@A310

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

MANDATORY MANDATORY MANDATORY

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

MANDATORY MANDATORY MANDATORY

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 (where

fitted) 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 (Refer to 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 (Refer to 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 (Refer to 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 (Refer to 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 (Refer to 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 (Refer to 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.