FHGAA Hook-up Chart of the Modification of the Wiring of the Relay 9QN in the LH Relay Box 107VU. Sheet 01

Fig. A-FHHAA Hook-up Chart of the Modification of the Wiring of the Relay 10QN in the LH Relay Box 107VU. Sheet 01

Fig. A-FWAAA Modification of the Wiring of the Relay 35QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWBAB Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWCAA Modification of the Wiring of the Relay 41QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWEAA Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWFAA Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWGAA Modification of the Wiring of the Relay 9QN in the LH Relay Box 107VU. Sheet 01 Sheet 02 Fig. A-FWHAA Modification of the Wiring of the Relay 10QN in the LH Relay Box 107VU. Sheet 01 Sheet 02 (a) Remove the relay 35QA (Refer to Fig. A-FBBAB Sheet 01): FIN 35QA 1 Relay NSA932843AA01 Item (1) Discard FIN 35QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 84 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (b) Install the relay GFI 35QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 35QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWAAA Sheet 01 and Fig. A-FWAAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHAAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 35QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (c) Remove the relay 36QA (Refer to Fig. A-FBBAB Sheet 01): FIN 36QA 1 Relay NSA932843AA01 Item (1) Discard FIN 36QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 85 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
3 Nut Item (5) Discard (d) Install the relay GFI 36QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 36QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWBAB Sheet 01 and Fig. A-FWBAB Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHBAB Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 36QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (e) Remove the relay 41QA (Refer to Fig. A-FBBAB Sheet 01): FIN 41QA 1 Relay NSA932843AA01 Item (1) Discard FIN 41QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 86 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
3 Washer Item (4) Discard 3 Nut Item (5) Discard (f) Install the relay GFI 41QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 41QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWCAA Sheet 01 and Fig. A-FWCAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHCAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 41QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (g) Remove the relay 109QA (Refer to Fig. A-FBBAB Sheet 01): FIN 109QA 1 Relay NSA932843AA01 Item (1) Discard FIN 109QAA 1 Base NSA932844AA Item (2) Discard Attached with:

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 87 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (h) Install the relay GFI 109QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 109QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWEAA Sheet 01 and Fig. A-FWEAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHEAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 109QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (i) Remove the relay 110QA (Refer to Fig. A-FBBAB Sheet 01): FIN 110QA 1 Relay NSA932843AA01 Item (1) Discard FIN 110QAA 1 Base NSA932844AA Item (2) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 88 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (j) Install the relay GFI 110QA: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 110QAA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWFAA Sheet 01 and Fig. A-FWFAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 22 (Refer to Fig. A-FHFAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 5 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 110QA 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). (k) Remove the relay 9QN (Refer to Fig. A-FBBAB Sheet 01): FIN 9QN 1 Relay NSA932843AA01 Item (1) Discard

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 89 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
FIN 9QNA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (l) Install the relay GFI 9QN: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 9QNA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWGAA Sheet 01 and Fig. A-FWGAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 20 (Refer to Fig. A-FHGAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 4 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 9QN 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb).

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 90 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (m) Remove the relay 10QN (Refer to Fig. A-FBBAB Sheet 01): FIN 10QN 1 Relay NSA932843AA01 Item (1) Discard FIN 10QNA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard (n) Install the relay GFI 10QN: 1 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 10QNA 1 Base E0673D0S Item 2 Attach with: 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5 NOTE: Tighten the three nuts Item 5 to a torque value of 0.10 m.daN (8.851 in.lb). 2 Modify the connections of the wires as shown in the wiring diagrams Fig. AFWHAA Sheet 01 and Fig. A-FWHAA Sheet 02 and as given in the hook-up chart lines: - 1 thru 20 (Refer to Fig. A-FHHAA Sheet 01). NOTE: If necessary, use: 6 Contact EN3155-017F1216 4 Contact EN3155-017F1620 3 Install (Refer to Fig. A-FBBAB Sheet 01): FIN 10QN 1 GFI ABS1629-28A0 Item 1 NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb). DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 91 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
**CONF ALL D. TEST **CONF 001 (1) Subtask 282170-840-401-001 - Preparation for Test Procedure Manpower Resources Skills ELECTRICAL References Aircraft Maintenance Manual (AMM) 12-11-28, Page Block 301 Fig. A-UBAAA Ground Fault Interrupter - Tripped/Not Tripped Sheet 01
(a) Refer to Fig. A-UBAAA Sheet 01 1 Inspect the GFI 35QA, 36QA, 41QA, 42QA, 109QA, and 110QA and make sure that it is in the reset (non-tripped) state (metal shaft is not seen on the trip/reset plunger). 2 If the GFI 35QA, 36QA, 41QA, 42QA, 109QA, and 110QA is tripped (metal shaft is seen on the trip/reset plunger) then reset by depressing the trip/reset plunger until it latches in. 3 Make sure that the left and right inner tanks and the center tank contains a minimum of 500 Kg (1,102 lb) of fuel. If necessary, refuel the tanks (Refer to AMM 12-11-28, Page Block 301). (2) Subtask 282170-700-001-001 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-50-20, Page Block 001 24-50-40, Page Block 001 28-21-12, Page Block 501 28-21-36, Page Block 401 (a) Remove the safety clip(s) and/or tag(s) and close/unlock these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1)

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 92 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 128VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 128VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 128VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 128VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 128VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 128VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 128VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 128VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 128VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 128VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 128VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 128VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)

or PANEL DESIGNATION FIN LOCATION SEE NOTES 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 132VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 132VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 132VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 132VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 132VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 132VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 93 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 132VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 132VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 132VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 132VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 132VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 132VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)
NOTE (1): For the location of the circuit breakers, refer to AMM 24-50-20, Page Block 001 and AMM 24-50-40, Page Block 001. (b) Do the operational test of the Inner Tanks Booster Pumps (Refer to AMM 28-21-12, Page Block 501). (c) Do the test procedure as specified after the installation of the center tank booster pumps (81QA, 82QA) (Refer to AMM 28-21-36, Page Block 401). (3) Subtask 282170-710-401-001 - Operational Test Work Zones and Access Panels Zone Access/Work location 121 Work location 132VU 35-QA 132VU 36-QA 132VU 41-QA 132VU 42-QA 132VU 109-QA 132VU 110-QA Manpower Resources Skills ELECTRICAL WARNING: ACCIDENTAL REARWARD FUEL TRANSFER CAN MOVE THE C OF G AFT OF SAFE LIMIT. MAKE SURE TRIM TANK VALVES ARE SHUT. ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Inner Tank Pump 2 pushbutton switch (P/BSW) (19QA) comes on. - L Inner Tank Pump 2 Selected OFF.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19 QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 94 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 107VU: - Press the test button on top of the L Inner Tank Pump 2 GFI (35QA). - L Inner Tank Pump 2 stops. On Panel 107VU: - the trip/RESET button on GFI (35QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) goes off. - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Inner Tank Pump 2 GFI (35QA) until it latches in. - L Inner Tank Pump 2 GFI (35QA) reset.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. Table 1 - Operational Test Procedure - 35QA L Inner Tank Pump 2
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Inner Tank Pump 1 pushbutton switch (P/BSW) (20QA) comes on. - R Inner Tank Pump 1 Selected OFF.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 95 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the R Inner Tank Pump 1 GFI (36QA). - R Inner Tank Pump 1 stops. On Panel 107VU: - the trip/RESET button on GFI (36QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) goes off. - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Inner Tank Pump 1 GFI (36QA) until it latches in. - R Inner Tank Pump 1 GFI (36QA) reset.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. Table 2 - Operational Test Procedure - 36QA R Inner Tank Pump 1
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Inner Tank Pump 1 pushbutton switch (P/BSW) (25QA) comes on. - L Inner Tank Pump 1 Selected OFF.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 96 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the L Inner Tank Pump 1 GFI (41QA). - L Inner Tank Pump 1 stops. On Panel 107VU: - the trip/RESET button on GFI (41QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) goes off. - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Inner Tank Pump 1 GFI (41QA) until it latches in. - L Inner Tank Pump 1 GFI (41QA) reset.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. Table 3 - Operational Test Procedure - 41QA L Inner Tank Pump 1
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Inner Tank Pump 2 pushbutton switch (P/BSW) (26QA) comes on. - R Inner Tank Pump 2 Selected OFF.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. On Panel 430VU: - Press (Select in) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 97 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the R Inner Tank Pump 2 GFI (42QA). - R Inner Tank Pump 2 stops. On Panel 107VU: - the trip/RESET button on GFI (42QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 2 P/BSW (26QA). On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) goes off. - OFF legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Inner Tank Pump 2 GFI (42QA) until it latches in. - R Inner Tank Pump 2 GFI (42QA) reset.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. Table 4 - Operational Test Procedure - 42QA R Inner Tank Pump 2
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Center Tank Pump pushbutton switch (P/BSW) (93QA) comes on. - L Center Tank Pump Selected OFF.

On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 98 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the L Center Tank Pump GFI (109QA). - L Center Tank Pump stops. On Panel 107VU: - the trip/RESET button on GFI (109QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). On Panel 430VU: - the FAULT legend lamp on the L Center Tank Pump P/BSW (93QA) goes off. - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Center Tank Pump GFI (109QA) until it latches in. - L Center Tank Pump GFI (109QA) reset.

On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. Table 5 - Operational Test Procedure - 109QA L Center Tank Pump
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Center Tank Pump pushbutton switch (P/BSW) (94QA) comes on. - R Center Tank Pump Selected OFF.

On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 99 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the R Center Tank Pump GFI (110QA). - R Center Tank Pump stops. On Panel 107VU: - the trip/RESET button on GFI (110QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). On Panel 430VU: - the FAULT legend lamp on the R Center Tank Pump P/BSW (94QA) goes off. - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Center Tank Pump GFI (110QA) until it latches in. - R Center Tank Pump GFI (110QA) reset.

On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. Table 6 - Operational Test Procedure - 110QA R Center Tank Pump
**CONF 002 (1) Subtask 282170-840-401-001 - Preparation for Test Procedure Manpower Resources Skills ELECTRICAL References Aircraft Maintenance Manual (AMM) 12-11-28, Page Block 301 Fig. A-UBAAA Ground Fault Interrupter - Tripped/Not Tripped Sheet 01
(a) Refer to Fig. A-UBAAA Sheet 01 1 Inspect the GFI 35QA, 36QA, 41QA, 42QA, 109QA, and 110QA and make sure that it is in the reset (non-tripped) state (metal shaft is not seen on the trip/reset plunger). 2 If the GFI 35QA, 36QA, 41QA, 42QA, 109QA, and 110QA is tripped (metal shaft is seen on the trip/reset plunger) then reset by depressing the trip/reset plunger until it latches in.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 100 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

3 Make sure that the left and right inner tanks and the center tank contains a minimum of 500 Kg (1,102 lb) of fuel. If necessary, refuel the tanks (Refer to AMM 12-11-28, Page Block 301). (2) Subtask 282170-700-001-001 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-50-20, Page Block 001 24-50-40, Page Block 001 28-21-12, Page Block 501 28-21-36, Page Block 401 (a) Remove the safety clip(s) and/or tag(s) and close/unlock these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 128VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 128VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 128VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 128VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 128VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 128VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 128VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 128VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 128VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 128VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 128VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 128VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)

or

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 101 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 132VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 132VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 132VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 132VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 132VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 132VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 132VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 132VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 132VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 132VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 132VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 132VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)
NOTE (1): For the location of the circuit breakers, refer to AMM 24-50-20, Page Block 001 and AMM 24-50-40, Page Block 001. (b) Do the operational test of the Inner Tanks Booster Pumps (Refer to AMM 28-21-12, Page Block 501). (c) Do the test procedure as specified after the installation of the center tank booster pumps (81QA, 82QA) (Refer to AMM 28-21-36, Page Block 401). (3) Subtask 282170-710-401-004 - Operational Test Manpower Resources Skills ELECTRICAL ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Inner Tank Pump 2 pushbutton switch (P/BSW) (19QA) comes on. - L Inner Tank Pump 2 Selected OFF.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 102 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19 QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 107VU: - Press the test button on top of the L Inner Tank Pump 2 GFI (35QA). - L Inner Tank Pump 2 stops. On Panel 107VU: - the trip/RESET button on GFI (35QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) goes off. - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Inner Tank Pump 2 GFI (35QA) until it latches in. - L Inner Tank Pump 2 GFI (35QA) reset.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. Table 1 - Operational Test Procedure - 35QA L Inner Tank Pump 2
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Inner Tank Pump 1 pushbutton switch (P/BSW) (20QA) comes on. - R Inner Tank Pump 1 Selected OFF.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 103 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 107VU: - Press the test button on top of the R Inner Tank Pump 1 GFI (36QA). - R Inner Tank Pump 1 stops. On Panel 107VU: - the trip/RESET button on GFI (36QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) goes off. - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Inner Tank Pump 1 GFI (36QA) until it latches in. - R Inner Tank Pump 1 GFI (36QA) reset.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. Table 2 - Operational Test Procedure - 36QA R Inner Tank Pump 1
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Inner Tank Pump 1 pushbutton switch (P/BSW) (25QA) comes on. - L Inner Tank Pump 1 Selected OFF.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 104 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 107VU: - Press the test button on top of the L Inner Tank Pump 1 GFI (41QA). - L Inner Tank Pump 1 stops. On Panel 107VU: - the trip/RESET button on GFI (41QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) goes off. - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Inner Tank Pump 1 GFI (41QA) until it latches in. - L Inner Tank Pump 1 GFI (41QA) reset.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. Table 3 - Operational Test Procedure - 41QA L Inner Tank Pump 1
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Inner Tank Pump 2 pushbutton switch (P/BSW) (26QA) comes on. - R Inner Tank Pump 2 Selected OFF.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. On Panel 430VU: - Press (Select in) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 105 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the R Inner Tank Pump 2 GFI (42QA). - R Inner Tank Pump 2 stops. On Panel 107VU: - the trip/RESET button on GFI (42QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 2 P/BSW (26QA). On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) goes off. - OFF legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Inner Tank Pump 2 GFI (42QA) until it latches in. - R Inner Tank Pump 2 GFI (42QA) reset.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. Table 4 - Operational Test Procedure - 42QA R Inner Tank Pump 2
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Center Tank Pump pushbutton switch (P/BSW) (93QA) comes on. - L Center Tank Pump Selected OFF.

On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 106 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the L Center Tank Pump GFI (109QA). - L Center Tank Pump stops. On Panel 107VU: - the trip/RESET button on GFI (109QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). On Panel 430VU: - the FAULT legend lamp on the L Center Tank Pump P/BSW (93QA) goes off. - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Center Tank Pump GFI (109QA) until it latches in. - L Center Tank Pump GFI (109QA) reset.

On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. Table 5 - Operational Test Procedure - 109QA L Center Tank Pump
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Center Tank Pump pushbutton switch (P/BSW) (94QA) comes on. - R Center Tank Pump Selected OFF.

On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 107 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the R Center Tank Pump GFI (110QA). - R Center Tank Pump stops. On Panel 107VU: - the trip/RESET button on GFI (110QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). On Panel 430VU: - the FAULT legend lamp on the R Center Tank Pump P/BSW (94QA) goes off. - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Center Tank Pump GFI (110QA) until it latches in. - R Center Tank Pump GFI (110QA) reset.

On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. Table 6 - Operational Test Procedure - 110QA R Center Tank Pump
**CONF 003 (1) Subtask 282170-840-401-001 - Preparation for Test Procedure Manpower Resources Skills ELECTRICAL References Aircraft Maintenance Manual (AMM) 12-11-28, Page Block 301 Fig. A-UBAAA Ground Fault Interrupter - Tripped/Not Tripped Sheet 01
(a) Refer to Fig. A-UBAAA Sheet 01 1 Inspect the GFI 35QA, 36QA, 41QA, 42QA, 109QA, and 110QA and make sure that it is in the reset (non-tripped) state (metal shaft is not seen on the trip/reset plunger). 2 If the GFI 35QA, 36QA, 41QA, 42QA, 109QA, and 110QA is tripped (metal shaft is seen on the trip/reset plunger) then reset by depressing the trip/reset plunger until it latches in.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 108 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

3 Make sure that the left and right inner tanks and the center tank contains a minimum of 500 Kg (1,102 lb) of fuel. If necessary, refuel the tanks (Refer to AMM 12-11-28, Page Block 301). (2) Subtask 282170-700-001-001 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-50-20, Page Block 001 24-50-40, Page Block 001 28-21-12, Page Block 501 28-21-36, Page Block 401 (a) Remove the safety clip(s) and/or tag(s) and close/unlock these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 128VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 128VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 128VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 128VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 128VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 128VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 128VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 128VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 128VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 128VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 128VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 128VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)

or

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 109 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 132VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 132VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 132VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 132VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 132VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 132VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 132VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 132VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 132VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 132VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 132VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 132VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)
NOTE (1): For the location of the circuit breakers, refer to AMM 24-50-20, Page Block 001 and AMM 24-50-40, Page Block 001. (b) Do the operational test of the Inner Tanks Booster Pumps (Refer to AMM 28-21-12, Page Block 501). (c) Do the test procedure as specified after the installation of the center tank booster pumps (81QA, 82QA) (Refer to AMM 28-21-36, Page Block 401). (3) Subtask 282170-710-401-004 - Operational Test Manpower Resources Skills ELECTRICAL ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Inner Tank Pump 2 pushbutton switch (P/BSW) (19QA) comes on. - L Inner Tank Pump 2 Selected OFF.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 110 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19 QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 107VU: - Press the test button on top of the L Inner Tank Pump 2 GFI (35QA). - L Inner Tank Pump 2 stops. On Panel 107VU: - the trip/RESET button on GFI (35QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) goes off. - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Inner Tank Pump 2 GFI (35QA) until it latches in. - L Inner Tank Pump 2 GFI (35QA) reset.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. Table 1 - Operational Test Procedure - 35QA L Inner Tank Pump 2
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Inner Tank Pump 1 pushbutton switch (P/BSW) (20QA) comes on. - R Inner Tank Pump 1 Selected OFF.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 111 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 107VU: - Press the test button on top of the R Inner Tank Pump 1 GFI (36QA). - R Inner Tank Pump 1 stops. On Panel 107VU: - the trip/RESET button on GFI (36QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) goes off. - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Inner Tank Pump 1 GFI (36QA) until it latches in. - R Inner Tank Pump 1 GFI (36QA) reset.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. Table 2 - Operational Test Procedure - 36QA R Inner Tank Pump 1
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Inner Tank Pump 1 pushbutton switch (P/BSW) (25QA) comes on. - L Inner Tank Pump 1 Selected OFF.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 112 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 107VU: - Press the test button on top of the L Inner Tank Pump 1 GFI (41QA). - L Inner Tank Pump 1 stops. On Panel 107VU: - the trip/RESET button on GFI (41QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) goes off. - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Inner Tank Pump 1 GFI (41QA) until it latches in. - L Inner Tank Pump 1 GFI (41QA) reset.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. Table 3 - Operational Test Procedure - 41QA L Inner Tank Pump 1
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Inner Tank Pump 2 pushbutton switch (P/BSW) (26QA) comes on. - R Inner Tank Pump 2 Selected OFF.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. On Panel 430VU: - Press (Select in) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 113 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the R Inner Tank Pump 2 GFI (42QA). - R Inner Tank Pump 2 stops. On Panel 107VU: - the trip/RESET button on GFI (42QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 2 P/BSW (26QA). On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) goes off. - OFF legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Inner Tank Pump 2 GFI (42QA) until it latches in. - R Inner Tank Pump 2 GFI (42QA) reset.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. Table 4 - Operational Test Procedure - 42QA R Inner Tank Pump 2
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Center Tank Pump pushbutton switch (P/BSW) (93QA) comes on. - L Center Tank Pump Selected OFF.

On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 114 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the L Center Tank Pump GFI (109QA). - L Center Tank Pump stops. On Panel 107VU: - the trip/RESET button on GFI (109QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). On Panel 430VU: - the FAULT legend lamp on the L Center Tank Pump P/BSW (93QA) goes off. - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Center Tank Pump GFI (109QA) until it latches in. - L Center Tank Pump GFI (109QA) reset.

On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. Table 5 - Operational Test Procedure - 109QA L Center Tank Pump
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Center Tank Pump pushbutton switch (P/BSW) (94QA) comes on. - R Center Tank Pump Selected OFF.

On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 115 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the R Center Tank Pump GFI (110QA). - R Center Tank Pump stops. On Panel 107VU: - the trip/RESET button on GFI (110QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). On Panel 430VU: - the FAULT legend lamp on the R Center Tank Pump P/BSW (94QA) goes off. - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Center Tank Pump GFI (110QA) until it latches in. - R Center Tank Pump GFI (110QA) reset.

On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. Table 6 - Operational Test Procedure - 110QA R Center Tank Pump
**CONF 004 (1) Subtask 282170-840-401-002 - Preparation for Test Procedure Manpower Resources Skills ELECTRICAL References Aircraft Maintenance Manual (AMM) 12-11-28, Page Block 301 Fig. A-UBAAA Ground Fault Interrupter - Tripped/Not Tripped Sheet 01
(a) Refer to Fig. A-UBAAA Sheet 01 1 Inspect the GFI 35QA, 36QA, 41QA, 42QA, 109QA, 110QA, 9QN and 10QN and make sure that it is in the reset (non-tripped) state (metal shaft is not seen on the trip/reset plunger). 2 If the GFI 35QA, 36QA, 41QA, 42QA, 109QA, 110QA, 9QN and 10QN is tripped (metal shaft is seen on the trip/reset plunger) then reset by depressing the trip/reset plunger until it latches in.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 116 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

3 Make sure that the left and right inner tanks and the center tank contains a minimum of 500 Kg (1,102 lb) of fuel. If necessary, refuel the tanks (Refer to AMM 12-11-28, Page Block 301). (2) Subtask 282170-700-001-002 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-50-10, Page Block 001 24-50-20, Page Block 001 24-50-40, Page Block 001 28-21-12, Page Block 501 28-21-36, Page Block 401 28-27-00, Page Block 501 (a) Remove the safety clip(s) and/or tag(s) and close/unlock these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/CTL 3QN (1) 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/WARN 5QN (1) 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 101VU FUEL/TRIM TANK/PUMP 1/SUPPLY 1QN (1) 101VU FUEL/TRIM TK/PUMP 2/SUPPLY 2QN (1) 128VU FUEL/TRIM TK/XFR PUMP 2/CTL 4QN (1) 128VU FUEL/TRIM TK/XFR PUMP 2/WARN 6QN (1) 128VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 128VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 128VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 128VU FUEL/R INR TK/PUMP 2/WARN 18QA (1)

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 117 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 128VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 128VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 128VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 128VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 128VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 128VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 128VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)

or PANEL DESIGNATION FIN LOCATION SEE NOTES 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/CTL 3QN (1) 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/WARN 5QN (1) 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 101VU FUEL/TRIM TANK/PUMP 1/SUPPLY 1QN (1) 101VU FUEL/TRIM TK/PUMP 2/SUPPLY 2QN (1) 132VU FUEL/TRIM TK/XFR PUMP 2/CTL 4QN (1) 132VU FUEL/TRIM TK/XFR PUMP 2/WARN 6QN (1) 132VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 132VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 132VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 132VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 132VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 132VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 132VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 132VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 118 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 132VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 132VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 132VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 132VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)
NOTE (1): For the location of the circuit breakers, refer to AMM 24-50-10, Page Block 001, AMM 24-50-20, Page Block 001 and AMM 24-50-40, Page Block 001. (b) Do the operational test of the Inner Tanks Booster Pumps (Refer to AMM 28-21-12, Page Block 501). (c) Do the test procedure as specified after the installation of the center tank booster pumps (81QA, 82QA) (Refer to AMM 28-21-36, Page Block 401). (d) Do the operational test of the Trim Tank Pumps (Refer to AMM 28-27-00, Page Block 501). (3) Subtask 282170-710-401-002 - Operational Test Work Zones and Access Panels Zone Access/Work location 121 Work location 132VU 35-QA 132VU 36-QA 132VU 41-QA 132VU 42-QA 132VU 109-QA 132VU 110-QA 107VU 9-QN 107VU 10-QN Manpower Resources Skills ELECTRICAL WARNING: ACCIDENTAL REARWARD FUEL TRANSFER CAN MOVE THE C OF G AFT OF SAFE LIMIT. MAKE SURE TRIM TANK VALVES ARE SHUT. ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Inner Tank Pump 2 pushbutton switch (P/BSW) (19QA) comes on. - L Inner Tank Pump 2 Selected OFF.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19 QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 119 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 107VU: - Press the test button on top of the L Inner Tank Pump 2 GFI (35QA). - L Inner Tank Pump 2 stops. On Panel 107VU: - the trip/RESET button on GFI (35QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) goes off. - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Inner Tank Pump 2 GFI (35QA) until it latches in. - L Inner Tank Pump 2 GFI (35QA) reset.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. Table 1 - Operational Test Procedure - 35QA L Inner Tank Pump 2
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Inner Tank Pump 1 pushbutton switch (P/BSW) (20QA) comes on. - R Inner Tank Pump 1 Selected OFF.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 120 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 107VU: - Press the test button on top of the R Inner Tank Pump 1 GFI (36QA). - R Inner Tank Pump 1 stops. On Panel 107VU: - the trip/RESET button on GFI (36QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) goes off. - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Inner Tank Pump 1 GFI (36QA) until it latches in. - R Inner Tank Pump 1 GFI (36QA) reset.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. Table 2 - Operational Test Procedure - 36QA R Inner Tank Pump 1
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Inner Tank Pump 1 pushbutton switch (P/BSW) (25QA) comes on. - L Inner Tank Pump 1 Selected OFF.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 121 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the L Inner Tank Pump 1 GFI (41QA). - L Inner Tank Pump 1 stops. On Panel 107VU: - the trip/RESET button on GFI (41QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) goes off. - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Inner Tank Pump 1 GFI (41QA) until it latches in. - L Inner Tank Pump 1 GFI (41QA) reset.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. Table 3 - Operational Test Procedure - 41QA L Inner Tank Pump 1
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Inner Tank Pump 2 pushbutton switch (P/BSW) (26QA) comes on. - R Inner Tank Pump 2 Selected OFF.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. On Panel 430VU: - Press (Select in) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 122 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the R Inner Tank Pump 2 GFI (42QA). - R Inner Tank Pump 2 stops. On Panel 107VU: - the trip/RESET button on GFI (42QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 2 P/BSW (26QA). On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) goes off. - OFF legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Inner Tank Pump 2 GFI (42QA) until it latches in. - R Inner Tank Pump 2 GFI (42QA) reset.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. Table 4 - Operational Test Procedure - 42QA R Inner Tank Pump 2
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Center Tank Pump pushbutton switch (P/BSW) (93QA) comes on. - L Center Tank Pump Selected OFF.

On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 123 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the L Center Tank Pump GFI (109QA). - L Center Tank Pump stops. On Panel 107VU: - the trip/RESET button on GFI (109QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). On Panel 430VU: - the FAULT legend lamp on the L Center Tank Pump P/BSW (93QA) goes off. - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Center Tank Pump GFI (109QA) until it latches in. - L Center Tank Pump GFI (109QA) reset.

On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. Table 5 - Operational Test Procedure - 109QA L Center Tank Pump
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Center Tank Pump pushbutton switch (P/BSW) (94QA) comes on. - R Center Tank Pump Selected OFF.

On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 124 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the R Center Tank Pump GFI (110QA). - R Center Tank Pump stops. On Panel 107VU: - the trip/RESET button on GFI (110QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). On Panel 430VU: - the FAULT legend lamp on the R Center Tank Pump P/BSW (94QA) goes off. - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Center Tank Pump GFI (110QA) until it latches in. - R Center Tank Pump GFI (110QA) reset.

On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. Table 6 - Operational Test Procedure - 110QA R Center Tank Pump
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the FUEL/TRIM TK Pump 1 pushbutton switch (P/BSW) (7QN) comes on. - FUEL/TRIM TK Pump 1 Selected OFF.

On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 1 P/BSW (7QN). - FUEL/TRIM TK Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 1 P/BSW (7QN). - FUEL/TRIM TK Pump 1 stops. On Panel 430VU: - OFF legend lamp on the FUEL/TRIM TK Pump 1 P/BSW (7QN) comes on. On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 1 P/BSW (7QN). - FUEL/TRIM TK Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 125 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the FUEL/TRIM TK Pump 1 GFI (9QN). - FUEL/TRIM TK Pump 1 stops. On Panel 107VU: - the trip/RESET button on GFI (9QN) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the FUEL/TRIM TK Pump 1 P/BSW (7QN) comes on. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 1 P/BSW (7QN). On Panel 430VU: - the FAULT legend lamp on the FUEL/TRIM TK Pump 1 P/BSW (7QN) goes off. - OFF legend lamp on the FUEL/TRIM TK Pump 1 P/BSW (7QN) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the FUEL/TRIM TK Pump 1 GFI (9QN) until it latches in. - FUEL/TRIM TK Pump 1 GFI (9QN) reset.

On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 1 P/BSW (7QN). - FUEL/TRIM TK Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 1 P/BSW (7QN). - FUEL/TRIM TK Pump 1 stops. On Panel 430VU: - OFF legend lamp on the FUEL/TRIM TK Pump 1 P/BSW (7QN) comes on. Table 7 - Operational Test Procedure - 9QN Transfer Control Pump 1
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the FUEL/TRIM TK Pump 2 pushbutton switch (P/BSW) (8QN) comes on. - FUEL/TRIM TK Pump 2 Selected OFF.

On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 2 P/BSW (8QN). - FUEL/TRIM TK Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 2 P/BSW (8QN). - FUEL/TRIM TK Pump 2 stops. On Panel 430VU: - OFF legend lamp on the FUEL/TRIM TK Pump 2 P/BSW (8QN) comes on. On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 2 P/BSW (8QN). - FUEL/TRIM TK Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 126 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the FUEL/TRIM TK Pump 2 GFI (10QN). - FUEL/TRIM TK Pump 2 stops. On Panel 107VU: - the trip/RESET button on GFI (10QN) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the FUEL/TRIM TK Pump 2 P/BSW (8QN) comes on. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 2 P/BSW (8QN). On Panel 430VU: - the FAULT legend lamp on the FUEL/TRIM TK Pump 2 P/BSW (8QN) goes off. - OFF legend lamp on the FUEL/TRIM TK Pump 2 P/BSW (8QN) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the FUEL/TRIM TK Pump 2 GFI (10QN) until it latches in. - FUEL/TRIM TK Pump 2 GFI (10QN) reset.

On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 2 P/BSW (8QN). - FUEL/TRIM TK Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 2 P/BSW (8QN). - FUEL/TRIM TK Pump 2 stops. On Panel 430VU: - OFF legend lamp on the FUEL/TRIM TK Pump 2 P/BSW (8QN) comes on. Table 8 - Operational Test Procedure - 10QN Transfer Control Pump 2
**CONF 005 (1) Subtask 282170-840-401-002 - Preparation for Test Procedure Manpower Resources Skills ELECTRICAL References Aircraft Maintenance Manual (AMM) 12-11-28, Page Block 301 Fig. A-UBAAA Ground Fault Interrupter - Tripped/Not Tripped Sheet 01
(a) Refer to Fig. A-UBAAA Sheet 01 1 Inspect the GFI 35QA, 36QA, 41QA, 42QA, 109QA, 110QA, 9QN and 10QN and make sure that it is in the reset (non-tripped) state (metal shaft is not seen on the trip/reset plunger). 2 If the GFI 35QA, 36QA, 41QA, 42QA, 109QA, 110QA, 9QN and 10QN is tripped (metal shaft is seen on the trip/reset plunger) then reset by depressing the trip/reset plunger until it latches in.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 127 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

3 Make sure that the left and right inner tanks and the center tank contains a minimum of 500 Kg (1,102 lb) of fuel. If necessary, refuel the tanks (Refer to AMM 12-11-28, Page Block 301). (2) Subtask 282170-700-001-002 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-50-10, Page Block 001 24-50-20, Page Block 001 24-50-40, Page Block 001 28-21-12, Page Block 501 28-21-36, Page Block 401 28-27-00, Page Block 501 (a) Remove the safety clip(s) and/or tag(s) and close/unlock these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/CTL 3QN (1) 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/WARN 5QN (1) 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 101VU FUEL/TRIM TANK/PUMP 1/SUPPLY 1QN (1) 101VU FUEL/TRIM TK/PUMP 2/SUPPLY 2QN (1) 128VU FUEL/TRIM TK/XFR PUMP 2/CTL 4QN (1) 128VU FUEL/TRIM TK/XFR PUMP 2/WARN 6QN (1) 128VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 128VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 128VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 128VU FUEL/R INR TK/PUMP 2/WARN 18QA (1)

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 128 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 128VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 128VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 128VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 128VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 128VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 128VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 128VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)

or PANEL DESIGNATION FIN LOCATION SEE NOTES 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/CTL 3QN (1) 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/WARN 5QN (1) 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 101VU FUEL/TRIM TANK/PUMP 1/SUPPLY 1QN (1) 101VU FUEL/TRIM TK/PUMP 2/SUPPLY 2QN (1) 132VU FUEL/TRIM TK/XFR PUMP 2/CTL 4QN (1) 132VU FUEL/TRIM TK/XFR PUMP 2/WARN 6QN (1) 132VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 132VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 132VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 132VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 132VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 132VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 132VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 132VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 129 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 132VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 132VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 132VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 132VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)
NOTE (1): For the location of the circuit breakers, refer to AMM 24-50-10, Page Block 001, AMM 24-50-20, Page Block 001 and AMM 24-50-40, Page Block 001. (b) Do the operational test of the Inner Tanks Booster Pumps (Refer to AMM 28-21-12, Page Block 501). (c) Do the test procedure as specified after the installation of the center tank booster pumps (81QA, 82QA) (Refer to AMM 28-21-36, Page Block 401). (d) Do the operational test of the Trim Tank Pumps (Refer to AMM 28-27-00, Page Block 501). (3) Subtask 282170-710-401-002 - Operational Test Work Zones and Access Panels Zone Access/Work location 121 Work location 132VU 35-QA 132VU 36-QA 132VU 41-QA 132VU 42-QA 132VU 109-QA 132VU 110-QA 107VU 9-QN 107VU 10-QN Manpower Resources Skills ELECTRICAL WARNING: ACCIDENTAL REARWARD FUEL TRANSFER CAN MOVE THE C OF G AFT OF SAFE LIMIT. MAKE SURE TRIM TANK VALVES ARE SHUT. ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Inner Tank Pump 2 pushbutton switch (P/BSW) (19QA) comes on. - L Inner Tank Pump 2 Selected OFF.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19 QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 130 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 107VU: - Press the test button on top of the L Inner Tank Pump 2 GFI (35QA). - L Inner Tank Pump 2 stops. On Panel 107VU: - the trip/RESET button on GFI (35QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) goes off. - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Inner Tank Pump 2 GFI (35QA) until it latches in. - L Inner Tank Pump 2 GFI (35QA) reset.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. Table 1 - Operational Test Procedure - 35QA L Inner Tank Pump 2
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Inner Tank Pump 1 pushbutton switch (P/BSW) (20QA) comes on. - R Inner Tank Pump 1 Selected OFF.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 131 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 107VU: - Press the test button on top of the R Inner Tank Pump 1 GFI (36QA). - R Inner Tank Pump 1 stops. On Panel 107VU: - the trip/RESET button on GFI (36QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) goes off. - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Inner Tank Pump 1 GFI (36QA) until it latches in. - R Inner Tank Pump 1 GFI (36QA) reset.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. Table 2 - Operational Test Procedure - 36QA R Inner Tank Pump 1
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Inner Tank Pump 1 pushbutton switch (P/BSW) (25QA) comes on. - L Inner Tank Pump 1 Selected OFF.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 132 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the L Inner Tank Pump 1 GFI (41QA). - L Inner Tank Pump 1 stops. On Panel 107VU: - the trip/RESET button on GFI (41QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) goes off. - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Inner Tank Pump 1 GFI (41QA) until it latches in. - L Inner Tank Pump 1 GFI (41QA) reset.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. Table 3 - Operational Test Procedure - 41QA L Inner Tank Pump 1
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Inner Tank Pump 2 pushbutton switch (P/BSW) (26QA) comes on. - R Inner Tank Pump 2 Selected OFF.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. On Panel 430VU: - Press (Select in) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 133 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the R Inner Tank Pump 2 GFI (42QA). - R Inner Tank Pump 2 stops. On Panel 107VU: - the trip/RESET button on GFI (42QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 2 P/BSW (26QA). On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) goes off. - OFF legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Inner Tank Pump 2 GFI (42QA) until it latches in. - R Inner Tank Pump 2 GFI (42QA) reset.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 2 P/BSW (26QA). - R Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 2 P/BSW (26QA) comes on. Table 4 - Operational Test Procedure - 42QA R Inner Tank Pump 2
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Center Tank Pump pushbutton switch (P/BSW) (93QA) comes on. - L Center Tank Pump Selected OFF.

On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 134 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the L Center Tank Pump GFI (109QA). - L Center Tank Pump stops. On Panel 107VU: - the trip/RESET button on GFI (109QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). On Panel 430VU: - the FAULT legend lamp on the L Center Tank Pump P/BSW (93QA) goes off. - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Center Tank Pump GFI (109QA) until it latches in. - L Center Tank Pump GFI (109QA) reset.

On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. Table 5 - Operational Test Procedure - 109QA L Center Tank Pump
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Center Tank Pump pushbutton switch (P/BSW) (94QA) comes on. - R Center Tank Pump Selected OFF.

On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 135 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the R Center Tank Pump GFI (110QA). - R Center Tank Pump stops. On Panel 107VU: - the trip/RESET button on GFI (110QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). On Panel 430VU: - the FAULT legend lamp on the R Center Tank Pump P/BSW (94QA) goes off. - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Center Tank Pump GFI (110QA) until it latches in. - R Center Tank Pump GFI (110QA) reset.

On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. Table 6 - Operational Test Procedure - 110QA R Center Tank Pump
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the FUEL/TRIM TK Pump 1 pushbutton switch (P/BSW) (7QN) comes on. - FUEL/TRIM TK Pump 1 Selected OFF.

On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 1 P/BSW (7QN). - FUEL/TRIM TK Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 1 P/BSW (7QN). - FUEL/TRIM TK Pump 1 stops. On Panel 430VU: - OFF legend lamp on the FUEL/TRIM TK Pump 1 P/BSW (7QN) comes on. On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 1 P/BSW (7QN). - FUEL/TRIM TK Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 136 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the FUEL/TRIM TK Pump 1 GFI (9QN). - FUEL/TRIM TK Pump 1 stops. On Panel 107VU: - the trip/RESET button on GFI (9QN) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the FUEL/TRIM TK Pump 1 P/BSW (7QN) comes on. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 1 P/BSW (7QN). On Panel 430VU: - the FAULT legend lamp on the FUEL/TRIM TK Pump 1 P/BSW (7QN) goes off. - OFF legend lamp on the FUEL/TRIM TK Pump 1 P/BSW (7QN) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the FUEL/TRIM TK Pump 1 GFI (9QN) until it latches in. - FUEL/TRIM TK Pump 1 GFI (9QN) reset.

On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 1 P/BSW (7QN). - FUEL/TRIM TK Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 1 P/BSW (7QN). - FUEL/TRIM TK Pump 1 stops. On Panel 430VU: - OFF legend lamp on the FUEL/TRIM TK Pump 1 P/BSW (7QN) comes on. Table 7 - Operational Test Procedure - 9QN Transfer Control Pump 1
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the FUEL/TRIM TK Pump 2 pushbutton switch (P/BSW) (8QN) comes on. - FUEL/TRIM TK Pump 2 Selected OFF.

On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 2 P/BSW (8QN). - FUEL/TRIM TK Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 2 P/BSW (8QN). - FUEL/TRIM TK Pump 2 stops. On Panel 430VU: - OFF legend lamp on the FUEL/TRIM TK Pump 2 P/BSW (8QN) comes on. On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 2 P/BSW (8QN). - FUEL/TRIM TK Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 137 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the FUEL/TRIM TK Pump 2 GFI (10QN). - FUEL/TRIM TK Pump 2 stops. On Panel 107VU: - the trip/RESET button on GFI (10QN) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the FUEL/TRIM TK Pump 2 P/BSW (8QN) comes on. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 2 P/BSW (8QN). On Panel 430VU: - the FAULT legend lamp on the FUEL/TRIM TK Pump 2 P/BSW (8QN) goes off. - OFF legend lamp on the FUEL/TRIM TK Pump 2 P/BSW (8QN) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the FUEL/TRIM TK Pump 2 GFI (10QN) until it latches in. - FUEL/TRIM TK Pump 2 GFI (10QN) reset.

On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 2 P/BSW (8QN). - FUEL/TRIM TK Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 2 P/BSW (8QN). - FUEL/TRIM TK Pump 2 stops. On Panel 430VU: - OFF legend lamp on the FUEL/TRIM TK Pump 2 P/BSW (8QN) comes on. Table 8 - Operational Test Procedure - 10QN Transfer Control Pump 2
**CONF 006 (1) Subtask 282170-840-401-003 - Preparation for Test Procedure Manpower Resources Skills ELECTRICAL References Aircraft Maintenance Manual (AMM) 12-11-28, Page Block 301 Fig. A-UBAAA Ground Fault Interrupter - Tripped/Not Tripped Sheet 01
(a) Refer to Fig. A-UBAAA Sheet 01 1 Inspect the GFI 35QA, 36QA, 41QA, 109QA, 110QA, 9QN and 10QN and make sure that it is in the reset (non-tripped) state (metal shaft is not seen on the trip/reset plunger). 2 If the GFI 35QA, 36QA, 41QA, 109QA, 110QA, 9QN and 10QN is tripped (metal shaft is seen on the trip/reset plunger) then reset by depressing the trip/reset plunger until it latches in.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 138 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

3 Make sure that the left and right inner tanks and the center tank contains a minimum of 500 Kg (1,102 lb) of fuel. If necessary, refuel the tanks (Refer to AMM 12-11-28, Page Block 301). (2) Subtask 282170-700-001-002 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-50-10, Page Block 001 24-50-20, Page Block 001 24-50-40, Page Block 001 28-21-12, Page Block 501 28-21-36, Page Block 401 28-27-00, Page Block 501 (a) Remove the safety clip(s) and/or tag(s) and close/unlock these circuit breakers: PANEL DESIGNATION FIN LOCATION SEE NOTES 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/CTL 3QN (1) 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/WARN 5QN (1) 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 101VU FUEL/TRIM TANK/PUMP 1/SUPPLY 1QN (1) 101VU FUEL/TRIM TK/PUMP 2/SUPPLY 2QN (1) 128VU FUEL/TRIM TK/XFR PUMP 2/CTL 4QN (1) 128VU FUEL/TRIM TK/XFR PUMP 2/WARN 6QN (1) 128VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 128VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 128VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 128VU FUEL/R INR TK/PUMP 2/WARN 18QA (1)

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 139 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 128VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 128VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 128VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 128VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) 128VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 128VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 128VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 128VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)

or PANEL DESIGNATION FIN LOCATION SEE NOTES 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/CTL 3QN (1) 22VU FUEL/TRIM TK/FWD XFR/PUMP 1/WARN 5QN (1) 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA (1) 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA (1) 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA (1) 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA (1) 101VU FUEL/CTR TK/L/PUMP/SUPPLY 99QA (1) 101VU FUEL/CTR TK/R/PUMP/SUPPLY 100QA (1) 101VU FUEL/TRIM TANK/PUMP 1/SUPPLY 1QN (1) 101VU FUEL/TRIM TK/PUMP 2/SUPPLY 2QN (1) 132VU FUEL/TRIM TK/XFR PUMP 2/CTL 4QN (1) 132VU FUEL/TRIM TK/XFR PUMP 2/WARN 6QN (1) 132VU FUEL/L INR TK/PUMP 2/WARN 11QA (1) 132VU FUEL/R INR TK/PUMP 1/WARN 12QA (1) 132VU FUEL/L INR TK/PUMP 1/WARN 17QA (1) 132VU FUEL/R INR TK/PUMP 2/WARN 18QA (1) 132VU FUEL/L INR TK/PUMP 2/CTL 59QA (1) 132VU FUEL/R INR TK/PUMP 1/CTL 60QA (1) 132VU FUEL/CTR TK/L/PUMP/CTL 63QA (1) 132VU FUEL/CTR TK/R/PUMP/CTL 64QA (1) DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 140 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 132VU FUEL/L INR TK/PUMP 1/CTL 69QA (1) 132VU FUEL/R INR TK/PUMP 2/CTL 70QA (1) 132VU FUEL/CTR TK/L/PUMP/WARN 101QA (1) 132VU FUEL/CTR TK/R/PUMP/WARN 102QA (1)
NOTE (1): For the location of the circuit breakers, refer to AMM 24-50-10, Page Block 001, AMM 24-50-20, Page Block 001 and AMM 24-50-40, Page Block 001. (b) Do the operational test of the Inner Tanks Booster Pumps (Refer to AMM 28-21-12, Page Block 501). (c) Do the test procedure as specified after the installation of the center tank booster pumps (81QA, 82QA) (Refer to AMM 28-21-36, Page Block 401). (d) Do the operational test of the Trim Tank Pumps (Refer to AMM 28-27-00, Page Block 501). (3) Subtask 282170-710-401-003 - Operational Test Work Zones and Access Panels Zone Access/Work location 121 Work location 132VU 35-QA 132VU 36-QA 132VU 41-QA 132VU 109-QA 132VU 110-QA 107VU 9-QN 107VU 10-QN Manpower Resources Skills ELECTRICAL WARNING: ACCIDENTAL REARWARD FUEL TRANSFER CAN MOVE THE C OF G AFT OF SAFE LIMIT. MAKE SURE TRIM TANK VALVES ARE SHUT. ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Inner Tank Pump 2 pushbutton switch (P/BSW) (19QA) comes on. - L Inner Tank Pump 2 Selected OFF.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19 QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 141 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 107VU: - Press the test button on top of the L Inner Tank Pump 2 GFI (35QA). - L Inner Tank Pump 2 stops. On Panel 107VU: - the trip/RESET button on GFI (35QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) goes off. - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Inner Tank Pump 2 GFI (35QA) until it latches in. - L Inner Tank Pump 2 GFI (35QA) reset.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 2 P/BSW (19QA). - L Inner Tank Pump 2 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 2 P/BSW (19QA) comes on. Table 1 - Operational Test Procedure - 35QA L Inner Tank Pump 2
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Inner Tank Pump 1 pushbutton switch (P/BSW) (20QA) comes on. - R Inner Tank Pump 1 Selected OFF.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 142 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 107VU: - Press the test button on top of the R Inner Tank Pump 1 GFI (36QA). - R Inner Tank Pump 1 stops. On Panel 107VU: - the trip/RESET button on GFI (36QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). On Panel 430VU: - the FAULT legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) goes off. - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Inner Tank Pump 1 GFI (36QA) until it latches in. - R Inner Tank Pump 1 GFI (36QA) reset.

On Panel 430VU: - Press (Select in) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Inner Tank Pump 1 P/BSW (20QA). - R Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the R Inner Tank Pump 1 P/BSW (20QA) comes on. Table 2 - Operational Test Procedure - 36QA R Inner Tank Pump 1
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Inner Tank Pump 1 pushbutton switch (P/BSW) (25QA) comes on. - L Inner Tank Pump 1 Selected OFF.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 143 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the L Inner Tank Pump 1 GFI (41QA). - L Inner Tank Pump 1 stops. On Panel 107VU: - the trip/RESET button on GFI (41QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). On Panel 430VU: - the FAULT legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) goes off. - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Inner Tank Pump 1 GFI (41QA) until it latches in. - L Inner Tank Pump 1 GFI (41QA) reset.

On Panel 430VU: - Press (Select in) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Inner Tank Pump 1 P/BSW (25QA). - L Inner Tank Pump 1 stops. On Panel 430VU: - OFF legend lamp on the L Inner Tank Pump 1 P/BSW (25QA) comes on. Table 3 - Operational Test Procedure - 41QA L Inner Tank Pump 1
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the L Center Tank Pump pushbutton switch (P/BSW) (93QA) comes on. - L Center Tank Pump Selected OFF.

On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 144 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the L Center Tank Pump GFI (109QA). - L Center Tank Pump stops. On Panel 107VU: - the trip/RESET button on GFI (109QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). On Panel 430VU: - the FAULT legend lamp on the L Center Tank Pump P/BSW (93QA) goes off. - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the L Center Tank Pump GFI (109QA) until it latches in. - L Center Tank Pump GFI (109QA) reset.

On Panel 430VU: - Press (Select in) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the L Center Tank Pump P/BSW (93QA). - L Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the L Center Tank Pump P/BSW (93QA) comes on. Table 4 - Operational Test Procedure - 109QA L Center Tank Pump
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the R Center Tank Pump pushbutton switch (P/BSW) (94QA) comes on. - R Center Tank Pump Selected OFF.

On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 145 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the R Center Tank Pump GFI (110QA). - R Center Tank Pump stops. On Panel 107VU: - the trip/RESET button on GFI (110QA) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). On Panel 430VU: - the FAULT legend lamp on the R Center Tank Pump P/BSW (94QA) goes off. - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the R Center Tank Pump GFI (110QA) until it latches in. - R Center Tank Pump GFI (110QA) reset.

On Panel 430VU: - Press (Select in) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the R Center Tank Pump P/BSW (94QA). - R Center Tank Pump stops. On Panel 430VU: - OFF legend lamp on the R Center Tank Pump P/BSW (94QA) comes on. Table 5 - Operational Test Procedure - 110QA R Center Tank Pump
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the FUEL/TRIM TK Pump 1 pushbutton switch (P/BSW) (7QN) comes on. - FUEL/TRIM TK Pump 1 Selected OFF.

On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 1 P/BSW (7QN). - FUEL/TRIM TK Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 1 P/BSW (7QN). - FUEL/TRIM TK Pump 1 stops. On Panel 430VU: - OFF legend lamp on the FUEL/TRIM TK Pump 1 P/BSW (7QN) comes on. On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 1 P/BSW (7QN). - FUEL/TRIM TK Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 146 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the FUEL/TRIM TK Pump 1 GFI (9QN). - FUEL/TRIM TK Pump 1 stops. On Panel 107VU: - the trip/RESET button on GFI (9QN) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the FUEL/TRIM TK Pump 1 P/BSW (7QN) comes on. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 1 P/BSW (7QN). On Panel 430VU: - the FAULT legend lamp on the FUEL/TRIM TK Pump 1 P/BSW (7QN) goes off. - OFF legend lamp on the FUEL/TRIM TK Pump 1 P/BSW (7QN) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the FUEL/TRIM TK Pump 1 GFI (9QN) until it latches in. - FUEL/TRIM TK Pump 1 GFI (9QN) reset.

On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 1 P/BSW (7QN). - FUEL/TRIM TK Pump 1 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 1 P/BSW (7QN). - FUEL/TRIM TK Pump 1 stops. On Panel 430VU: - OFF legend lamp on the FUEL/TRIM TK Pump 1 P/BSW (7QN) comes on. Table 6 - Operational Test Procedure - 9QN Transfer Control Pump 1
ACTION RESULT On Panel 430VU: - Check that the OFF legend lamp on the FUEL/TRIM TK Pump 2 pushbutton switch (P/BSW) (8QN) comes on. - FUEL/TRIM TK Pump 2 Selected OFF.

On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 2 P/BSW (8QN). - FUEL/TRIM TK Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 2 P/BSW (8QN). - FUEL/TRIM TK Pump 2 stops. On Panel 430VU: - OFF legend lamp on the FUEL/TRIM TK Pump 2 P/BSW (8QN) comes on. On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 2 P/BSW (8QN). - FUEL/TRIM TK Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 147 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

ACTION RESULT On Panel 107VU: - Press the test button on top of the FUEL/TRIM TK Pump 2 GFI (10QN). - FUEL/TRIM TK Pump 2 stops. On Panel 107VU: - the trip/RESET button on GFI (10QN) extends revealing the metallic shaft. On Panel 430VU: - the FAULT legend lamp on the FUEL/TRIM TK Pump 2 P/BSW (8QN) comes on. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 2 P/BSW (8QN). On Panel 430VU: - the FAULT legend lamp on the FUEL/TRIM TK Pump 2 P/BSW (8QN) goes off. - OFF legend lamp on the FUEL/TRIM TK Pump 2 P/BSW (8QN) comes on. On Panel 107VU: - Press (Select in) the trip/RESET plunger on top of the FUEL/TRIM TK Pump 2 GFI (10QN) until it latches in. - FUEL/TRIM TK Pump 2 GFI (10QN) reset.

On Panel 430VU: - Press (Select in) the FUEL/TRIM TK Pump 2 P/BSW (8QN). - FUEL/TRIM TK Pump 2 runs. On Panel 430VU: - OFF legend lamp goes off - FAULT legend lamp comes on and then goes off. On Panel 430VU: - Press (Release out) the FUEL/TRIM TK Pump 2 P/BSW (8QN). - FUEL/TRIM TK Pump 2 stops. On Panel 430VU: - OFF legend lamp on the FUEL/TRIM TK Pump 2 P/BSW (8QN) comes on. Table 7 - Operational Test Procedure - 10QN Transfer Control Pump 2
**CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 282170-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001 52-30-00, Page Block 001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the door 132AZ (Refer to AMM 06-41-52, Page Block 001). (c) Close the FWD Cargo-compartment door 831 (Refer to AMM 52-30-00, Page Block 001 and AMM 06-41-52, Page Block 001).
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 148 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN (d) Remove the access platform(s). (e) Restore the system and the aircraft to the normal operating condition. **CONF 002 (1) Subtask 282170-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001 52-30-00, Page Block 001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the door 132AZ (Refer to AMM 06-41-52, Page Block 001). (c) Close the FWD Cargo-compartment door 831 (Refer to AMM 52-30-00, Page Block 001 and AMM 06-41-52, Page Block 001). (d) Remove the access platform(s). (e) Restore the system and the aircraft to the normal operating condition. **CONF 003 (1) Subtask 282170-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001 52-30-00, Page Block 001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the door 132AZ (Refer to AMM 06-41-52, Page Block 001). (c) Close the FWD Cargo-compartment door 831 (Refer to AMM 52-30-00, Page Block 001 and AMM 06-41-52, Page Block 001). (d) Remove the access platform(s). (e) Restore the system and the aircraft to the normal operating condition.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 149 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN
**CONF 004 (1) Subtask 282170-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001 52-30-00, Page Block 001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the door 132AZ (Refer to AMM 06-41-52, Page Block 001). (c) Close the FWD Cargo-compartment door 831 (Refer to AMM 52-30-00, Page Block 001 and AMM 06-41-52, Page Block 001). (d) Remove the access platform(s). (e) Restore the system and the aircraft to the normal operating condition. **CONF 005 (1) Subtask 282170-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001 52-30-00, Page Block 001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the door 132AZ (Refer to AMM 06-41-52, Page Block 001). (c) Close the FWD Cargo-compartment door 831 (Refer to AMM 52-30-00, Page Block 001 and AMM 06-41-52, Page Block 001). (d) Remove the access platform(s). (e) Restore the system and the aircraft to the normal operating condition. **CONF 006 (1) Subtask 282170-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 150 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001 52-30-00, Page Block 001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the door 132AZ (Refer to AMM 06-41-52, Page Block 001). (c) Close the FWD Cargo-compartment door 831 (Refer to AMM 52-30-00, Page Block 001 and AMM 06-41-52, Page Block 001). (d) Remove the access platform(s). (e) Restore the system and the aircraft to the normal operating condition.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 151 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF ALL

PLUNGER NOT TRIPPED

PLUNGER TRIPPED GFI TRIP/RESET

PLUNGER 107VU

GROUND FAULT INTERRUPTER (GFI) TEST BUTTON



### C 

## B **C B**  

## A FR20

FR1 Z120 

### A

B_SB_282170_7_BAAA_01_00 Figure A-UBAAA - Sheet 01 Ground Fault Interrupter - Tripped/Not Tripped
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 152 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 001 thru 003

FR20

FR1 Z120

B_SB_282170_5_BAAA_01_00 107VU 36QA 41QA 42QA 109QA 110QA 35QA

Figure A-FBAAA - Sheet 01 Location of the Modification
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 153 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 004 thru 006

FR20

FR1 Z120 36QA 41QA 42QA 109QA 110QA 35QA

B_SB_282170_5_BAAB_01_00 9QN 10QN 107VU

Figure A-FBAAB - Sheet 01 Location of the Modification
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 154 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 001 thru 003

(5) (2)

(3) (1)

(4) (3 POS)

(3 POS) (3 POS) (3 POS) (3 POS)

(3 POS) 2
1 5

4 3 

### B **C**

**B C**  **B C** 

**B C**  **B C** 

**B C**  110QA 42QA

41QA 109QA 35QA 36QA

107VU 

## A 

## BEFORE **AFTER**

**B C**  FR20

FR1 Z120 

### A

B_SB_282170_5_BBAA_01_00 Figure A-FBBAA - Sheet 01 Modification of the Equipment in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 155 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 004 thru 006

(5) (2)

(3) (1)

(4) (3 POS)

(3 POS) (3 POS) (3 POS) (3 POS)

(3 POS) 2
1 5

4 3 

### B **C**

**B C**  **B C** 

**B C**  **B C** 

**B C**  110QA 42QA

41QA 109QA 35QA 36QA

107VU 

## A 

## BEFORE **AFTER**

**B C**  FR20

FR1 Z120 

### A

B_SB_282170_5_BBAB_01_00 

### B **C B**  **C**

9QN

10QN

Figure A-FBBAB - Sheet 01 Modification of the Equipment in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 156 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF ALL

Figure A-FWAAA - Sheet 01 Modification of the Wiring of the Relay 35QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 157 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF ALL

Figure A-FWAAA - Sheet 02 Modification of the Wiring of the Relay 35QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 158 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF ALL

END1 LEAD END2 Instructions Zone or

Panel Elec.Ident. Term Terminal P/N Wire Ident. Co Rte Gauge Lenght mm Inch Zone or Panel Elec.Ident. Term Terminal P/N L i n e 1 107VU 35QA−A X 2821−0074 CF24 107VU 105QA−A 3 M1O 2 107VU 35QA−A X1 EN3155−017F1620 2821−0074 CF24 107VU 105QA−A 3 M1N 3 107VU 35QA−A Z 2821−0075 CF24 107VU 269VT 1E M1O 4 107VU 35QA−A X2 EN3155−017F1620 2821−0075 CF24 107VU 269VT 1E M1N 5 107VU 35QA−A 2 2821−0084 B QF16 107VU 1809VC X M1O 6 107VU 35QA−A A2 EN3155−017F1216 2821−0084 B QF16 107VU 1809VC X M1N 7 107VU 35QA−A 6 2821−0085 Y QF16 107VU 1809VC V M1O 8 107VU 35QA−A B2 EN3155−017F1216 2821−0085 Y QF16 107VU 1809VC V M1N 9 107VU 35QA−A 8 2821−0086 R QF16 107VU 1809VC W M1O 10 107VU 35QA−A C2 EN3155−017F1216 2821−0086 R QF16 107VU 1809VC W M1N 11 107VU 35QA−A 1 2821−0201 B QF16 107VU 1815VC X M1O 12 107VU 35QA−A A1 EN3155−017F1216 2821−0201 B QF16 107VU 1815VC X M1N 13 107VU 35QA−A 5 2821−0202 Y QF16 107VU 1815VC V M1O 14 107VU 35QA−A B1 EN3155−017F1216 2821−0202 Y QF16 107VU 1815VC V M1N 15 107VU 35QA−A 7 2821−0203 R QF16 107VU 1815VC W M1O 16 107VU 35QA−A C1 EN3155−017F1216 2821−0203 R QF16 107VU 1815VC W M1N 17 107VU 35QA−A 3 2821−0672 CF24 107VU 1369VT 1F M1O 18 107VU 35QA−A 12 EN3155−017F1620 2821−0672 CF24 107VU 1369VT 1F M1N 19 107VU 35QA−A 4 2821−0932 CF24 107VU 2040VC HH M1O 20 107VU 35QA−A 13 EN3155−017F1620 2821−0932 CF24 107VU 2040VC HH M1N 21 107VU 35QA−A B 2821−0933 CF24 107VU 1369VT 22L M1O 22 107VU 35QA−A 11 EN3155−017F1620 2821−0933 CF24 107VU 1369VT 22L M1N 23 24 25

M1O = OLD HOOK−UP ON END 1 M1N = NEW HOOK−UP ON END 1
Figure A-FHAAA - Sheet 01 Hook-up Chart of the Modification of the Wiring of the Relay 35QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 159 7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 001, 003

Figure A-FWBAA - Sheet 01 Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 160 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 001, 003

Figure A-FWBAA - Sheet 02 Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 161 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 002, 004 thru 006

Figure A-FWBAB - Sheet 01 Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 162 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 002, 004 thru 006

Figure A-FWBAB - Sheet 02 Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 163 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 001, 003

END1 LEAD END2 Instructions Zone or

Panel Elec.Ident. Term Terminal P/N Wire Ident. Co Rte Gauge Lenght mm Inch Zone or Panel Elec.Ident. Term Terminal P/N L i n e 1 107VU 36QA−A X 2821−0120 CF24 107VU 106QA−A 3 M1O 2 107VU 36QA−A X1 EN3155−017F1620 2821−0120 CF24 107VU 106QA−A 3 M1N 3 107VU 36QA−A Z 2821−0121 CF24 107VU 269VT 1F M1O 4 107VU 36QA−A X2 SN3155−017F1620 2821−0121 CF24 107VU 269VT 1F M1N 5 107VU 36QA−A 1 2821−0131 B QF16 107VU 1815VC U M1O 6 107VU 36QA−A A1 EN3155−017F1216 2821−0131 B QF16 107VU 1815VC U M1N 7 107VU 36QA−A 5 2821−0132 Y QF16 107VU 1815VC T M1O 8 107VU 36QA−A B1 EN3155−017F1216 2821−0132 Y QF16 107VU 1815VC T M1N 9 107VU 36QA−A 7 2821−0133 R QF16 107VU 1815VC S M1O 10 107VU 36QA−A C1 EN3155−017F1216 2821−0133 R QF16 107VU 1815VC S M1N 11 107VU 36QA−A 2 2821−0134 B QF16 107VU 1809VC U M1O 12 107VU 36QA−A A2 EN3155−017F1216 2821−0134 B QF16 107VU 1809VC U M1N 13 107VU 36QA−A 6 2821−0135 Y QF16 107VU 1809VC T M1O 14 107VU 36QA−A B2 EN3155−017F1216 2821−0135 Y QF16 107VU 1809VC T M1N 15 107VU 36QA−A 8 2821−0136 R QF16 107VU 1809VC S M1O 16 107VU 36QA−A C2 EN3155−017F1216 2821−0136 R QF16 107VU 1809VC S M1N 17 107VU 36QA−A 3 2821−0676 CF24 107VU 1369VT 1J M1O 18 107VU 36QA−A 12 SN3155−017F1620 2821−0676 CF24 107VU 1369VT 1J M1N 19 107VU 36QA−A 4 2821−0958 CF24 107VU 2040VC GG M1O 20 107VU 36QA−A 13 EN3155−017F1620 2821−0958 CF24 107VU 2040VC GG M1N 21 107VU 36QA−A B 2821−0959 CF24 107VU 1369VT 22M M1O 22 107VU 36QA−A 11 EN3155−017F1620 2821−0959 CF24 107VU 1369VT 22M M1N 23 24 25

M1O = OLD HOOK−UP ON END 1 M1N = NEW HOOK−UP ON END 1
Figure A-FHBAA - Sheet 01 Hook-up Chart of the Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 164 7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 002, 004 thru 006

END1 LEAD END2 Instructions Zone or

Panel Elec.Ident. Term Terminal P/N Wire Ident. Co Rte Gauge Lenght mm Inch Zone or Panel Elec.Ident. Term Terminal P/N L i n e 1 107VU 36QA−A X 2821−0120 CF24 107VU 106QA−A 3 M1O 2 107VU 36QA−A X1 EN3155−017F1620 2821−0120 CF24 107VU 106QA−A 3 M1N 3 107VU 36QA−A Z 2821−0121 CF24 107VU 229VT 6A M1O 4 107VU 36QA−A X2 SN3155−017F1620 2821−0121 CF24 107VU 229VT 6A M1N 5 107VU 36QA−A 1 2821−0131 B QF16 107VU 1815VC U M1O 6 107VU 36QA−A A1 EN3155−017F1216 2821−0131 B QF16 107VU 1815VC U M1N 7 107VU 36QA−A 5 2821−0132 Y QF16 107VU 1815VC T M1O 8 107VU 36QA−A B1 EN3155−017F1216 2821−0132 Y QF16 107VU 1815VC T M1N 9 107VU 36QA−A 7 2821−0133 R QF16 107VU 1815VC S M1O 10 107VU 36QA−A C1 EN3155−017F1216 2821−0133 R QF16 107VU 1815VC S M1N 11 107VU 36QA−A 2 2821−0134 B QF16 107VU 1809VC U M1O 12 107VU 36QA−A A2 EN3155−017F1216 2821−0134 B QF16 107VU 1809VC U M1N 13 107VU 36QA−A 6 2821−0135 Y QF16 107VU 1809VC T M1O 14 107VU 36QA−A B2 EN3155−017F1216 2821−0135 Y QF16 107VU 1809VC T M1N 15 107VU 36QA−A 8 2821−0136 R QF16 107VU 1809VC S M1O 16 107VU 36QA−A C2 EN3155−017F1216 2821−0136 R QF16 107VU 1809VC S M1N 17 107VU 36QA−A 3 2821−0676 CF24 107VU 1369VT 1J M1O 18 107VU 36QA−A 12 SN3155−017F1620 2821−0676 CF24 107VU 1369VT 1J M1N 19 107VU 36QA−A 4 2821−0958 CF24 107VU 2040VC GG M1O 20 107VU 36QA−A 13 EN3155−017F1620 2821−0958 CF24 107VU 2040VC GG M1N 21 107VU 36QA−A B 2821−0959 CF24 107VU 1369VT 22M M1O 22 107VU 36QA−A 11 EN3155−017F1620 2821−0959 CF24 107VU 1369VT 22M M1N 23 24 25

M1O = OLD HOOK−UP ON END 1 M1N = NEW HOOK−UP ON END 1
Figure A-FHBAB - Sheet 01 Hook-up Chart of the Modification of the Wiring of the Relay 36QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 165 7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF ALL

Figure A-FWCAA - Sheet 01 Modification of the Wiring of the Relay 41QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 166 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF ALL

Figure A-FWCAA - Sheet 02 Modification of the Wiring of the Relay 41QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 167 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF ALL

END1 LEAD END2 Instructions Zone or

Panel Elec.Ident. Term Terminal P/N Wire Ident. Co Rte Gauge Lenght mm Inch Zone or Panel Elec.Ident. Term Terminal P/N L i n e 1 107VU 41QA−A X 2821−0028 CF24 107VU 103QA−A 3 M1O 2 107VU 41QA−A X1 EN3155−017F1620 2821−0028 CF24 107VU 103QA−A 3 M1N 3 107VU 41QA−A Z 2821−0029 CF24 107VU 269VT 1D M1O 4 107VU 41QA−A X2 EN3155−017F1620 2821−0029 CF24 107VU 269VT 1D M1N 5 107VU 41QA−A 7 2821−0035 R QF16 107VU 1814VC S M1O 6 107VU 41QA−A C1 EN3155−017F1216 2821−0035 R QF16 107VU 1814VC S M1N 7 107VU 41QA−A 1 2821−0196 B QF16 107VU 1814VC U M1O 8 107VU 41QA−A A1 EN3155−017F1216 2821−0196 B QF16 107VU 1814VC U M1N 9 107VU 41QA−A 5 2821−0197 Y QF16 107VU 1814VC T M1O 10 107VU 41QA−A B1 EN3155−017F1216 2821−0197 Y QF16 107VU 1814VC T M1N 11 107VU 41QA−A 2 2821−0038 B QF16 107VU 1808VC U M1O 12 107VU 41QA−A A2 EN3155−017F1216 2821−0038 B QF16 107VU 1808VC U M1N 13 107VU 41QA−A 6 2821−0041 Y QF16 107VU 1808VC T M1O 14 107VU 41QA−A B2 EN3155−017F1216 2821−0041 Y QF16 107VU 1808VC T M1N 15 107VU 41QA−A 8 2821−0044 R QF16 107VU 1808VC S M1O 16 107VU 41QA−A C2 EN3155−017F1216 2821−0044 R QF16 107VU 1808VC S M1N 17 107VU 41QA−A 3 2821−0668 CF24 107VU 269VT 4D M1O 18 107VU 41QA−A 12 EN3155−017F1620 2821−0668 CF24 107VU 269VT 4D M1N 19 107VU 41QA−A 4 2821−0916 CF24 107VU 427VC C M1O 20 107VU 41QA−A 13 EN3155−017F1620 2821−0916 CF24 107VU 427VC C M1N 21 107VU 41QA−A B 2821−0919 CF24 107VU 1369VT 2J M1O 22 107VU 41QA−A 11 EN3155−017F1620 2821−0919 CF24 107VU 1369VT 2J M1N 23 24 25

M1O = OLD HOOK−UP ON END 1 M1N = NEW HOOK−UP ON END 1
Figure A-FHCAA - Sheet 01 Hook-up Chart of the Modification of the Wiring of the Relay 41QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 168 7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 001 thru 005

Figure A-FWDAA - Sheet 01 Modification of the Wiring of the Relay 42QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 169 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 001 thru 005

Figure A-FWDAA - Sheet 02 Modification of the Wiring of the Relay 42QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 170 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 001 thru 005

END1 LEAD END2 Instructions Zone or

Panel Elec.Ident. Term Terminal P/N Wire Ident. Co Rte Gauge Lenght mm Inch Zone or Panel Elec.Ident. Term Terminal P/N L i n e 1 107VU 42QA−A X 2821−0166 CF24 107VU 104QA−A 3 M1O 2 107VU 42QA−A X1 EN3155−017F1620 2821−0166 CF24 107VU 104QA−A 3 M1N 3 107VU 42QA−A Z 2821−0167 CF24 107VU 269VT 1G M1O 4 107VU 42QA−A X2 EN3155−017F1620 2821−0167 CF24 107VU 269VT 1G M1N 5 107VU 42QA−A 1 2821−0175 B QF16 107VU 1814VC G M1O 6 107VU 42QA−A A1 EN3155−017F1216 2821−0175 B QF16 107VU 1814VC G M1N 7 107VU 42QA−A 5 2821−0176 Y QF16 107VU 1814VC H M1O 8 107VU 42QA−A B1 EN3155−017F1216 2821−0176 Y QF16 107VU 1814VC H M1N 9 107VU 42QA−A 7 2821−0177 R QF16 107VU 1814VC J M1O 10 107VU 42QA−A C1 EN3155−017F1216 2821−0177 R QF16 107VU 1814VC J M1N 11 107VU 42QA−A 2 2821−0178 B QF16 107VU 1808VC F M1O 12 107VU 42QA−A A2 EN3155−017F1216 2821−0178 B QF16 107VU 1808VC F M1N 13 107VU 42QA−A 6 2821−0179 Y QF16 107VU 1808VC E M1O 14 107VU 42QA−A B2 EN3155−017F1216 2821−0179 Y QF16 107VU 1808VC E M1N 15 107VU 42QA−A 8 2821−0180 R QF16 107VU 1808VC D M1O 16 107VU 42QA−A C2 EN3155−017F1216 2821−0180 R QF16 107VU 1808VC D M1N 17 107VU 42QA−A 3 2821−0680 CF24 107VU 269VT 4F M1O 18 107VU 42QA−A 12 EN3155−017F1620 2821−0680 CF24 107VU 269VT 4F M1N 19 107VU 42QA−A 4 2821−0980 CF24 107VU 427VC D M1O 20 107VU 42QA−A 13 EN3155−017F1620 2821−0980 CF24 107VU 427VC D M1N 21 107VU 42QA−A B 2821−0981 CF24 107VU 1369VT 22K M1O 22 107VU 42QA−A 11 EN3155−017F1620 2821−0981 CF24 107VU 1369VT 22K M1N 23 24 25

M1O = OLD HOOK−UP ON END 1 M1N = NEW HOOK−UP ON END 1
Figure A-FHDAA - Sheet 01 Hook-up Chart of the Modification of the Wiring of the Relay 42QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 171 7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 002, 004 thru 006

Figure A-FWEAA - Sheet 01 Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 172 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 002, 004 thru 006

Figure A-FWEAA - Sheet 02 Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 173 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 001

Figure A-FWEAB - Sheet 01 Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 174 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 001

Figure A-FWEAB - Sheet 02 Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 175 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 003

Figure A-FWEAC - Sheet 01 Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 176 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 003

Figure A-FWEAC - Sheet 02 Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 177 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 002, 004 thru 006

END1 LEAD END2 Instructions Zone or

Panel Elec.Ident. Term Terminal P/N Wire Ident. Co Rte Gauge Lenght mm Inch Zone or Panel Elec.Ident. Term Terminal P/N L i n e 1 107VU 109QA−A Z 2821−0559 CF24 107VU 229VT 6K M1O 2 107VU 109QA−A X2 EN3155−017F1620 2821−0559 CF24 107VU 229VT 6K M1N 3 107VU 109QA−A 1 2821−0563 B QF16 107VU 1815VC G M1O 4 107VU 109QA−A A1 EN3155−017F1216 2821−0563 B QF16 107VU 1815VC G M1N 5 107VU 109QA−A 5 2821−0567 Y QF16 107VU 1815VC F M1O 6 107VU 109QA−A B1 EN3155−017F1216 2821−0567 Y QF16 107VU 1815VC F M1N 7 107VU 109QA−A 7 2821−0571 R QF16 107VU 1815VC E M1O 8 107VU 109QA−A C1 EN3155−017F1216 2821−0571 R QF16 107VU 1815VC E M1N 9 107VU 109QA−A 2 2821−0564 B QF16 107VU 1809VC G M1O 10 107VU 109QA−A A2 EN3155−017F1216 2821−0564 B QF16 107VU 1809VC G M1N 11 107VU 109QA−A 6 2821−0568 Y QF16 107VU 1809VC J M1O 12 107VU 109QA−A B2 EN3155−017F1216 2821−0568 Y QF16 107VU 1809VC J M1N 13 107VU 109QA−A 8 2821−0572 R QF16 107VU 1809VC H M1O 14 107VU 109QA−A C2 EN3155−017F1216 2821−0572 R QF16 107VU 1809VC H M1N 15 107VU 109QA−A 3 2821−0662 CF24 107VU 1369VT 1G M1O 16 107VU 109QA−A 12 EN3155−017F1620 2821−0662 CF24 107VU 1369VT 1G M1N 17 107VU 109QA−A 4 2821−0994 CF24 107VU 2040VC FF M1O 18 107VU 109QA−A 13 EN3155−017F1620 2821−0994 CF24 107VU 2040VC FF M1N 19 107VU 109QA−A B 2821−0995 CF24 107VU 269VT 7E M1O 20 107VU 109QA−A 11 EN3155−017F1620 2821−0995 CF24 107VU 269VT 7E M1N 21 107VU 109QA−A X 2821−1002 CF24 107VU 107QA−A 1 M1O 22 107VU 109QA−A X1 EN3155−017F1620 2821−1002 CF24 107VU 107QA−A 1 M1N 23 24 25

M1O = OLD HOOK−UP ON END 1 M1N = NEW HOOK−UP ON END 1
Figure A-FHEAA - Sheet 01 Hook-up Chart of the Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 178 7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 001

END1 LEAD END2 Instructions Zone or

Panel Elec.Ident. Term Terminal P/N Wire Ident. Co Rte Gauge Lenght mm Inch Zone or Panel Elec.Ident. Term Terminal P/N L i n e 1 107VU 109QA−A Z 2821−0559 CF24 107VU 269VT 1B M1O 2 107VU 109QA−A X2 EN3155−017F1620 2821−0559 CF24 107VU 269VT 1B M1N 3 107VU 109QA−A 1 2821−0563 B QF16 107VU 1815VC G M1O 4 107VU 109QA−A A1 EN3155−017F1216 2821−0563 B QF16 107VU 1815VC G M1N 5 107VU 109QA−A 5 2821−0567 Y QF16 107VU 1815VC F M1O 6 107VU 109QA−A B1 EN3155−017F1216 2821−0567 Y QF16 107VU 1815VC F M1N 7 107VU 109QA−A 7 2821−0571 R QF16 107VU 1815VC E M1O 8 107VU 109QA−A C1 EN3155−017F1216 2821−0571 R QF16 107VU 1815VC E M1N 9 107VU 109QA−A 2 2821−0564 B QF16 107VU 1809VC G M1O 10 107VU 109QA−A A2 EN3155−017F1216 2821−0564 B QF16 107VU 1809VC G M1N 11 107VU 109QA−A 6 2821−0568 Y QF16 107VU 1809VC J M1O 12 107VU 109QA−A B2 EN3155−017F1216 2821−0568 Y QF16 107VU 1809VC J M1N 13 107VU 109QA−A 8 2821−0572 R QF16 107VU 1809VC H M1O 14 107VU 109QA−A C2 EN3155−017F1216 2821−0572 R QF16 107VU 1809VC H M1N 15 107VU 109QA−A 3 2821−0662 CF24 107VU 1369VT 1G M1O 16 107VU 109QA−A 12 EN3155−017F1620 2821−0662 CF24 107VU 1369VT 1G M1N 17 107VU 109QA−A 4 2821−0994 CF24 107VU 2040VC FF M1O 18 107VU 109QA−A 13 EN3155−017F1620 2821−0994 CF24 107VU 2040VC FF M1N 19 107VU 109QA−A B 2821−0995 CF24 107VU 269VT 7E M1O 20 107VU 109QA−A 11 EN3155−017F1620 2821−0995 CF24 107VU 269VT 7E M1N 21 107VU 109QA−A X 2821−1002 CF24 107VU 107QA−A 1 M1O 22 107VU 109QA−A X1 EN3155−017F1620 2821−1002 CF24 107VU 107QA−A 1 M1N 23 24 25

M1O = OLD HOOK−UP ON END 1 M1N = NEW HOOK−UP ON END 1
Figure A-FHEAB - Sheet 01 Hook-up Chart of the Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 179 7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 003

END1 LEAD END2 Instructions Zone or

Panel Elec.Ident. Term Terminal P/N Wire Ident. Co Rte Gauge Lenght mm Inch Zone or Panel Elec.Ident. Term Terminal P/N L i n e 1 107VU 109QA−A Z 2821−0559 CF24 107VU 269VT 1B M1O 2 107VU 109QA−A X2 EN3155−017F1620 2821−0559 CF24 107VU 269VT 1B M1N 3 107VU 109QA−A 1 2821−0563 B QF16 107VU 1815VC G M1O 4 107VU 109QA−A A1 EN3155−017F1216 2821−0563 B QF16 107VU 1815VC G M1N 5 107VU 109QA−A 5 2821−0567 Y QF16 107VU 1815VC F M1O 6 107VU 109QA−A B1 EN3155−017F1216 2821−0567 Y QF16 107VU 1815VC F M1N 7 107VU 109QA−A 7 2821−0571 R QF16 107VU 1815VC E M1O 8 107VU 109QA−A C1 EN3155−017F1216 2821−0571 R QF16 107VU 1815VC E M1N 9 107VU 109QA−A 2 2821−0564 B QF16 107VU 1809VC G M1O 10 107VU 109QA−A A2 EN3155−017F1216 2821−0564 B QF16 107VU 1809VC G M1N 11 107VU 109QA−A 6 2821−0568 Y QF16 107VU 1809VC J M1O 12 107VU 109QA−A B2 EN3155−017F1216 2821−0568 Y QF16 107VU 1809VC J M1N 13 107VU 109QA−A 8 2821−0572 R QF16 107VU 1809VC H M1O 14 107VU 109QA−A C2 EN3155−017F1216 2821−0572 R QF16 107VU 1809VC H M1N 15 107VU 109QA−A 3 2821−0662 CF24 107VU 1369VT 1G M1O 16 107VU 109QA−A 12 EN3155−017F1620 2821−0662 CF24 107VU 1369VT 1G M1N 17 107VU 109QA−A 4 2821−0994 CF24 107VU 2040VC FF M1O 18 107VU 109QA−A 13 EN3155−017F1620 2821−0994 CF24 107VU 2040VC FF M1N 19 107VU 109QA−A B 2821−0995 CF24 107VU 269VT 7E M1O 20 107VU 109QA−A 11 EN3155−017F1620 2821−0995 CF24 107VU 269VT 7E M1N 21 107VU 109QA−A X 2821−0996 CF24 107VU 269VT 7N M1O 22 107VU 109QA−A X1 EN3155−017F1620 2821−0996 CF24 107VU 269VT 7N M1N 23 24 25

M1O = OLD HOOK−UP ON END 1 M1N = NEW HOOK−UP ON END 1
Figure A-FHEAC - Sheet 01 Hook-up Chart of the Modification of the Wiring of the Relay 109QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 180 7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 001 thru 002, 004 thru 006

Figure A-FWFAA - Sheet 01 Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 181 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 001 thru 002, 004 thru 006

Figure A-FWFAA - Sheet 02 Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 182 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 003

Figure A-FWFAB - Sheet 01 Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 183 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 003

Figure A-FWFAB - Sheet 02 Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 184 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 001 thru 002, 004 thru 006

END1 LEAD END2 Instructions Zone or

Panel Elec.Ident. Term Terminal P/N Wire Ident. Co Rte Gauge Lenght mm Inch Zone or Panel Elec.Ident. Term Terminal P/N L i n e 1 107VU 110QA−A Z 2821−0607 CF24 107VU 269VT 1A M1O 2 107VU 110QA−A X2 EN3155−017F1620 2821−0607 CF24 107VU 269VT 1A M1N 3 107VU 110QA−A 1 2821−0611 B QF16 107VU 1814VC R M1O 4 107VU 110QA−A A1 EN3155−017F1216 2821−0611 B QF16 107VU 1814VC R M1N 5 107VU 110QA−A 5 2821−0615 Y QF16 107VU 1814VC P M1O 6 107VU 110QA−A B1 EN3155−017F1216 2821−0615 Y QF16 107VU 1814VC P M1N 7 107VU 110QA−A 7 2821−0619 R QF16 107VU 1814VC N M1O 8 107VU 110QA−A C1 EN3155−017F1216 2821−0619 R QF16 107VU 1814VC N M1N 9 107VU 110QA−A 2 2821−0612 B QF16 107VU 1808VC R M1O 10 107VU 110QA−A A2 EN3155−017F1216 2821−0612 B QF16 107VU 1808VC R M1N 11 107VU 110QA−A 6 2821−0616 Y QF16 107VU 1808VC P M1O 12 107VU 110QA−A B2 EN3155−017F1216 2821−0616 Y QF16 107VU 1808VC P M1N 13 107VU 110QA−A 8 2821−0620 R QF16 107VU 1808VC N M1O 14 107VU 110QA−A C2 EN3155−017F1216 2821−0620 R QF16 107VU 1808VC N M1N 15 107VU 110QA−A 3 2821−0664 CF24 107VU 269VT 4E M1O 16 107VU 110QA−A 12 EN3155−017F1620 2821−0664 CF24 107VU 269VT 4E M1N 17 107VU 110QA−A 4 2821−1021 CF24 107VU 427VC G M1O 18 107VU 110QA−A 13 EN3155−017F1620 2821−1021 CF24 107VU 427VC G M1N 19 107VU 110QA−A B 2821−1022 CF24 107VU 269VT 7C M1O 20 107VU 110QA−A 11 EN3155−017F1620 2821−1022 CF24 107VU 269VT 7C M1N 21 107VU 110QA−A X 2821−1026 CF24 107VU 108QA−A 1 M1O 22 107VU 110QA−A X1 EN3155−017F1620 2821−1026 CF24 107VU 108QA−A 1 M1N 23 24 25

M1O = OLD HOOK−UP ON END 1 M1N = NEW HOOK−UP ON END 1
Figure A-FHFAA - Sheet 01 Hook-up Chart of the Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 185 7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 003

END1 LEAD END2 Instructions Zone or

Panel Elec.Ident. Term Terminal P/N Wire Ident. Co Rte Gauge Lenght mm Inch Zone or Panel Elec.Ident. Term Terminal P/N L i n e 1 107VU 110QA−A Z 2821−0607 CF24 107VU 269VT 1A M1O 2 107VU 110QA−A X2 EN3155−017F1620 2821−0607 CF24 107VU 269VT 1A M1N 3 107VU 110QA−A 1 2821−0611 B QF16 107VU 1814VC R M1O 4 107VU 110QA−A A1 EN3155−017F1216 2821−0611 B QF16 107VU 1814VC R M1N 5 107VU 110QA−A 5 2821−0615 Y QF16 107VU 1814VC P M1O 6 107VU 110QA−A B1 EN3155−017F1216 2821−0615 Y QF16 107VU 1814VC P M1N 7 107VU 110QA−A 7 2821−0619 R QF16 107VU 1814VC N M1O 8 107VU 110QA−A C1 EN3155−017F1216 2821−0619 R QF16 107VU 1814VC N M1N 9 107VU 110QA−A 2 2821−0612 B QF16 107VU 1808VC R M1O 10 107VU 110QA−A A2 EN3155−017F1216 2821−0612 B QF16 107VU 1808VC R M1N 11 107VU 110QA−A 6 2821−0616 Y QF16 107VU 1808VC P M1O 12 107VU 110QA−A B2 EN3155−017F1216 2821−0616 Y QF16 107VU 1808VC P M1N 13 107VU 110QA−A 8 2821−0620 R QF16 107VU 1808VC N M1O 14 107VU 110QA−A C2 EN3155−017F1216 2821−0620 R QF16 107VU 1808VC N M1N 15 107VU 110QA−A 3 2821−0664 CF24 107VU 269VT 4E M1O 16 107VU 110QA−A 12 EN3155−017F1620 2821−0664 CF24 107VU 269VT 4E M1N 17 107VU 110QA−A 4 2821−1021 CF24 107VU 427VC G M1O 18 107VU 110QA−A 13 EN3155−017F1620 2821−1021 CF24 107VU 427VC G M1N 19 107VU 110QA−A B 2821−1022 CF24 107VU 269VT 7C M1O 20 107VU 110QA−A 11 EN3155−017F1620 2821−1022 CF24 107VU 269VT 7C M1N 21 107VU 110QA−A X 2821−1023 CF24 107VU 269VT 7J M1O 22 107VU 110QA−A X1 EN3155−017F1620 2821−1023 CF24 107VU 269VT 7J M1N 23 24 25

M1O = OLD HOOK−UP ON END 1 M1N = NEW HOOK−UP ON END 1
Figure A-FHFAB - Sheet 01 Hook-up Chart of the Modification of the Wiring of the Relay 110QA in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 186 7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 005 thru 006

Figure A-FWGAA - Sheet 01 Modification of the Wiring of the Relay 9QN in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 187 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 005 thru 006

Figure A-FWGAA - Sheet 02 Modification of the Wiring of the Relay 9QN in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 188 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 004

Figure A-FWGAB - Sheet 01 Modification of the Wiring of the Relay 9QN in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 189 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 004

Figure A-FWGAB - Sheet 02 Modification of the Wiring of the Relay 9QN in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 190 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 005 thru 006

END1 LEAD END2 Instructions Zone or

Panel Elec.Ident. Term Terminal P/N Wire Ident. Co Rte Gauge Lenght mm Inch Zone or Panel Elec.Ident. Term Terminal P/N L i n e 1 107VU 9QN−A 1 2821−0059 B QF16 107VU 1815VC D M1O 2 107VU 9QN−A A1 EN3155−017F1216 2821−0059 B QF16 107VU 1815VC D M1N 3 107VU 9QN−A 5 2821−0060 Y QF16 107VU 1815VC H M1O 4 107VU 9QN−A B1 EN3155−017F1216 2821−0060 Y QF16 107VU 1815VC H M1N 5 107VU 9QN−A 7 2821−0061 R QF16 107VU 1815VC J M1O 6 107VU 9QN−A C1 EN3155−017F1216 2821−0061 R QF16 107VU 1815VC J M1N 7 107VU 9QN−A 2 2821−0062 B QF16 107VU 1680VC −R M1O 8 107VU 9QN−A A2 EN3155−017F1216 2821−0062 B QF16 107VU 1680VC −R M1N 9 107VU 9QN−A 6 2821−0063 Y QF16 107VU 1680VC −S M1O 10 107VU 9QN−A B2 EN3155−017F1216 2821−0063 Y QF16 107VU 1680VC −S M1N 11 107VU 9QN−A 8 2821−0064 R QF16 107VU 1680VC −T M1O 12 107VU 9QN−A C2 EN3155−017F1216 2821−0064 R QF16 107VU 1680VC −T M1N 13 107VU 9QN−A Z 2821−0068 CF24 107VU 226VT 9G M1O 14 107VU 9QN−A X2 EN3155−017F1620 2821−0068 CF24 107VU 226VT 9G M1N 15 107VU 9QN−A X 2821−0074 CF24 107VU 11QL−A 1 M1O 16 107VU 9QN−A X1 EN3155−017F1620 2821−0074 CF24 107VU 11QL−A 1 M1N 17 107VU 9QN−A 3 2821−1800 CF24 107VU 226VT 9C M1O 18 107VU 9QN−A 12 EN3155−017F1620 2821−1800 CF24 107VU 226VT 9C M1N 19 107VU 9QN−A B 2821−1804 CF24 107VU 709VC −Q M1O 20 107VU 9QN−A 11 EN3155−017F1620 2821−1804 CF24 107VU 709VC −Q M1N 21 22 23 24 25

M1O = OLD HOOK−UP ON END 1 M1N = NEW HOOK−UP ON END 1
Figure A-FHGAA - Sheet 01 Hook-up Chart of the Modification of the Wiring of the Relay 9QN in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 191 7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 004

END1 LEAD END2 Instructions Zone or

Panel Elec.Ident. Term Terminal P/N Wire Ident. Co Rte Gauge Lenght mm Inch Zone or Panel Elec.Ident. Term Terminal P/N L i n e 1 107VU 9QN−A 1 2821−0059 B QF16 107VU 1815VC D M1O 2 107VU 9QN−A A1 EN3155−017F1216 2821−0059 B QF16 107VU 1815VC D M1N 3 107VU 9QN−A 5 2821−0060 Y QF16 107VU 1815VC H M1O 4 107VU 9QN−A B1 EN3155−017F1216 2821−0060 Y QF16 107VU 1815VC H M1N 5 107VU 9QN−A 7 2821−0061 R QF16 107VU 1815VC J M1O 6 107VU 9QN−A C1 EN3155−017F1216 2821−0061 R QF16 107VU 1815VC J M1N 7 107VU 9QN−A 2 2821−0062 B QF16 107VU 1680VC −R M1O 8 107VU 9QN−A A2 EN3155−017F1216 2821−0062 B QF16 107VU 1680VC −R M1N 9 107VU 9QN−A 6 2821−0063 Y QF16 107VU 1680VC −S M1O 10 107VU 9QN−A B2 EN3155−017F1216 2821−0063 Y QF16 107VU 1680VC −S M1N 11 107VU 9QN−A 8 2821−0064 R QF16 107VU 1680VC −T M1O 12 107VU 9QN−A C2 EN3155−017F1216 2821−0064 R QF16 107VU 1680VC −T M1N 13 107VU 9QN−A Z 2821−0068 CF24 107VU 226VT 9G M1O 14 107VU 9QN−A X2 EN3155−017F1620 2821−0068 CF24 107VU 226VT 9G M1N 15 107VU 9QN−A X 2821−0074 CF24 107VU 11QL−A 1 M1O 16 107VU 9QN−A X1 EN3155−017F1620 2821−0074 CF24 107VU 11QL−A 1 M1N 17 107VU 9QN−A 3 2821−0082 CF24 107VU 226VT 9C M1O 18 107VU 9QN−A 12 EN3155−017F1620 2821−0082 CF24 107VU 226VT 9C M1N 19 107VU 9QN−A B 2821−0089 CF24 107VU 709VC −Q M1O 20 107VU 9QN−A 11 EN3155−017F1620 2821−0089 CF24 107VU 709VC −Q M1N 21 22 23 24 25

M1O = OLD HOOK−UP ON END 1 M1N = NEW HOOK−UP ON END 1
Figure A-FHGAB - Sheet 01 Hook-up Chart of the Modification of the Wiring of the Relay 9QN in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 192 7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 005 thru 006

Figure A-FWHAA - Sheet 01 Modification of the Wiring of the Relay 10QN in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 193 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 005 thru 006

Figure A-FWHAA - Sheet 02 Modification of the Wiring of the Relay 10QN in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 194 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 004

Figure A-FWHAB - Sheet 01 Modification of the Wiring of the Relay 10QN in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 195 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 004

Figure A-FWHAB - Sheet 02 Modification of the Wiring of the Relay 10QN in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 196 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 005 thru 006

END1 LEAD END2 Instructions Zone or

Panel Elec.Ident. Term Terminal P/N Wire Ident. Co Rte Gauge Lenght mm Inch Zone or Panel Elec.Ident. Term Terminal P/N L i n e 1 107VU 10QN−A 1 2821−0023 B QF16 107VU 1814VC A M1O 2 107VU 10QN−A A1 EN3155−017F1216 2821−0023 B QF16 107VU 1814VC A M1N 3 107VU 10QN−A 5 2821−0024 Y QF16 107VU 1814VC B M1O 4 107VU 10QN−A B1 EN3155−017F1216 2821−0024 Y QF16 107VU 1814VC B M1N 5 107VU 10QN−A 7 2821−0025 R QF16 107VU 1814VC C M1O 6 107VU 10QN−A C1 EN3155−017F1216 2821−0025 R QF16 107VU 1814VC C M1N 7 107VU 10QN−A 2 2821−0026 B QF16 107VU 1825VC −N M1O 8 107VU 10QN−A A2 EN3155−017F1216 2821−0026 B QF16 107VU 1825VC −N M1N 9 107VU 10QN−A 6 2821−0027 Y QF16 107VU 1825VC −P M1O 10 107VU 10QN−A B2 EN3155−017F1216 2821−0027 Y QF16 107VU 1825VC −P M1N 11 107VU 10QN−A 8 2821−0028 R QF16 107VU 1825VC −Q M1O 12 107VU 10QN−A C2 EN3155−017F1216 2821−0028 R QF16 107VU 1825VC −Q M1N 13 107VU 10QN−A Z 2821−0032 CF24 107VU 226VT 9B M1O 14 107VU 10QN−A X2 EN3155−017F1620 2821−0032 CF24 107VU 226VT 9B M1N 15 107VU 10QN−A X 2821−0038 CF24 107VU 12QL−A 1 M1O 16 107VU 10QN−A X1 EN3155−017F1620 2821−0038 CF24 107VU 12QL−A 1 M1N 17 107VU 10QN−A 3 2821−1799 CF24 107VU 226VT 9A M1O 18 107VU 10QN−A 12 EN3155−017F1620 2821−1799 CF24 107VU 226VT 9A M1N 19 107VU 10QN−A B 2821−1803 CF24 107VU 427VC W M1O 20 107VU 10QN−A 11 EN3155−017F1620 2821−1803 2M CF24 105VU 427VC W M1N 21 22 23 24 25

M1O = OLD HOOK−UP ON END 1 M1N = NEW HOOK−UP ON END 1
Figure A-FHHAA - Sheet 01 Hook-up Chart of the Modification of the Wiring of the Relay 10QN in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 197 7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN

**CONF 004

END1 LEAD END2 Instructions Zone or

Panel Elec.Ident. Term Terminal P/N Wire Ident. Co Rte Gauge Lenght mm Inch Zone or Panel Elec.Ident. Term Terminal P/N L i n e 1 107VU 10QN−A 1 2821−0023 B QF16 107VU 1814VC A M1O 2 107VU 10QN−A A1 EN3155−017F1216 2821−0023 B QF16 107VU 1814VC A M1N 3 107VU 10QN−A 5 2821−0024 Y QF16 107VU 1814VC B M1O 4 107VU 10QN−A B1 EN3155−017F1216 2821−0024 Y QF16 107VU 1814VC B M1N 5 107VU 10QN−A 7 2821−0025 R QF16 107VU 1814VC C M1O 6 107VU 10QN−A C1 EN3155−017F1216 2821−0025 R QF16 107VU 1814VC C M1N 7 107VU 10QN−A 2 2821−0026 B QF16 107VU 1825VC −N M1O 8 107VU 10QN−A A2 EN3155−017F1216 2821−0026 B QF16 107VU 1825VC −N M1N 9 107VU 10QN−A 6 2821−0027 Y QF16 107VU 1825VC −P M1O 10 107VU 10QN−A B2 EN3155−017F1216 2821−0027 Y QF16 107VU 1825VC −P M1N 11 107VU 10QN−A 8 2821−0028 R QF16 107VU 1825VC −Q M1O 12 107VU 10QN−A C2 EN3155−017F1216 2821−0028 R QF16 107VU 1825VC −Q M1N 13 107VU 10QN−A Z 2821−0032 CF24 107VU 226VT 9B M1O 14 107VU 10QN−A X2 EN3155−017F1620 2821−0032 CF24 107VU 226VT 9B M1N 15 107VU 10QN−A X 2821−0038 CF24 107VU 12QL−A 1 M1O 16 107VU 10QN−A X1 EN3155−017F1620 2821−0038 CF24 107VU 12QL−A 1 M1N 17 107VU 10QN−A 3 2821−0079 CF24 107VU 226VT 9A M1O 18 107VU 10QN−A 12 EN3155−017F1620 2821−0079 CF24 107VU 226VT 9A M1N 19 107VU 10QN−A B 2821−0081 CF24 107VU 427VC W M1O 20 107VU 10QN−A 11 EN3155−017F1620 2821−0081 2M CF24 105VU 427VC W M1N 21 22 23 24 25

M1O = OLD HOOK−UP ON END 1 M1N = NEW HOOK−UP ON END 1
Figure A-FHHAB - Sheet 01 Hook-up Chart of the Modification of the Wiring of the Relay 10QN in the LH Relay Box 107VU.
DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 198 7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN REPORTING SHEET 

### TITLE: FUEL SYSTEM - INTRODUCE GROUND FAULT INTERRUPTER (GFI) MODIFICATION No.: 13382H5685 Please complete the appropriate item (A or B): A - SB WILL BE embodied YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:

B - SB HAS BEEN embodied on aircraft: Operator comments:
From Airline: Name/Title: Signature: Date: If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either: Modification Operational Impact (MOI), if available YES/NO Or : Intermediate revision YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - Updating of maintenance documentation to show pre and post SB data. - Updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. Please return this completed sheet to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: SDC32 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: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 1 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A310 SERVICE BULLETIN QUALITY PERCEPTION FORM 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 further 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 4321 - Quality rating of the Accomplishment Instructions 4321 - Quality rating of the Illustrations 4321 - 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 Operator Supplied X Mod/Inspection X Manpower X Industry support X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments:

Operator: Date: Name/Title: Please return this form to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: Feb 28/12 SERVICE BULLETIN No.: A310-28-2170 REVISION No.: 00 - Feb 28/12 Page: 1 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.