A300-600 A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 28

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

ELECTRICAL BONDING

MODIFICATION No. : 12495H5555

This page transmits Revision No. 03 of Service Bulletin No. A300-28-6064

ADDITIONAL WORK

Additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No. 03 issued to include improvements further to discrepancies found during accomplishment.

CHANGES

SUMMARY :

- EFFECTIVITY

. Operators 09V and 98W have been deleted. Operator MXU has been added.

- MANPOWER

. Additional work has been added.

PLANNING INFORMATION :

- EFFECTIVITY

. 1.A. Effectivity has been updated. Kits B11 and B19 have been raised in issue. Config. 08 note

added. Additional work notes have been added.

- DESCRIPTION

. 1.D.(7) Additional work has been added.

- Accomplishment Timescale

. 1.E.(2)(d) Additional work has been added.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 1 of 4

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- MANPOWER

. 1.G. Additional work has been added. Kits B11 and B19 have been raised in issue.

- REFERENCES

. 1.J. Service Bulletin A300-28-6089.

MATERIAL INFORMATION :

- MATERIAL - PRICE AND AVAILABILITY

. 2.A. Kit B11 and B19 have been raised in issue.

- LIST OF COMPONENTS

. 2.C. Kit B11 has been raised in issue. Item 60 has been replace with Item 70.

. 2.C. Kit B19 has been raised in issue.

. 2.D.(2) Additional work has been added.

ACCOMPLISHMENT INSTRUCTIONS :

- Preparation

. 3.A.(1)(j) Additional work has been added.

- MODIFICATION

. 3.B.(1)(a) Note has been updated.

. 3.B.(5)(a) Text corrected. Kits B11 and B19 have been raised in issue.

. 3.B.(9)(b)2 Item (4) has been corrected to Item (11).

. 3.B.(16) Kit B11 has been raised in issue.

. 3.B.(16)(a) Kit B11 has been raised in issue.

. 3.B.(16)(a)6 Item 60 has been replaced with Item 70

. 3.B.(16)(a)7 Item 60 has been replaced with Item 70.

. 3.B.(16)(c) Kit B11 has been raised in issue.

. 3.B.(16)(d) Kit B11 has been raised in issue.

. 3.B.(23) Kit B19 has been raised in issue.

. 3.B.(23)(a)1 Item 70 has been replaced with Item 71.

. 3.B.(23)(a)3 Item 70 has been replaced with Item 71.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

.

- TESTS

. 3.C.(5) Additional work has been added.

- CLOSE-UP

. 3.D.(3) Additional work has been added.

- Figure 6

. Figure 6, Sheet 2 : Detail 25, 2 points added.

- Figure 7

. Figure 7, Sheet 1 : Item 25, 6 points become 8 points.

- Figure 10

. Figure 10, Sheet 4 updated.

- Figure 30

. Sheet 1 Item 70 has been replaced with Item 71.

- Figure 31

. Sheet 2 washer has been added.

- Figure 42

. Item 60 has been replaced with Item 70.

- Figure 50

. Figure added for additional work.

- Figure 51

. Figure added for additional work.

- Figure 52

. Figure added for additional work.

FILING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 3

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A300-600 A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

HISTORY OF PREVIOUS REVISIONS

Revision No. 01 was issued to:

- incorporate the comments of an airline request,

- update the effectivity,

- apply refuel/defuel valve modification on the LH wing for all aircraft.

Other minor changes to the new Service Bulletin format were added.

This Service Bulletin has been revised following operator queries on figure references, item numbers,

bolt lengths and effectivity applicability.

Revision No. 02 was issued to include improvements further to discrepancies found during

accomplishment.

REVISION SEQUENCE

ORIGINAL : Jul 28/05

REVISION No. : 01 - Apr 03/07

REVISION No. : 02 - Mar 10/08

REVISION No. : 03 - Dec 15/08

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 4

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is

not approved for modification of the aircraft

MANDATORY MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 28

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

ELECTRICAL BONDING

MODIFICATION No. : 12495H5555

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

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

bonding in the aircraft fuel tanks.

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

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

bonding points in the wings fuel tanks and center tank.

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

electrical bonding protection of all the equipment in the fuel tanks for the design life goal of the aircraft.

It is Mandatory to accomplish this modification before the 31st December 2010.

This Service Bulletin has been validated on A300-600 aircraft MSN 0569.

EVALUATION TABLE

COMPLIANCE Mandatory CANCELS INSPECTION SB No

POTENTIAL AD Yes A/C OPERATION AFFECTED No

RELIABILITY AFFECTED No PAX COMFORT AFFECTED No

COST SAVING No ETOPS AFFECTED No

STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED No

DEFUEL/VENTILATION Yes KIT PRICE (USD) Refer to SB

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 12495H5555

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 1 of 4

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

SUMMARY

As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural

strength, reliability, operational characteristics, affecting the airworthiness of the product. All other changes

are Major changes.

EFFECTIVITY

This Service Bulletin is applicable to these operators:

AAL AAW ABD AMU CES CSN DLH EGN F2I FDX GXY IRA JAL KAC KAL LAA MON MSR MXU OAL

OHY QTR SUD TAR THA UPS

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : None

OEB : None

AOT : None

SIL : 28-072

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

OTHERS : None

NATURE OF THE WORK

AIRCRAFT : Yes

EQUIPMENT : No

HARD : No

SOFT : No

OBRM : No

MANPOWER

Center Tank, Kit 286064A01R05

TOTAL MANHOURS 114.5

ELAPSED TIME (HOURS) 73.0

Center Tank, Kit 286064A02R02

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

SUMMARY

TOTAL MANHOURS 114.5

ELAPSED TIME (HOURS) 73.0

Center Tank, Kit 286064A03R00

TOTAL MANHOURS 104.5

ELAPSED TIME (HOURS) 63.0

LH and RH Wing Fuel Tanks - Config. 08 (Post Mod. 12226 Aircraft only)

TOTAL MANHOURS 20

ELAPSED TIME (HOURS) 10.0

LH and RH Wing Fuel Tanks - All other Aircraft

TOTAL MANHOURS 226.0*

ELAPSED TIME (HOURS) 114.5

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

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

ADDITIONAL WORK (Introduced by Rev 01)

TOTAL MANHOURS 2.0

ELAPSED TIME (HOURS) 2.0

ADDITIONAL WORK

TOTAL MANHOURS 62.5

ELAPSED TIME (HOURS) 31.0

MATERIAL INFORMATION

AIRCRAFT DATA

Center Tank - Kit 286064A01R05 thru Kit 286064A03R00:

Bonding leads, clamps, rivets, bolts, nuts and washers.

Wings Fuel Tanks Equipment - Kit 286064B01R05 thru Kit 286064B28R01:

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 3

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

SUMMARY

Bonding leads, clamps, bolts, nuts, washers and drain attachment plates.

NOTE : Kit 286064B24 has not been used.

ADDITIONAL WORK (Introduced by Rev 01)

Wings Fuel Tanks Equipment - Kit 286064B39R00:

Bonding leads, nuts and screws.

APPENDICES

None

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 4

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 28

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

ELECTRICAL BONDING

MODIFICATION No. : 12495H5555

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property

of AIRBUS; no intellectual property right or license 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 part to third parties and shall not be duplicated in any manner

(except for the purpose of performing the tasks described hereunder and provided that any recipient of such

document shall comply with the conditions herein), without AIRBUS prior written consent.

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Models

B4-601 B4-603 B4-605R B4-620 B4-622 B4-622R C4-605R/F C4-620 F4-605R F4-622R

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft MSN:

0252 0284 0294 0301 0307 0312 0317 0321 0336 0341 0344 0348 0351 0354 0358

0361 0365 0368 0380 0384 0388 0395 0398 0401 0405 0408 0411 0414 0417 0423

0459-0466 0469-0471 0474 0477 0479 0505-0518 0521 0525 0529 0530 0532 0533

0536 0540 0543 0546 0553-0561 0563 0566 0569 0572 0575 0577 0579 0581 0582

0584 0601-0619 0621 0623 0625-0633 0635 0637 0639 0641 0643 0645 0657 0659

0662 0664 0666 0668 0670 0673 0675 0677 0679 0681 0683 0685 0688 0692 0694

0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721-0750

0752-0764 0766-0775 0777-0794 0797 0799-0841

(b) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the

time of issue in accordance with the information available to AIRBUS. Any future

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 1 of 251

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

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

AAL 0423 0459 0460 0461 0462 0463 0465 0466 0469 0470 0471 0474

0506 0507 0508 0509 0510 0511 0512 0513 0514 0515 0516 0517

0606 0610 0612 0615 0619 0626 0639 0643 0645 0675

AAW 0354

ABD 0529 0557 0755 0758

AMU 0677 0743

CES 0521 0525 0532 0707 0725 0732 0741 0746 0754 0763

CSN 0733 0734 0739 0750 0756 0762

DLH 0380 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623

0701 0773

EGN 0555 0625

F2I 0284 0294 0301 0307 0312 0317 0321 0336 0341 0348 0351

FDX 0358 0361 0365 0388 0417 0477 0479 0530 0536 0543 0559 0572

0575 0579 0581 0611 0613 0630 0633 0657 0659 0668 0709

0713 0715 0726 0728 0735 0736 0738 0742 0745 0748 0752

0757 0759 0760 0761 0766 0768 0769 0771 0772 0774 0777

0778 0779 0780 0781 0789 0790 0791 0792 0793 0794 0799

0800 0801 0802 0803 0804

GXY 0533

IRA 0632 0696 0723 0727

JAL 0602 0617 0621 0637 0641 0670 0679 0683 0703 0711 0724 0729

0730 0737 0740 0753 0770 0783 0797 0836 0837 0838

KAC 0344 0673 0694 0699 0719 0721

KAL 0582 0609 0627 0631 0662 0685 0692 0717 0722 0731

LAA 0601 0616

MON 0540 0556 0604 0605

MSR 0561 0607

MXU 0767 0788

OAL 0603

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 2

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A300-600 A300-600

SERVICE BULLETIN

OPERATOR MSN

OHY 0584 0744 0747 0749 0764

QTR 0554 0560 0614 0664 0688

SUD 0252 0666 0775

TAR 0505 0558 0563

THA 0368 0384 0395 0398 0464 0518 0566 0569 0577 0628 0629 0635

0681 0705 0782 0784 0785 0786 0787

UPS 0805 0806 0807 0808 0809 0810 0811 0812 0813 0814 0815 0816

0817 0818 0819 0820 0821 0822 0823 0824 0825 0826 0827 0828

0829 0830 0831 0832 0833 0834 0835 0839 0840 0841

(c) Effectivity by MSN and Kit/Configuration

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

0423 0459-0466 0469-0471 0474 0506-0518 0529 0533 0536 0540 0555-0557 0559

0561 0566 0569 0572 0575 0577 0579 0581-0582 0584 0603-0610 0612 0615 0619

0625-0629 0631-0632 0635 0639 0643 0645 0657 0659 0662 0666 0673 0675 0677

0681 0685 0692 0694 0701 0705 0717 0722-0723 0725

KIT No. QTY PER A/C CONFIGURATION

286064A01R05 1 01

NOTE(01) Kit 286064A01R05 concerns the modification of the electrical bonding in

the center tank and is valid for aircraft on which Mod. No. 8692S20032

(FUEL - SECTION - INTRODUCE MOULDED PARTS ON A300/600)

is not embodied.

NOTE(02) Additional work is required by this revision for aircraft modified by

Revision 00 or 01 or 02.

NOTE(03) Config. 01 is valid for aircraft on which Mod. No. 04801H5078 (FUEL -

INSTALL TRIM TANK SYSTEM) is embodied.

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

0477 0479 0505 0521 0525 0530 0532 0543 0546 0553-0554 0558 0560 0563

0601-0602 0611 0613-0614 0616-0618 0621 0623 0630 0633 0637 0641 0664 0668

0670 0679 0683 0688 0696 0699 0703 0707 0709 0711 0713 0715 0719 0721 0724

KIT No. QTY PER A/C CONFIGURATION

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 3

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

286064A01R05 1 01

286064A03R00 1 01

NOTE(01) Kit 286064A01R05 concerns the modification of the electrical bonding in

the center tank and is valid for aircraft on which Mod. No. 8692S20032

(FUEL - SECTION - INTRODUCE MOULDED PARTS ON A300/600)

is not embodied.

NOTE(02) Additional work is required by this revision for aircraft modified by

Revision 00 or 01 or 02.

NOTE(03) Config. 01 is valid for aircraft on which Mod. No. 04801H5078 (FUEL -

INSTALL TRIM TANK SYSTEM) is embodied.

NOTE(04) Kit 286064A03R00 concerns the modification of the electrical bonding in

the center tank and is valid for aircraft on which Mod. No. 12315S22009

(FUEL - FUEL PUMP SYSTEM - ADD BONDING LEAD ON RH AND

LH CENTER TANK BOOSTER PUMP CANISTERS) is not embodied

and for aircraft on which Mod. No. 12314H5524 (FUEL - FUEL PUMP

SYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMP

CANISTERS) or Mod. No. 13041H5657 (FUEL - FUEL PUMP

SYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMP

CANISTERS) are not embodied or Service Bulletin No. A300-28-6069

or A300-28-6089 are not accomplished.

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

0252 0284 0294 0301 0307 0312 0317 0321 0336 0341 0344 0348 0351 0354 0358

0361 0365 0368 0380 0384 0388 0395 0398 0401 0405 0408 0411 0414 0417

KIT No. QTY PER A/C CONFIGURATION

286064A01R05 1 02

286064A03R00 1 02

NOTE(01) Kit 286064A01R05 concerns the modification of the electrical bonding in

the center tank and is valid for aircraft on which Mod. No. 8692S20032

(FUEL - SECTION - INTRODUCE MOULDED PARTS ON A300/600)

is not embodied.

NOTE(02) Additional work is required by this revision for aircraft modified by

Revision 00 or 01 or 02.

NOTE(03) Config. 02 is valid for aircraft on which Mod. No. 04801H5078 (FUEL -

INSTALL TRIM TANK SYSTEM) is not embodied.

NOTE(04) Kit 286064A03R00 concerns the modification of the electrical bonding in

the center tank and is valid for aircraft on which Mod. No. 12315S22009

(FUEL - FUEL PUMP SYSTEM - ADD BONDING LEAD ON RH AND

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 4

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A300-600 A300-600

SERVICE BULLETIN

LH CENTER TANK BOOSTER PUMP CANISTERS) is not embodied

and for aircraft on which Mod. No. 12314H5524 (FUEL - FUEL PUMP

SYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMP

CANISTERS) or Mod. No. 13041H5657 (FUEL - FUEL PUMP

SYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMP

CANISTERS) are not embodied or Service Bulletin No. A300-28-6069

or A300-28-6089 are not accomplished.

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

0726-0750 0752-0764 0766-0775 0777-0794 0797 0799-0841

KIT No. QTY PER A/C CONFIGURATION

286064A02R02 1 None

NOTE(01) Kit 286064A02R02 concerns the modification of the electrical bonding in

the center tank and is valid for aircraft on which Mod. No. 8692S20032

(FUEL - SECTION - INTRODUCE MOULDED PARTS ON A300/600)

is embodied.

NOTE(02) Additional work is required by this revision for aircraft modified by

Revision 00 or 01 or 02.

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

0252 0284 0294 0301 0307 0312 0317 0321 0336 0341 0344 0348 0351 0354 0358

0361 0365 0368 0380 0384 0388 0395 0398 0401 0405 0408 0411 0414 0417 0423

0459-0466 0469-0471 0474 0477 0479 0505-0518 0521 0525 0529-0530 0532-0533

0536 0540 0543 0546 0553-0561 0563 0566 0569 0572 0575 0577 0579 0581-0582

0584 0601-0619 0621 0623 0625-0633 0635 0637 0639 0641 0643 0645 0657 0659

0662 0664 0666 0668 0670 0673 0675 0677 0679 0681 0683 0685 0688 0692 0694

0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721-0750

0752-0764 0766-0775 0777-0794 0797 0799-0804

KIT No. QTY PER A/C CONFIGURATION

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 5

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

286064B01R05 2 None

286064B02R02 4 01

286064B02R02 12 02

286064B03R03 2 None

286064B04R03 2 None

286064B05R01 2 None

286064B06R03 2 None

286064B07R01 1 None

286064B08R03 2 None

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 6

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION

286064B09R04 2 None

286064B10R01 2 None

286064B11R05 2 None

286064B12R01 2 None

286064B13R03 2 None

286064B14R02 2 None

286064B15R04 2 None

286064B16R03 2 None

286064B17R01 2 None

286064B18R04 2 None

286064B19R02 2 None

286064B21R01 2 04

286064B22R05 2 03

286064B23R01 2 06

286064B25R01 2 07

286064B26R01 12 02

286064B27R01 1 02

286064B28R01 1 02

286064B39R00

(ADDITIONAL

WORK only)

1 05

NOTE : Config. 01 - Post SB A300-57-6070 (Mod. 11055).

Config. 02 - Pre SB A300-57-6070 (Mod. 11055).

Config. 03 - Post Mod. 08680 and Post SB A300-28-6028 (Mod. 08679)

aircraft.

Config. 04 - Post Mod. 06128 aircraft.

Config. 06 - Pre Mod. 06708 aircraft.

Config. 07 - Pre Mod. 04607 aircraft.

Kit 286064B39R00 is only applicable to Additional Work described in

Rev 01 of this Service Bulletin.

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

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 7

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

0805-0811

KIT No. QTY PER A/C CONFIGURATION

286064B20R06 2 08

NOTE : Config. 08 - Post Mod. 12226 aircraft.

NOTE : Mod. No. 12365H5540 (FUEL - GENERAL - REVISE ELECTRICAL

BONDING OF EQUIPMENT IN INNER WING FUEL TANKS) is

embodied on MSN 0812 and subsequent.

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

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

the electrical bonding in the aircraft fuel tanks.

This Service Bulletin has been validated on A300-600 aircraft MSN 0569.

(2) Objective/Action

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

electrical bonding of the equipment in the fuel tanks.

This modification consists of installing additional bonding leads and electrical bonding

points in the wings fuel tanks and center tank.

(3) Advantages

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

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

design life goal of the aircraft.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to:

(1) Center Tank - Kit 286064A01R05, Kit 286064A02R02 and Kit 286064A03R00

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 8

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

(a) Defuel and vent the center fuel tanks.

(b) Get access to the center fuel tanks.

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

(2) Center Tank Kit 286064A01R05

(a) Modify or install the bonding points.

(3) Center Tank Kit 286064A02R02

(a) Modify or install the bonding points.

(4) Center Tank Kit 286064A03R00

(a) Install the bonding points.

(5) LH and RH Wing Fuel Tanks - Kit 286064B01R05 thru Kit 286064B28R01

NOTE : Kit 286064B24 has not been used.

(a) Defuel and vent the wings fuel tanks.

(b) Fully extend the slats.

(c) Get access to the applicable equipment in the wings fuel tanks (rib bay 1-2 thru

to rib bay 27-28, LH and RH wing) for all Configs except Config. 08. For Config.

08 rib bays 1-2 only.

(d) Install additional bonding leads and electrical bonding points.

(e) Do electrical bonding resistant tests of the new electrical bonding points.

(f) Re-fuel the wings fuel tanks.

(g) Check the wings fuel tanks for leaks.

(h) Close-up.

(6) ADDITIONAL WORK (Introduced by Rev 01)

(a) Refuel/Defuel Valve LH Wing - Kit 286064B39R00

1 Defuel and vent the LH wing fuel tank.

2 Get access to rib bay 13 to 14.

3 Bond the refuel/defuel valve.

(7) ADDITIONAL WORK

(a) Preparation

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 9

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

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

(c) Test

(d) Close-up

E. COMPLIANCE

(1) Classification

Mandatory

(2) Accomplishment Timescale

(a) It is mandatory to accomplish this Service Bulletin before 31st December 2010.

(b) Accomplishment of this Service Bulletin has been rendered mandatory by the issue

of an Airworthiness Directive (AD) published by the European Aviation Safety

Agency (EASA). The AD must be used as the reference document for the mandatory

accomplishment timescale.

(c) ADDITIONAL WORK (Introduced by Rev 01)

1 It is mandatory to accomplish the additional work before 31st December 2010.

(d) ADDITIONAL WORK

1 It is mandatory to accomplish the additional work before 31st December 2010.

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA 21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS

origin, 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 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 operators 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 and sealants, etc. and general administration are also not included.

Center Tank Kit 286064A01R05

Get access 30.0

Check of the bonding points 40.0

Modification/install the bonding points 13.0

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 10

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Test 1.5

Close-up 30.0

TOTAL MANHOURS 114.5

ELAPSED TIME (HOURS) 73.0

Center Tank Kit 286064A02R02

Get access 30.0

Check of the bonding points 40.0

Modification/install the bonding points 13.0

Test 1.5

Close-up 30.0

TOTAL MANHOURS 114.5

ELAPSED TIME (HOURS) 73.0

Center Tank Kit 286064A03R00

Get access 30.0

Check of the bonding points 40.0

Install the bonding points 3.0

Test 1.5

Close-up 30.0

TOTAL MANHOURS 104.5

ELAPSED TIME (HOURS) 63.0

LH and RH Wing Fuel Tanks.

The hours for the following kits are for both wings.

Rib Bay 1-2, Config. 08 Aircraft Only Kit 286064B20R06

Modification 20.0

TOTAL MANHOURS 20.0

ELAPSED TIME (HOURS) 10.0

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 11

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

NOTE : After the completion of the work in the wings fuel tanks, operators should allow

two hours for fuel leak tests.

Rib Bay 1-2, Kit 286064B01R05 All Aircraft

Get access 1.0

Modification 21.0

Close up 1.0

TOTAL MANHOURS 23.0

ELAPSED TIME (HOURS) 11.5

Rib Bay 1-2, Kit 286064B22R05 Config. 03 Aircraft

Modification 6.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 1-2, Kit 286064B23R01 Config. 06 Aircraft

Modification 2.0

TOTAL MANHOURS 2.0

ELAPSED TIME (HOURS) 1.0

Rib Bay 2-3, Kit 286064B01R05 All Aircraft

Modification 6.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 2-3, Kit 286064B21R01 Config. 04 Aircraft

Modification 6.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 5-6, Kit 286064B03R03 All Aircraft

Get access 1.0

Modification 4.0

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 12

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 5-6, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 8-9, Kit 286064B04R03 All Aircraft

Get access 1.0

Modification 6.0

Close up 1.0

TOTAL MANHOURS 8.0

ELAPSED TIME (HOURS) 4.0

Rib Bay 8-9, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 9-10, Kit 286064B05R01 All Aircraft

Get access 1.0

Modification 6.0

Close up 1.0

TOTAL MANHOURS 8.0

ELAPSED TIME (HOURS) 4.0

Rib Bay 9-10, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 13

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Rib Bay 10-11, Kit 286064B06R03 All Aircraft

Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 10-11, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 11-12, Kit 286064B07R01 All Aircraft

Get access 1.0

Modification 2.0

Close up 1.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 4.0

Rib Bay 12-13, Kit 286064B08R03 All Aircraft

Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 12-13, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 13-14, and Kit 286064B09R04 All Aircraft

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 14

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Get access 1.0

Modification 6.0

Close up 1.0

TOTAL MANHOURS 8.0

ELAPSED TIME (HOURS) 4.0

Rib Bay 14-15, Kit 286064B10R01 All Aircraft

Get access 1.0

Modification 14.0

Close up 1.0

TOTAL MANHOURS 16.0

ELAPSED TIME (HOURS) 8.0

Rib Bay 14-15, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 14-15, Kit 286064B25R01 Config. 07 Aircraft

Modification 2.0

TOTAL MANHOURS 2.0

ELAPSED TIME (HOURS) 1.0

Rib Bay 15-16, Kit 286064B11R05 All Aircraft

Get access 1.0

Modification 8.0

Close up 1.0

TOTAL MANHOURS 10.0

ELAPSED TIME (HOURS) 5.0

Rib Bay 15-16, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

Modification 4.0

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 15

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 16-17, Kit 286064B12R01 All Aircraft

Get access 1.0

Modification 2.0

Close up 1.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 17-18, Kit 286064B25R01 Config. 07 Aircraft

Get access 1.0

Modification 1.0

Close up 1.0

TOTAL MANHOURS 3.0

ELAPSED TIME (HOURS) 1.5

Rib Bay 18-19, Kit 286064B13R03 All Aircraft

Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 18-19, Kit 286064B02R02 or Kit 286064B26R01 Config. 01 and Config. 02

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 20-21, Kit 286064B14R02 All Aircraft

Get access 1.0

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 16

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 20-21, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 21-22, Kit 286064B15R04 All Aircraft

Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 21-22 Kit 286064B02R02 or Kit 286064B26R01 Config. 01 and Config. 02

Modification 4.0

TOTAL MANHOURS 4.0

ELAPSED TIME (HOURS) 2.0

Rib Bay 24-25, Kit 286064B16R03 All Aircraft

Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0

ELAPSED TIME (HOURS) 3.0

Rib Bay 24-25, Kit 286064B02R02 or Kit 286064B26R01 Config. 01 and Config. 02

Modification 4.0

TOTAL MANHOURS 4.0

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 17

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

ELAPSED TIME (HOURS) 2.0

Rib Bay 25-26, Kit 286064B19R02 All Aircraft

Get access 1.0

Modification 1.0

Close up 1.0

TOTAL MANHOURS 3.0

ELAPSED TIME (HOURS) 1.5

Rib Bay 26-27, Kit 286064B17R01 All Aircraft

Get access 1.0

Modification 5.0

Close up 1.0

TOTAL MANHOURS 7.0

ELAPSED TIME (HOURS) 3.5

Rib Bay 26-27, Kit 286064B27R01 or Kit 286064B28R01 Config. 02 Aircraft

Modification 5.0

TOTAL MANHOURS 5.0

ELAPSED TIME (HOURS) 2.5

Rib Bay 27-28, Kit 286064B18R04 All Aircraft

Get access 1.0

Modification 8.0

Close up 1.0

TOTAL MANHOURS 10.0

ELAPSED TIME (HOURS) 5.0

Rib Bay 27-28, Kit 286064B02R02 or Kit 286064B26R01 Config. 01 and Config. 02

Modification 4.0

TOTAL MANHOURS 4.0

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 18

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

ELAPSED TIME (HOURS) 2.0

NOTE : The overall manhours for the wings fuel tanks can vary between 162 total manhours,

elapsed time 83 manhours and 226 total manhours, 113 elapsed time manhours,

depending on the aircraft configuration.

NOTE : After the completion of the work in the wings fuel tanks, operators should allow

two hours for fuel leak tests.

ADDITIONAL WORK (Introduced by Rev 01)

Rib Bay 13-14, Kit 286064B39R00 All Aircraft

Get access 0.5

Modification 1.0

Close up 0.5

TOTAL MANHOURS 2.0

ELAPSED TIME (HOURS) 2.0

ADDITIONAL WORK

Get access 30.0

Check of the bonding points 1.0

Test 1.5

Close-up 30.0

TOTAL MANHOURS 62.5

ELAPSED TIME (HOURS) 31.0

H. WEIGHT AND BALANCE

Not changed

I. ELECTRICAL LOAD DATA

Not changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) : 06-41-57 20-28-11 24-00-00 24-31-11

24-41-00 27-80-00 28-00-00 28-10-00

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

28-25-21 33-13-00 33-14-00 57-20-43

57-23-11

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 19

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Elec. Std. Practices Manual (ESPM) : 20-51-10 20-55-00

Service Information Letter (SIL) : 28-072

Structural Repair Manual (SRM) : 51-40-20 51-40-30 51-40-44 51-43-00

51-75-10 51-76-10 51-76-20

Consumable Materials List (CML)

Service Bulletin (SB) : A300-28-6028 A300-28-6069

A300-28-6089 A300-57-6026

A300-57-6070

K. PUBLICATIONS AFFECTED

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

28-25-15 28-25-21 28-42-23 28-42-24

28-42-35 28-42-36 28-42-44 28-42-45

28-43-21 28-46-21 28-46-22 57-20-43

Illustrated Parts Catalogue (IPC) : 28-11-05 28-11-11 28-11-12 28-21-13

28-21-21 28-25-03 28-25-05 28-25-12

28-26-03 28-42-44 28-43-05 57-20-43

L. INTERCHANGEABILITY/MIXABILITY

None

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 20

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

2. MATERIAL INFORMATION

A. MATERIAL - PRICE AND AVAILABILITY

(1) Material

Operators with aircraft shown in the effectivity of this Service Bulletin should submit a

purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:

AIRBUS Spares Support and Services

Weg beim Jaeger 150

P.O. Box 630262

D-22335 HAMBURG

GERMANY

For ordering by internet: http://spares.airbus.com

For ordering by fax: +49 40 50 76 25 90

(2) Price and Availability

Kit 286064A01R05

Cost : 60 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064A02R02

Cost : 70 US dollars

Availability : 90 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 286064A03R00

Cost : 90 US dollars

Availability : 90 calendar days from receipt of order

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

at the issue date of the Service Bulletin.

Kit 286064B01R05

Cost : 150 US dollars

Availability : 90 calendar days from receipt of order

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 21

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B02R02

Cost : 30 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B03R03

Cost : 60 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B04R03

Cost : 80 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B05R01

Cost : 50 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B06R03

Cost : 230 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B07R01

Cost : 10 US dollars

Availability : 90 calendar days from receipt of order

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 22

Printed in France © AIRBUS 2008 All rights reserved
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SERVICE BULLETIN

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B08R03

Cost : 130 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B09R04

Cost : 20 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B10R01

Cost : 520 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B11R05

Cost : 110 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B12R01

Cost : 20 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B13R03

Cost : 180 US dollars

Availability : 90 calendar days from receipt of order

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 23

Printed in France © AIRBUS 2008 All rights reserved
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SERVICE BULLETIN

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B14R02

Cost : 150 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B15R04

Cost : 140 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B16R03

Cost : 71.90 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B17R01

Cost : 140 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B18R04

Cost : 120 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B19R02

Cost : 30 US dollars

Availability : 90 calendar days from receipt of order

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 24

Printed in France © AIRBUS 2008 All rights reserved
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SERVICE BULLETIN

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B20R06

Cost : 120 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B21R01

Cost : 130 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B22R05

Cost : 10 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B23R01

Cost : 13 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B25R01

Cost : 120 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B26R01

Cost : 30 US dollars

Availability : 90 calendar days from receipt of order

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 25

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B27R01

Cost : 150 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

Kit 286064B28R01

Cost : 150 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

NOTE : The kits availability given above is the standard lead time from the date of your

purchase order. If you require the Kits before this time, please include your

retrofit planning schedule with your order so that we can try to comply with

your requirements.

ADDITIONAL WORK (Introduced by Rev 01)

Kit 286064B39R00

Cost : 20 US dollars

Availability : 90 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditions

at the issue date of this Service Bulletin.

NOTE : The kits availability given above is the standard lead time from the date of your

purchase order. If you require the Kits before this time, please include your

retrofit planning schedule with your order so that we can try to comply with

your requirements.

B. INDUSTRY SUPPORT INFORMATION

None

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 26

Printed in France © AIRBUS 2008 All rights reserved
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SERVICE BULLETIN

C. LIST OF COMPONENTS

Kit 286064A01R05

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

2 NAS1303-3 2 Bolt

3 NAS1149F0332P 2 Washer

4 NAS1726-4E 2 Nut

5 NAS1726-3E 14 Nut

7 E0088-10-125 1 Lead

8 NSA5519-2B 3 Clamp

13 AN735D40 8 Clamp

14 NAS1801-3-8 8 Screw

15 E0088-10-80 7 Lead

16 E0088-10-160 3 Lead

17 NAS1303-2 2 Bolt

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

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

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

to part number relationship.

Kit 286064A02R02

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

2 NAS1303-3 2 Bolt

3 NAS1149F0332P 1 Washer

4 NAS1726-4E 1 Nut

5 NAS1726-3E 18 Nut

7 E0088-10-125 1 Lead

8 NSA5519-2B 3 Clamp

9 NSA5050-4 1 Nut

13 AN735D40 8 Clamp

14 NAS1801-3-8 8 Screw

15 E0088-10-80 7 Lead

16 E0088-10-160 3 Lead

17 NAS1303-2 1 Bolt

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

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

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

to part number relationship.

Kit 286064A03R00

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

2 NAS1303-3 2 Bolt

3 NAS1149F0332P 2 Washer

5 NAS1726-3E 2 Nut

10 E0088-10-200 2 Lead

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 27

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

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

11 ASNA2050DCJ3215 4 Rivet

12 A9242127720000 2 Angle

Kit 286064B01R05

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

4 NSA5472-4K7 4 Nut

14 E0088-41-160 1 Lead

15 AN742D6 1 Clamp

16 NSA5474-3K7 11 Nut

17 NSA5020-3-3 3 Bolt

20 NSA5474-4K7 7 Nut

25 H19200C4 1 Nut

27 NSA5041VBV3-4 1 Bolt

28 AN960C10L 1 Washer

34 NSA5041VBV3-10 2 Bolt

35 NSA5519-2B 4 Clamp

37 NAS1303-2 4 Bolt

38 E0088-10-100 2 Lead

39 E0088-41-100 2 Lead

45 NSA5022-4-21 4 Screw

46 NAS1304-3 4 Bolt

49 NSA5472-5K7 5 Nut

52 A2824028520000 3 Washer

53 AN960PD416 3 Washer

74 AN960KD10L 2 Washer

77 NSA5041VBV3-8 1 Bolt

Kit 286064B02R02

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

4 NSA5472-4K7 4 Nut

9 A5715206420000 1 Plate

13 NAS1252-416L 1 Washer

Kit 286064B03R03

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

2 NSA5020-3-6 1 Bolt

4 NSA5472-4K7 2 Nut

5 AN960C416L 1 Washer

6 NSA5041VBV4-2 1 Bolt

16 NSA5474-3K7 1 Nut

70 NSA5020-3-2 1 Bolt

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 28

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A300-600 A300-600

SERVICE BULLETIN

Kit 286064B04R03

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

4 NSA5472-4K7 2 Nut

5 AN960C416L 1 Washer

16 NSA5474-3K7 1 Nut

17 NSA5020-3-3 1 Bolt

25 H19200C4 1 Nut

30 NSA5041VBV4-3 1 Bolt

88 AN960KD10 1 Washer

Kit 286064B05R01

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

1 E0088-40-100 1 Lead

3 NSA5041VBV4-11 1 Bolt

4 NSA5472-4K7 2 Nut

5 AN960C416L 1 Washer

7 NSA5041VBV3-5 1 Bolt

14 E0088-41-160 1 Lead

15 AN742D6 1 Clamp

16 NSA5474-3K7 3 Nut

17 NSA5020-3-3 1 Bolt

19 ABS0114-4-18 1 Bolt

20 NSA5474-4K7 1 Nut

31 NAS1303-10 1 Bolt

Kit 286064B06R03

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

1 E0088-40-100 1 Lead

4 NSA5472-4K7 3 Nut

5 AN960C416L 1 Washer

16 NSA5474-3K7 1 Nut

18 NSA5472-3K7 1 Nut

28 AN960C10L 1 Washer

32 NSA5041VBV4-9 1 Bolt

33 NSA5041VBV3-3 1 Bolt

40 ABS0114-4-16 1 Bolt

70 NSA5020-3-2 1 Bolt

Kit 286064B07R01

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

16 NSA5474-3K7 2 Nut

20 NSA5474-4K7 1 Nut

39 E0088-41-100 1 Lead

50 AN742D8 1 Clamp

51 NAS1100-3-7 1 Screw

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REVISION No. : 03 - Dec 15/08 Page : 29

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SERVICE BULLETIN

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

55 NAS1304-11 1 Bolt

56 NAS1303-7 1 Bolt

58 NAS1304-14 1 Bolt

Kit 286064B08R03

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

4 NSA5472-4K7 3 Nut

5 AN960C416L 1 Washer

16 NSA5474-3K7 2 Nut

28 AN960C10L 1 Washer

32 NSA5041VBV4-9 1 Bolt

41 NSA5041VBV3-2 1 Bolt

42 NAS1303-1 1 Bolt

44 ABS0114-4-15 1 Bolt

89 E0088-40-190 1 Lead

Kit 286064B09R04

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

16 NSA5474-3K7 4 Nut

17 NSA5020-3-3 1 Bolt

20 NSA5474-4K7 2 Nut

25 H19200C4 1 Nut

51 NAS1100-3-7 2 Screw

59 E0088-41-304 2 Lead

70 NSA5020-3-2 1 Bolt

90 NSA5020-3-5 1 Bolt

Kit 286064B10R01

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

1 E0088-40-100 1 Lead

4 NSA5472-4K7 2 Nut

5 AN960C416L 1 Washer

7 NSA5041VBV3-5 1 Bolt

14 E0088-41-160 1 Lead

15 AN742D6 1 Clamp

16 NSA5474-3K7 8 Nut

17 NSA5020-3-3 1 Bolt

18 NSA5472-3K7 2 Nut

20 NSA5474-4K7 3 Nut

26 NSA5041VBV3-7 1 Bolt

35 NSA5519-2B 4 Clamp

37 NAS1303-2 4 Bolt

38 E0088-10-100 2 Lead

39 E0088-41-100 2 Lead

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 30

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SERVICE BULLETIN

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

45 NSA5022-4-21 4 Screw

54 NSA5041VBV4-7 1 Bolt

57 ABS0114-4-14 1 Bolt

69 NSA5041VBV3-6 2 Bolt

Kit 286064B11R05

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

1 E0088-40-100 1 Lead

4 NSA5472-4K7 5 Nut

5 AN960C416L 1 Washer

14 E0088-41-160 1 Lead

15 AN742D6 1 Clamp

16 NSA5474-3K7 1 Nut

17 NSA5020-3-3 1 Bolt

18 NSA5472-3K7 2 Nut

20 NSA5474-4K7 3 Nut

28 AN960C10L 1 Washer

29 NSA5041VBV4-8 1 Bolt

33 NSA5041VBV3-3 1 Bolt

46 NAS1304-3 2 Bolt

49 NSA5472-5K7 2 Nut

52 A2824028520000 2 Washer

53 AN960PD416 1 Washer

70 NSA5020-3-2 1 Bolt

85 ABS0114-4-13 1 Bolt

Kit 286064B12R01

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

16 NSA5474-3K7 2 Nut

70 NSA5020-3-2 1 Bolt

71 NSA5020-3-4 1 Bolt

Kit 286064B13R03

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

1 E0088-40-100 1 Lead

4 NSA5472-4K7 3 Nut

5 AN960C416L 1 Washer

16 NSA5474-3K7 1 Nut

18 NSA5472-3K7 1 Nut

28 AN960C10L 1 Washer

29 NSA5041VBV4-8 1 Bolt

33 NSA5041VBV3-3 1 Bolt

42 NAS1303-1 1 Bolt

61 ABS0114-4-12 1 Bolt

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 31

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SERVICE BULLETIN

Kit 286064B14R02

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

1 E0088-40-100 1 Lead

4 NSA5472-4K7 3 Nut

5 AN960C416L 1 Washer

12 NSA5041VBV4-5 1 Bolt

16 NSA5474-3K7 1 Nut

25 H19200C4 1 Nut

54 NSA5041VBV4-7 1 Bolt

63 ABS0114-4-10 1 Bolt

69 NSA5041VBV3-6 1 Bolt

Kit 286064B15R04

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

1 E0088-40-100 1 Lead

4 NSA5472-4K7 1 Nut

5 AN960C416L 1 Washer

12 NSA5041VBV4-5 1 Bolt

16 NSA5474-3K7 2 Nut

28 AN960C10L 1 Washer

41 NSA5041VBV3-2 1 Bolt

42 NAS1303-1 1 Bolt

64 NSA5475-4K7 2 Nut

86 ABS0114-4-9 1 Bolt

Kit 286064B16R03

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

1 E0088-40-100 1 Lead

5 AN960C416L 1 Washer

7 NSA5041VBV3-5 1 Bolt

16 NSA5474-3K7 2 Nut

27 NSA5041VBV3-4 1 Bolt

28 AN960C10L 1 Washer

62 NSA5041VBV4-6 1 Bolt

64 NSA5475-4K7 2 Nut

87 DHS1085-4 1 Washer

91 ABS0114-4-6 1 Bolt

Kit 286064B17R01

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

1 E0088-40-100 1 Lead

4 NSA5472-4K7 2 Nut

5 AN960C416L 1 Washer

12 NSA5041VBV4-5 1 Bolt

16 NSA5474-3K7 8 Nut

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 32

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SERVICE BULLETIN

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

18 NSA5472-3K7 1 Nut

20 NSA5474-4K7 1 Nut

28 AN960C10L 1 Washer

67 ABS0114-4-5 1 Bolt

72 ABS0114-3-6 1 Bolt

Kit 286064B18R04

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

1 E0088-40-100 1 Lead

5 AN960C416L 1 Washer

7 NSA5041VBV3-5 3 Bolt

16 NSA5474-3K7 3 Nut

20 NSA5474-4K7 1 Nut

30 NAS1304-4 2 Bolt

64 NSA5475-4K7 2 Nut

65 DHS783-63-18 1 Washer

78 NSA5041VBV4-4 1 Bolt

79 ABS0114-4-4 1 Bolt

87 DHS1085-4 1 Washer

Kit 286064B19R02

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

16 NSA5474-3K7 1 Nut

17 NSA5020-3-3 1 Bolt

71 NSA5020-3-4 1 Bolt

Kit 286064B20R06

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

14 E0088-41-160 1 Lead

15 AN742D6 1 Clamp

16 NSA5474-3K7 15 Nut

17 NSA5020-3-3 3 Bolt

20 NSA5474-4K7 5 Nut

25 H19200C4 1 Nut

27 NSA5041VBV3-4 1 Bolt

28 AN960C10L 1 Washer

34 NSA5041VBV3-10 2 Bolt

35 NSA5519-2B 4 Clamp

37 NAS1303-2 8 Bolt

38 E0088-10-100 2 Lead

39 E0088-41-100 2 Lead

45 NSA5022-4-21 4 Screw

46 NAS1304-3 2 Bolt

52 A2824028520000 1 Washer

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 33

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SERVICE BULLETIN

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

53 AN960PD416 2 Washer

74 AN960KD10L 2 Washer

77 NSA5041VBV3-8 1 Bolt

Kit 286064B21R01

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

16 NSA5474-3K7 2 Nut

17 NSA5020-3-3 1 Bolt

77 NSA5041VBV3-8 1 Bolt

Kit 286064B22R05

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

16 NSA5474-3K7 7 Nut

23 NAS1303-8 1 Bolt

37 NAS1303-2 4 Bolt

82 NSA5480PN3-5 2 Bolt

Kit 286064B23R01

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

16 NSA5474-3K7 1 Nut

17 NSA5020-3-3 1 Bolt

38 E0088-10-100 1 Lead

83 NSA5519-4B 1 Clamp

Kit 286064B25R01

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

16 NSA5474-3K7 2 Nut

20 NSA5474-4K7 2 Nut

62 NSA5041VBV4-6 1 Bolt

66 NAS1153-12 1 Screw

68 NSA5041VBV4-14 1 Bolt

69 NSA5041VBV3-6 1 Bolt

Kit 286064B26R01

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

4 NSA5472-4K7 4 Nut

10 A5715206420100 1 Plate

13 NAS1252-416L 1 Washer

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 34

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SERVICE BULLETIN

Kit 286064B27R01

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

4 NSA5472-4K7 5 Nut

9 A5715206420000 1 Plate

12 NSA5041VBV4-5 4 Bolt

13 NAS1252-416L 1 Washer

Kit 286064B28R01

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

4 NSA5472-4K7 5 Nut

10 A5715206420100 1 Plate

12 NSA5041VBV4-5 4 Bolt

13 NAS1252-416L 1 Washer

Kit 286064B39R00 (ADDITIONAL WORK Introduced by Rev 01)

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

16 NSA5474-3K7 2 Nut

20 NSA5474-4K7 2 Nut

51 NAS1100-3-7 2 Screw

59 E0088-41-304 2 Lead

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

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

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

to part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

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

MAT No.

Sealant Mat. No. 09-001 As required

Sealant Mat. No. 09-002 As required

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

Corrosion Inhibiting Brush

Consistency

Mat. No. 09-013B As required

Corrosion Inhibiting Fillet

Consistency

Mat. No. 09-016B As required

Sealant Mat. No. 09-018 As required

Corrosion Inhibiting Sealant

Sprayable

Mat. No. 09-025 As required

Sealant Mat. No. 09-530 As required

Cleaning agent Mat. No. 11-026 As required

Alodine Mat. No. 13-002 As required

Primer Mat. No. 16-001C As required

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 35

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

MAT No.

Varnish Mat. No. 16-021 As required

NOTE : To accomplish this Service Bulletin it is necessary to use the expendable parts

listed in the AMM 28-25-21 P. Block 401.

(2) Components

Center Tank

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

EN6115V5-15 1 Screw

EN6115V5-16 1 Screw

NSA5041VP4-11 2 Screw

NSA5041-3-9 1 Screw

NSA5061-3 1 Washer

NSA5061-4 5 Washer

NSA5112-03 1 Washer

NSA5112-04 3 Washer

NSA5050-3 48 Nut

NSA5050-4 21 Nut

NSA5050-5 2 Nut

NSA5050-6 4 Nut

NSA5075-6 2 Nut

NSA5182-4 2 Nut

NSA5182-3 2 Nut

NAS1726-3E 1 Nut

NAS1726-4E 7 Nut

ASNA2529-4 2 Nut

ASNA2529-5 2 Nut

ASNA2029-3 2 Nut

NSA5355-4CA 1 Nut

ASNA2050DXJ4828 2 Rivet

ASNA2050DCJ3215 54 Rivet

ASNA2050DCJ4020 2 Rivet

Additional Work

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

NSA5061-3 1 Washer

NSA5112-04 1 Washer

E. PARTS TO BE RE-IDENTIFIED BY THE OPERATOR

None

F. TOOLING - PRICE AND AVAILABILITY

None

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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SERVICE BULLETIN

G. SPECIAL TOOLS

None

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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This Page Intentionally Left Blank

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL

WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

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

AND NOTICES ARE IN POSITION BEFORE YOU START THIS MODIFICATION.

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

PRECAUTIONS (REFER TO AMM 28-00-00 PAGE BLOCK 301).

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

CONCENTRATION IS BELOW 20% OF THE LOWER EXPLOSION LIMIT (LEL).

WARNING : OBEY THE MANUFACTURER’S SAFETY INSTRUCTIONS WHEN YOU USE

SEALANTS, VARNISH AND CLEANING AGENTS IN THE FUEL TANKS.

CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY

SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR

MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND

THE WORK AREA AS CLEAN AS POSSIBLE, TO DO THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTH, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL METAL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

(1) Preparation

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

block 301).

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

TRAVEL RANGES OF THE SLATS/FLAPS.

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

(c) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-11, Page block 301).

(d) Put access platforms in position as necessary.

(e) Defuel and ventilate the center fuel tanks and the wing fuel tanks (Refer to AMM

28-10-00, Page block 301 and AMM 28-25-00, Page block 301).

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

Page block 401).

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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

during the ventilation process.

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

safety and tagged and warning notices are in position.

(h) For Slat Track Canisters and Screwjack Canisters it is necessary to remove the

inboard heat shields (as applicable) to allow the removal/installation of the applicable

canister-flange nut (Refer to AMM 57-20-43, Page block 401).

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

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

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

removal/installation of Track Cans/Jack Cans, refer to AMM 57-20-43, Page block

401.

(j) ADDITIONAL WORK

1 De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page block

301).

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

Page block 301).

3 Put the access platforms in position.

4 Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PWR.

5 Make sure that there is (are) warning notice(s) on the external power

receptacle(s) to tell persons not to connect an external power source.

6 Make sure that the EMER EXIT LT pushbutton switch on the panel 26VU is on

the DISARM position.

7 In the flight compartment, on the overhead panel 51VU, release the BAT

pushbutton switch.

8 Display a warning notice on the overhead panel 51VU to tell persons not to

operate the batteries.

9 Display a warning notice on refuel/defuel panel 110VU to tell persons not to

operate the NORMAL BATTERY switch.

10 Display a warning notice in the cockpit to tell persons not to start the Auxiliary

Power Unit (APU).

11 Display a warning notice in the cockpit to tell persons not to start ENG 1, 2.

12 Battery disconnection :

- For the job set-up, refer to the removal/installation of the batteries (Refer to

AMM 24-31-11, Page block 401).

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- Turn the knurled nut a quarter turn.

- Disconnect the connectors.

- Put blanking caps on the disconnected electrical connectors.

13 Open, safety and tag these circuit breakers :

Depending on aircraft configuration

PANEL DESIGNATION FIN LOCATION

22VU FUEL/TK LO LVL AND CAL/L OUTR &

R INR & CTR R

1QJ 208/B26

22VU FUEL/TK LO LVL AND CAL/R OUTR &

L INR & CTR L

2QJ 208/B27

132VU FUEL/FUELING HI LVL 6QJ 321/P57

132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58

132VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 321/P56

132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59

132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60

132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

or

PANEL DESIGNATION FIN LOCATION

22VU FUEL/TK LO LVL AND CAL/L OUTR &

R INR & CTR R

1QJ 208/B26

22VU FUEL/TK LO LVL AND CAL/R OUTR &

L INR & CTR L

2QJ 208/B27

128VU FUEL/FUELING HI LVL 6QJ 805/L87

128VU FUEL/FUELING OVERFLOW AND CAL 5QJ 805/L86

128VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 805/L88

128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83

128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84

128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85

14 Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-11, Page

block 301).

15 Defuel and ventilate the center fuel tank and the wing fuel tanks (Refer to AMM

28-10-00, Page block 301 and AMM 28-25-00, Page block 301).

16 Remove additional wing manhole covers as necessary (Refer to AMM 28-11-22,

Page block 401).

17 Open the access doors 147AZ and 148AZ (Refer to AMM 28-11-29, Page

block 401).

(2) Standard Practices

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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Printed in France © AIRBUS 2008 All rights reserved
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SERVICE BULLETIN

(a) For access to the slat track canisters and screw-jack canisters (LH and RH wings),

refer to AMM 57-20-43, Page block 401.

(b) For wing access panels/doors, refer to AMM 06-41-57, Page block 001.

(c) For the removal and installation of fasteners, refer to SRM 51-40-20.

(d) Cut rivets to the applicable length.

(e) For fastener hole and drill information, refer to SRM 51-40-44.

(f) For alternative fasteners, refer to SRM 51-40-30.

(g) For applicable torque values of fasteners, refer to SRM 51-43-00.

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

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

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

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

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

(m) For the installation of the new bonding leads and new bonding positions in the wings

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

- the preparation of the bonding positions.

- the installation of bonding leads, clamps and the installation of bolts as bonding

bolts.

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

- the application of protective coating to bonding items.

B. MODIFICATION

(1) Kit 286064A01R05, Kit 286064A02R02 and Kit 286064A03R00

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

NOTE : In Fuel Center Tank, the modification consists in :

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

Figure 1, Sheet 1.

For each point identified check the presence of blue coat :

- If blue coat present, no further action.

- If no blue coat then :

Measure the electrical resistance between part and the structure, (Refer

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

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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

- If the ohmic resistance >10mhm, do the bonding, (Refer to AMM

20-28-11, Page block 001).

1 Check the bonding points Items 1 thru 5 at FR44.

Refer to Figure 1, Sheet 1 (General location)

Refer to Figure 2, Sheets 1 thru 6 (Detailed location)

Refer to Figure 3, Sheet 1 (Result table)

2 Check the bonding points Items 6 thru 24 at FR47.

Refer to Figure 1, Sheet 1 (General location)

Refer to Figure 4, Sheets 1 thru 17 (Detailed location)

Refer to Figure 5, Sheet 1 (Result table)

3 Check the bonding points Items 25 thru 29 on the rib 1 (LH side).

Refer to Figure 1, Sheet 1 (General location)

Refer to Figure 6, Sheets 1 thru 3 (Detailed location)

Refer to Figure 7, Sheet 1 (Result table)

4 Check the bonding points Items 30 thru 44 on the intrados panel.

Refer to Figure 1, Sheet 1 (General location)

Refer to Figure 8, Sheets 1 thru 10 (Detailed location)

Refer to Figure 9, Sheet 1 (Result table)

5 Check the bonding points Items 45 thru 51 on the rib 1 (RH side).

Refer to Figure 1, Sheet 1 (General location)

Refer to Figure 10, Sheets 1 thru 6 (Detailed location)

Refer to Figure 11, Sheet 1 (Result table)

6 Check the bonding points Items 52 thru 78 on the extrados panel.

Refer to Figure 1, Sheet 1 (General location)

Refer to Figure 12, Sheets 1 thru 8 (Detailed location)

Refer to Figure 13, Sheet 1 (Result table)

(2) Kit 286064A01R05

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 43

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

(a) Modify or install the bonding points.

1 Modify the refueling pipes on LH side between FR44 and FR47, valid for aircraft

on which Mod. No. 04801H5078 (FUEL - INSTALL TRIM TANK SYSTEM) is

embodied.

Refer to Figure 14 Sheets 1 thru 3

a Remove :

1 screw Item (285) Retain

1 washer Item (3) Retain

Disengage the bonding lead item (281) without complete removal.

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

Figure 14 Sheet 3

- Install on the sleeve item (268) :

1 Bonding Lead E0088-10-80 Item 15

1 Nut NAS1726-3E Item 5

1 Clamp AN735D40 Item 13

1 Screw NAS1801-3-8 Item 14

b Install the bonding leads item (281) and 15 with :

1 Screw Item (285)

1 Washer Item (3)

NOTE : Items (3) and (285) were retained at removal.

c For aircraft on which modification No. 06549 (FUEL - TRIM TANK SYSTEM

- EMBODY ANTI-MODIFICATION TO ALLOW CHANGE FROM "WET" TO

"DRY") is not embodied, do a stripping on the sleeve item (268) to the

dimensions given in the Figure 14 Sheet 3 detail E.

- Install on the sleeve item (268) :

1 Bonding Lead E0088-10-80 Item 15

1 Nut NAS1726-3E Item 5

1 Clamp AN735D40 Item 13

1 Screw NAS1801-3-8 Item 14

- Remove :

1 Screw Item (220) Retain

1 Nut Item (4) Discard

- Install the bonding lead Item 15 with :

1 Screw Item (220)

1 Nut NAS1726-4E Item 4

NOTE : Item (220) was retained at removal.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 44

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

2 Modify the tube item (283) from TTS pipes, valid for aircraft on which Mod. No.

04801H5078 (FUEL - INSTALL TRIM TANK SYSTEM) is embodied.

Refer to Figure 15 Sheets 1 thru 3

a Remove :

Refer to Figure 15 Sheets 2 and 3

1 Screw Item (285) Retain

1 Washer Item (3) Retain

Disengage the bonding lead item (284) without complete removal.

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

Figure 15 Sheet 3

c Install on the sleeve item (268) :

1 Bonding Lead E0088-10-80 Item 15

1 Nut NAS1726-3E Item 5

1 Clamp AN735D40 Item 13

1 Screw NAS1801-3-8 Item 14

d Install the bonding leads item (284) and 15 with :

1 Screw Item (285)

1 Washer Item (3)

NOTE : Items (3) and (285) were retained at removal.

3 Modify the sleeves item (268).

Refer to Figure 15 Sheets 1, 4 thru 6

a Remove :

Refer to Figure 15 Sheet 4

1 Screw Item (2) Retain

1 Washer Item (3) Retain

1 Screw Item (269) Retain

1 Nut Item (4) Discard

- Disengage the bonding lead item (16).

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

Figure 15 Sheet 6.

c On the tee pipe, do strippings to the dimensions given in the Figure 15

Sheet 6.

d Install on the sleeves item (268) :

Refer to Figure 15 Sheet 6

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 45

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

2 Bonding Lead E0088-10-160 Item 16

2 Clamp AN735D40 Item 13

2 Nut NAS1726-3E Item 5

2 Screw NAS1801-3-8 Item 14

e Put the bonding leads Item (16) and Item 16 in position on the tee pipe.

Refer to Figure 15 Sheet 5

f Install :

1 Screw Item (2)

1 Washer Item (3)

1 Screw Item (269)

1 Nut NAS1726-4E Item 4

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

4 Modify the sleeves item (268) from TTS pipes, valid for aircraft on which Mod.

No. 04801H5078 (FUEL - INSTALL TRIM TANK SYSTEM) is embodied.

Refer to Figure 15 Sheets 7 and 8

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

Figure 15 Sheet 8.

b Install on the sleeves item (268) :

Refer to Figure 15 Sheet 8

3 Bonding Lead E0088-10-80 Item 15

3 Clamp AN735D40 Item 13

3 Nut NAS1726-3E Item 5

3 Screw NAS1801-3-8 Item 14

c Remove from the tee pipe :

Refer to Figure 15 Sheet 8

2 Screw Item (569) Retain

2 Nut Item (5) Discard

d Put the bonding leads Item 15 in position on the tee pipe.

Refer to Figure 15 Sheets 7 and 8

e Install on the tee pipe :

Refer to Figure 15 Sheet 8

2 Screw Item (569)

2 Nut NAS1726-3E Item 5

NOTE : Item (569) was retained at removal.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 46

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

5 Modify the feed pipes, valid for aircraft on which Mod. No. 04801H5078 (FUEL -

INSTALL TRIM TANK SYSTEM) is embodied.

Refer to Figure 16 Sheets 1 thru 3

a Remove from LH side :

1 Screw Item (285) Retain

1 Washer Item (413) Retain

b On the tube item (333), do a stripping to the dimensions given in the

Figure 16 Sheet 2.

c Install :

1 Bonding Lead E0088-10-80 Item 15

1 Clamp NSA5519-2B Item 8

1 Bolt NAS1303-3 Item 2

1 Nut NAS1726-3E Item 5

1 Screw Item (285)

1 Washer Item (413)

NOTE : Items (285) and (413) were retained at removal.

d Remove from RH side :

1 Screw Item (285) Retain

1 Washer Item (413) Retain

1 Nut Item (5) Discard

Disengage the bonding lead without complete removal.

e On the tube item (334), do a stripping to the dimensions given in the

Figure 16 Sheet 3.

f Install :

1 Bonding Lead E0088-10-160 Item 16

1 Clamp NSA5519-2B Item 8

1 Bolt NAS1303-3 Item 2

1 Nut NAS1726-3E Item 5

Put the bonding leads Item in position with :

1 Screw Item (285)

1 Washer Item (413)

1 Nut NAS1726-3E Item 5

NOTE : Items (285) and (413) were retained at removal.

6 Modify the feed pipe, valid for aircraft on which Mod. No. 04801H5078 (FUEL -

INSTALL TRIM TANK SYSTEM) is not embodied.

Refer to Figure 16 Sheets 1 and 3

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 47

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

a Remove from RH side :

1 Screw Item (285) Retain

1 Washer Item (413) Retain

1 Nut Item (5) Discard

Disengage the bonding lead without complete removal.

b On the tube item (334), do a stripping to the dimensions given in the

Figure 16 Sheet 3.

c Install :

1 Bonding Lead E0088-10-160 Item 16

1 Clamp NSA5519-2B Item 8

1 Bolt NAS1303-3 Item 2

1 Nut NAS1726-3E Item 5

Put the bonding leads Item in position with :

1 Screw Item (285)

1 Washer Item (413)

1 Nut NAS1726-3E Item 5

NOTE : Items (285) and (413) were retained at removal.

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

Refer to Figure 17 Sheets 1 and 2

a Remove :

1 Screw Item (2) Retain

1 Washer Item (3) Retain

- Disengage the bonding lead without complete removal.

b On the tube, do a stripping to the dimensions given in the Figure 17 Sheet 2.

c Install :

1 Nut NAS1726-3E Item 5

2 Bolt NAS1303-2 Item 17

2 Washer NAS1149F0332P Item 3

1 Bonding Lead E0088-10-125 Item 7

1 Clamp NSA5519-2B Item 8

- Install the bonding leads with :

1 Screw Item (2)

1 Washer Item (3)

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

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 48

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

(3) Kit 286064A02R02

(a) Modify or install the bonding points.

1 Modify the refueling pipes on LH side between FR44 and FR47.

Refer to Figure 18 Sheets 1 thru 3

a Remove :

1 Screw Item (285) Retain

1 Washer Item (3) Retain

Disengage the bonding lead item (281) without complete removal.

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

the Figure 18, Sheet 3

- Install on the sleeve item (268) :

1 Bonding Lead E0088-10-80 Item 15

1 Nut NAS1726-3E Item 5

1 Clamp AN735D40 Item 13

1 Screw NAS1801-3-8 Item 14

b Install the bonding leads item (281) and 15 with :

1 Screw Item (285)

1 Washer Item (3)

NOTE : Items (3) and (285) were retained at removal.

c For aircraft on which modification No. 06549 (FUEL - TRIM TANK SYSTEM

- EMBODY ANTI-MODIFICATION TO ALLOW CHANGE FROM "WET" TO

"DRY") is not embodied, do a stripping on the sleeve item (268) to the

dimensions given in the Figure 18, Sheet 3 detail E.

- Install on the sleeve item (268) :

1 Bonding Lead E0088-10-80 Item 15

1 Nut NAS1726-3E Item 5

1 Clamp AN735D40 Item 13

1 Screw NAS1801-3-8 Item 14

- Remove :

1 Screw Item (220) Retain

1 Nut Item (4) Discard

- Install the bonding lead Item 15 with :

1 Screw Item (220)

1 Nut NAS1726-4E Item 4

NOTE : Item (220) was retained at removal.

2 Modify the tube item (283) from TTS pipes.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 49

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Refer to Figure 19 Sheets 1 thru 3

a Remove :

Refer to Figure 19 Sheets 2 and 3

1 Screw Item (1) Retain

1 Nut Item (5) Discard

Disengage the bonding lead item (284) without complete removal.

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

Figure 19, Sheet 3

c Install on the sleeve item (268) :

1 Bonding Lead E0088-10-80 Item 15

1 Nut NAS1726-3E Item 5

1 Clamp AN735D40 Item 13

1 Screw NAS1801-3-8 Item 14

d Install the bonding leads item (284) and 15 with :

1 Screw Item (1)

1 Nut NAS1726-3E Item 5

NOTE : Item (1) was retained at removal.

3 Modify the sleeves item (268).

Refer to Figure 19 Sheets 1, 4 thru 6

a Remove :

Refer to Figure 19 Sheet 4

1 Screw Item (1) Retain

1 Nut Item (5) Discard

1 Screw Item (255) Retain

1 Nut Item (9) Discard

- Disengage the bonding lead item (249).

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

Figure 19, Sheet 6.

c On the tee pipe, do strippings to the dimensions given in the Figure 19,

Sheets 4 and 6.

d Install on the sleeves item (268) :

Refer to Figure 19 Sheet 6

2 Bonding Lead E0088-10-160 Item 16

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 50

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

2 Clamp AN735D40 Item 13

2 Nut NAS1726-3E Item 5

2 Screw NAS1801-3-8 Item 14

e Put the bonding leads Item (249) and Item 16 in position on the tee pipe.

Refer to Figure 19 Sheet 5

f Install :

1 Screw Item (1)

1 Nut NAS1726-3E Item 5

1 Screw Item (255)

1 Nut NSA5050-4 Item 9

NOTE : Items (1) and (255) were retained at removal.

4 Modify the sleeves item (268) from TTS pipes :

Refer to Figure 19 Sheets 7 and 8

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

Figure 19, Sheet 8.

b Install on the sleeves item (268) :

Refer to Figure 19 Sheet 8

3 Bonding Lead E0088-10-80 Item 15

3 Clamp AN735D40 Item 13

3 Nut NAS1726-3E Item 5

3 Screw NAS1801-3-8 Item 14

c Remove from the tee pipe :

Refer to Figure 19 Sheet 8

2 Screw Item (569) Retain

2 Nut Item (5) Discard

d Put the bonding leads Item 15 in position on the tee pipe.

Refer to Figure 19 Sheets 7 and 8

e Install on the tee pipe :

Refer to Figure 19 Sheet 8

2 Screw Item (569)

2 Nut NAS1726-3E Item 5

NOTE : Items (569) were retained at removal.

5 Modify the feed pipes.

Refer to Figure 20 Sheets 1 thru 3

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 51

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

a Remove from LH side :

1 Screw Item (1) Retain

1 Nut Item (5) Discard

b On the tube item (333), do a stripping to the dimensions given in the Figure

20, Sheet 2.

c Install :

1 Bonding Lead E0088-10-80 Item 15

1 Clamp NSA5519-2B Item 8

1 Bolt NAS1303-3 Item 2

2 Nut NAS1726-3E Item 5

1 Screw Item (1)

NOTE : Item (1) was retained at removal.

d Remove from RH side :

1 Screw Item (1) Retain

1 Nut Item (5) Discard

Disengage the bonding lead without complete removal.

e On the tube item (334), do a stripping to the dimensions given in the Figure

20, Sheet 3.

f Install :

1 Bonding Lead E0088-10-160 Item 16

1 Clamp NSA5519-2B Item 8

1 Bolt NAS1303-3 Item 2

1 Nut NAS1726-3E Item 5

Put the bonding leads in position with :

1 Screw Item (1)

1 Nut NAS1726-3E Item 5

NOTE : Item (1) was retained at removal.

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

Refer to Figure 21 Sheets 1 and 2

a Remove :

1 Screw Item (1) Retain

1 Nut Item (5) Discard

- Disengage the bonding lead without complete removal.

b On the tube, do a stripping to the dimensions given in the Figure 21, Sheet 2.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 52

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

c Install :

1 Nut NAS1726-3E Item 5

1 Bolt NAS1303-2 Item 17

1 Washer NAS1149F0332P Item 3

1 Bonding Lead E0088-10-125 Item 7

1 Clamp NSA5519-2B Item 8

- Install the bonding leads with :

1 Screw Item (1)

1 Nut NAS1726-3E Item 5

NOTE : Item (1) was retained at removal.

(4) Kit 286064A03R00

(a) Install the bonding points.

1 Remove :

2 Screw Item (206) Retain

2 Washer Item (260) Retain

2 On the blanking plates item (310), do a stripping to the dimension given in the

Figure 22, Sheets 2 and 3.

3 Temporarily install the bonding lead item 10 on the angle item 12.

4 Temporarily install the angle item 12 on the structure as shown in the Figure

22, Sheets 2 and 3.

5 Drill the structure to match the holes of the angle item 12 at the dimensions

given in the Figure 22, Sheet 3.

6 Install :

2 Angle A9242127720000 Item 12

with

4 Rivet ASNA2050DCJ3215 Item 11

7 Install :

2 Screw Item (206)

2 Washer Item (260)

2 Bonding Lead E0088-10-200 Item 10

2 Nut NAS1726-3E Item 5

2 Bolt NAS1303-3 Item 2

2 Washer NAS1149F0332P Item 3

NOTE : Items (206) and (260) were retained at removal.

(5) Wings Fuel Tanks

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 53

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

(a) The Tables that follow list all the equipment in the wings fuel tanks that are to be

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

for each rib bay is given in para. (6) thru (25) for pre Mod. 12226 aircraft and

para. (26) for Post Mod. 12226 aircraft.

Paragraph (27) refers to the ADDITIONAL WORK that is necessary if this Service

Bulletin has been embodied on aircraft at original issue, which were not Config.

05 aircraft.

The worksteps given are for the LH wing. The worksteps for the RH wing are the

same unless otherwise stated.

TABLE 1 - PRE. MOD. 12226 AIRCRAFT

LH AND RH WING

APPLICABLE RIB BAY

EQUIPMENT TO

BE ELECTRICALLY

BONDED

REFERENCED

FIGURES

APPLICABLE KIT

Rib Bay 1-2 Water Drain Valves.

Water Scavenge Pipes

(Config. 03 aircraft).

MLI.

Fuel Feed Pipe.

Low Fuel Pressure

Switches.

Fuel Booster Pumps.

Fuel Booster Pumps

(Config. 06 aircraft).

Diffuser.

Fuel Level sensor.

Figure 23, Sheet 1

Figure 24, Sheet 1

Figure 25, Sheet 1

Figure 26, Sheet 1

Figure 27, Sheet 1

Figure 28, Sheet 1

Figure 29, Sheet 2

Figure 30, Sheet 2

Kit B01R05 all aircraft.

For Config. 03 aircraft

Kit B22R05.

For Config. 06 aircraft

Kit B23R01.

Rib Bay 2-3 Diffuser.

Calibration Sensor

(Config. 04 aircraft)

Figure 29, Sheet 1

Figure 30, Sheet 1

Kit B01R05 all aircraft.

For Config. 04 aircraft

Kit B21R01.

Rib Bay 5-6 Slat Track Canister 3. Figure 31, Sheet 1,

Sheet 2

Kit B03R03 all aircraft

and Kit B02R02 or

B26R01 for Config. 02

aircraft

Rib Bay 8-9 Slat Track Canister 4.

MLI.

Figure 32, Sheet 1

Figure 31, Sheet 2

Figure 25, Sheet 1

Kit B04R03 all aircraft

and Kit B02R02 or

B26R01 for Config. 02

aircraft.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 54

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

LH AND RH WING

APPLICABLE RIB BAY

EQUIPMENT TO

BE ELECTRICALLY

BONDED

REFERENCED

FIGURES

APPLICABLE KIT

Rib Bay 9-10 Screwjack Canister 3.

Water Drain Valve.

Figure 33, Sheet 1,

Sheet 2

Figure 23, Sheet 1

Kit B05R01 all aircraft

and Kit B02R02 or

B26R01 for Config. 02

aircraft.

Rib Bay 10-11 Slat Track Canister 5 Figure 34, Sheet 1

Figure 31, Sheet 2

Kit B06R03 all aircraft

and Kit B02R02 or

B26R01 for Config. 02

aircraft.

Rib Bay 11-12 (RH Wing

only)

Cadensicon. Figure 35, Sheet 1 Kit B07R01 all aircraft.

Rib Bay 12-13 Slat Track Canister 6. Figure 36, Sheet 1

Figure 31 Sheet 2

Kit B08R03 all aircraft

and Kit B02R02 or

B26R01 for Config. 02

aircraft.

Rib Bay 13-14 MLI.

Refuel/Defuel Valves.

Fuel Level Sensor.

Overwing Refuel Panel.

Figure 25, Sheet 1

Figure 37, Sheet 1 and

Sheet 2

Figure 30, Sheet 1

Figure 39, Sheet 1

Kit B09R04 all aircraft.

Rib Bay 14-15 Screwjack Canister 4.

Water Drain Valve.

Low Fuel Pressure

Switches.

Fuel Booster Pumps.

Provision for Fuel

Jettison System -

Blanking plate (Config.

07 aircraft).

Figure 40, Sheet 1

Figure 33, Sheet 2

Figure 23, Sheet 1,

Sheet 2

Figure 27, Sheet 2 and

Sheet 2

Figure 41, Sheet 1

Figure 38, Sheet 1

Kit B10R01 all aircraft

and Kit B02R02 or

B26R01 for Config. 02

aircraft. Kit B25R01 for

Config. 07 aircraft.

Rib Bay 15-16 Slat Track Canister 7.

Diffuser.

Water Drain Valve.

Figure 42, Sheet 1

Figure 31, Sheet 2

Figure 29, Sheet 3

Figure 23, Sheet 1

Kit B11R05 all aircraft

and Kit B02R02 or

B26R01 for Config. 02

aircraft.

Rib Bay 16-17 Fuel Level Sensor. Figure 30, Sheet 2 Kit B12R01 all aircraft.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 55

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

LH AND RH WING

APPLICABLE RIB BAY

EQUIPMENT TO

BE ELECTRICALLY

BONDED

REFERENCED

FIGURES

APPLICABLE KIT

Rib Bay 17-18 Provision for a Fuel

Jettison System -

Blanking Plates (Config.

07 aircraft).

Figure 38, Sheet1 Kit B25R01 for Config.

07 aircraft.

Rib Bay 18-19 Slat Track Canister 8. Figure 43, Sheet 1

Figure 31, Sheet 2

Kit B13R03 all aircraft

and Kit B02R02 or

B26R01 for Config 01

and Config. 02 aircraft.

Rib Bay 20-21 Screwjack Canister 5.

MLI

Figure 44, Sheet 1

Figure 33, Sheet 2

Figure 25, Sheet 1

Kit B14R02 all aircraft

and Kit B02R02 or

B26R01 for Config. 02

aircraft.

Rib Bay 21-22 Slat Track Canister 9. Figure 45, Sheet 1

Figure 31, Sheet 2

Kit B15R04 all aircraft

and Kit B02R02 or

B26R01 for Config 01

and Config. 02 aircraft.

Rib Bay 24-25 Slat Track Canister 10 Figure 46, Sheet 1

Figure 31, Sheet 2

Kit B16R03 all aircraft

and Kit B02R02 or

B26R01 for Config. 01

and Config. 02 aircraft.

Rib Bay 25-26 Fuel level Sensor Figure 30, Sheet 1 Kit B19R02 all aircraft.

Rib Bay 26-27 Screwjack Canister 6.

MLI.

Overwing Refuel Panel.

Figure 47, Sheet 1

Figure 25, Sheet 1

Figure 39, Sheet 1

Kit B17R01 all aircraft

and Kit B27R01 or

B28R01 for Config. 02

aircraft.

Rib Bay 27-28 Slat Track Canister 11.

Water Drain.

Fuel Overflow Sensor.

Overpressure Protector.

Figure 48, Sheet 1

Figure 31, Sheet 2

Figure 23, Sheet 1

Figure 30, Sheet 4

Figure 49, Sheet 1

Kit B18R04 all aircraft

and Kit B02R02 or

B26R01 for Config. 01

and Config. 02 aircraft.

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

ADDITIONAL WORK (Introduced by Rev 01)

Rib Bay 13-14

Additional Work

Refuel/Defuel Valves LH

Wing

Figure 37, Sheet 1 and

Sheet 2

Kit B39R00

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 56

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

TABLE 2 - CONFIG 08 POST Mod. 12226 AIRCRAFT ONLY

LH and RH WING -

APPLICABLE RIB BAY

EQUIPMENT TO

BE ELECTRICALLY

BONDED

REFERENCE FIGURES APPLICABLE KIT

Rib Bay 1-2 Water Drain Valves.

Water Scavenge Pipe.

MLI.

Fuel Feed Pipe Support

Bracket.

Low Fuel Pressure

Switches.

Fuel Booster Pumps

Canisters.

Fuel Diffuser.

Low Level Fuel Sensor.

Figure 23, Sheet 1

Figure 24, Sheet 2

Figure 25, Sheet 1

Figure 26, Sheet 1

Figure 27, Sheet 1

Figure 28, Sheet 1

Figure 29, Sheet 4

Figure 30, Sheet 3

Kit B20R06

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

(6) Rib Bay 1-2

Kit 286064B01R05 all aircraft

Kit 286064B22R05 Config. 03 aircraft

Kit 286064B23R01 Config. 06 aircraft

(a) Forward Rib Bay Water Drain Valve

Kit 286064B01R05

Refer to Figure 23, Sheet 1, Detail D

1 At the water drain valve, remove:

- one nut, Item (20), discard.

- one bolt, Item (19), retain.

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

through the wing skin also prepare the countersink. Install:

- 1 retained bolt, Item (19).

1 Nut NSA5474-4K7 Item 20

(b) Aft Rib Bay Water Drain Valve

Kit 286064B01R05

Refer to Figure 23, Sheet 1, Detail A

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 57

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

1 At the water drain valve, remove:

- one nut, Item (20), discard.

- one bolt, Item (19), retain.

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

1 Clamp AN742D6 Item 15

1 Lead E0088-41-160 Item 14

1 Bolt NSA5020-3-3 Item 17

1 Nut NSA5474-3K7 Item 16

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

through the wing skin also prepare the countersink. Install:

- 1 retained bolt, Item (19).

- the other end of bonding lead, Item 14.

1 Nut NSA5474-4K7 Item 20

(c) Water Scavenge Pipe - Config. 03 aircraft

Kit 286064B22R05

Refer to Figure 24, Sheet 1

1 At the pipe clamps (Refer to Detail A and Detail C), remove:

- five nuts, Item (16), discard.

- three bolts, Item (37), discard.

- two bolts, Item (82), discard.

- three clamps, Item (22), retain.

2 At the water drain-pipe support bracket (Refer to Detail B), remove:

- two nuts, Item (16), discard.

- one bolt, Item (37), discard.

- one bolt, Item (23), discard.

- one clamp, Item (22) retain.

If the support bracket is attached by rivets, remove one of the rivets and increase

the diameter of the hole to 4.826-4-877mm (0.1900-0.1920in.) to allow for the

installation of a bolt.

3 On the support bracket and pipe clamp position (refer to Detail B) prepare

the bonding area and install:

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 58

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- 1 retained clamp, Item (22).

1 Bolt NAS1303-2 Item 37

1 Bolt NAS1303-8 Item 23

2 Nut NSA5474-3K7 Item 16

4 On the support brackets and pipe clamp positions (refer to Detail A and C)

prepare the bonding areas and install:

- 3 retained clamps, Item (22).

2 Bolt NSA5480PN3-5 Item 82

3 Bolt NAS1303-2 Item 37

5 Nut NSA5474-3K7 Item 16

(d) MLI

Kit 286064B01R05

Refer to Figure 25, Sheet 1, Detail B

1 At the base of the MLI, remove:

- one nut, Item (25), discard.

- the related bolt, Item (24), retain.

2 Prepare the bonding area and for the bolt that goes through the wing skin,

prepare the countersink. Install:

- the retained bolt, Item (24)

1 Nut H19200C4 Item 25

(e) Fuel Feed Pipe Support

Kit 286064B01R05

Refer to Figure 26, Sheet 1

1 At the fuel pipe support bracket, upper section, remove:

- one nut, Item (16), discard.

- one bolt, Item (27), discard.

2 At the fuel pipe support bracket, lower section, remove:

- one nut, Item (16), discard.

- one bolt, Item (77), discard.

- one washer, Item (28), if installed, discard.

3 At the fuel pipe support bracket, upper section, prepare the bonding area

and install:

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 59

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

1 Bolt NSA5041VBV3-4 Item 27

1 Nut NSA5474-3K7 Item 16

4 At the fuel pipe support bracket, lower section, prepare the bonding area and

install:

1 Bolt NSA5041VBV3-8 Item 77

1 Nut NSA5474-3K7 Item 16

and if applicable:

1 Washer AN960C10L Item 28

(f) Low Fuel Pressure Switches

Kit 286064B01R05

Refer to Figure 27, Sheet 1

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

- one nut, Item (16), discard.

- one bolt, Item (34), discard.

2 At the two pressure switch pipes prepare the bonding areas and install:

2 Clamp NSA5519-2B Item 35

2 Lead E0088-10-100 Item 38

2 Bolt NAS1303-2 Item 37

2 Nut NSA5474-3K7 Item 16

3 At the two pressure switches attachments to the rear spar prepare the bonding

areas and attach the bonding leads, Item 38, with:

2 Bolt NSA5041VBV3-10 Item 34

2 Nut NSA5474-3K7 Item 16

4 Torque tighten the nuts, Item 16, to between 0.34-0.40 mdaN (30-35 lbf.in.).

(g) Fuel Booster Pumps Canisters - All Aircraft

Kit 286064B01R05

Refer to Figure 28, Sheet 1

1 At each canister flange (at the positions shown in the figure), remove:

- two bolts, Item (45), discard.

CAUTION : BOLTS THAT GO THROUGH THE FAIRING ARE NOT TO BE USED

AS BONDING BOLTS.

2 At the two canister flanges prepare the bonding areas and for the bolts through

the wing skin prepare the countersinks only and install:

4 Bolt NSA5022-4-21 Item 45

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 60

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

3 At each of the canisters, at the fuel outlet flange (adjacent to the existing bonding

lead, refer to Detail C) remove:

- one nut (20), discard.

- one bolt, Item (43), retain.

4 On the two pressure switch pipes prepare the bonding areas and install:

2 Clamp NSA5519-2B Item 35

2 Lead E0088-41-100 Item 39

2 Bolt NAS1303-2 Item 37

2 Nut NSA5474-3K7 Item 16

5 Torque tighten the bonding lead nuts, Item 16, to between 0.34-0.40 mdaN

(30-35 lbf.in.).

6 At the two canisters, adjacent to the existing bonding leads, prepare the bonding

areas and attach the bonding leads, Item 39, with:

- two retained bolts, Item (43).

2 Nut NSA5474-4K7 Item 20

7 Torque tighten the nuts, Item 20, to between 0.68-0.70 mdaN (60-70 lbf.in.).

(h) Fuel Booster Pump Config. 06 aircraft

Kit 286064B23R01

Refer to Figure 28, Sheet 1

1 At the rear of the outboard canister, on the canister housing (refer to Detail

B), remove:

- one bolt, Item (47), retain.

- one washer, Item (48), retain.

2 On the canister pipe prepare the bonding area and install:

1 Clamp NSA5519-4B Item 83

1 Lead E0088-10-100 Item 38

1 Bolt NSA5020-3-3 Item 17

1 Nut NSA5474-3K7 Item 16

3 Torque tighten the bonding lead nut, Item 16, to between 0.34-0.40 mdaN

(30-35 lbf.in.).

4 Attach the bonding lead, Item 38, to the canister housing with:

- one retained bolt, Item (47).

- one retained washer, Item (48).

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 61

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

(i) Diffuser

Kit 286064B01R05

Refer to Figure 29, Sheet 2, Detail B

1 At the diffuser, remove:

- one nut, Item (20), discard.

- one washer, Item (52), discard.

- two bolts, Item (46), discard.

- two washers, Item (53), discard.

2 At the support brackets attachment to the structure, remove:

- two nuts, Item (49), discard.

or

- two nuts, Item (4), discard.

NOTE : The bolts that attach the support brackets to the structure are an

interference fit through the wing skin and are therefore bonded,

do not remove.

3 At the diffuser prepare the bonding areas and install:

2 Bolt NAS1304-3 Item 46

2 Washer AN960PD416 Item 53

1 Washer A2824028520000 Item 52

1 Nut NSA5474-4K7 Item 20

4 At the diffuser support bracket attachments to the structure, prepare the bonding

areas around the bolt holes in the brackets only and install:

2 Nut NSA5472-5K7 Item 49

or

2 Nut NSA5472-4K7 Item 4

(j) Fuel Level Sensor

Kit 286064B01R05

Refer to Figure 30, Sheet 2, Detail E

NOTE : It is not necessary to disconnect the sensor for this modification.

1 At the sensor bracket, remove:

- one nut, Item (16), discard

- one washer, Item (74), discard.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 62

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- one bolt, Item (17), discard.

2 At the support bracket of the FQI Probe No.2, remove:

- one nut, Item (16), discard.

- one washer, Item (74), discard.

- one bolt (17), discard.

3 At the support bracket, where it is attached to the structure, remove:

- one nut, Item (49), discard.

NOTE : The bolt that attaches the support bracket to the structure is an

interference fit through the wing skin and is therefore bonded,

do not remove.

4 At the support bracket, where it is attached to the structure, prepare the bonding

area that surrounds the bolt hole and install:

1 Nut NSA5472-5K7 Item 49

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

1 Bolt NSA5020-3-3 Item 17

1 Washer AN960KD10L Item 74

1 Nut NSA5474-3K7 Item 16

6 At the support bracket of the FQI Probe No.2 prepare the bonding areas and

install:

1 Bolt NSA5020-3-3 Item 17

1 Washer AN960KD10L Item 74

1 Nut NSA5474-3K7 Item 16

(7) Rib Bay 2-3

Kit 286064B01R05

Kit 286064B21R01

(a) Diffuser

Kit 286064B01R05

Refer to Figure 29, Sheet 1, Detail A

1 At the diffuser, remove:

- two nuts, Item (20), discard.

- two washers, Item (52), discard.

- one washer, Item (53), (if installed), discard.

- two bolts, Item (46), discard.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 63

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

2 At the diffuser support brackets attachment to the structure, remove:

- two nuts, Item (49), discard.

or

- two nuts, Item (4), discard.

NOTE : The bolts that attach the support bracket to the structure are an

interference fit through the wing skin and are therefore bonded,

do not remove.

3 At the diffuser prepare the bonding areas and install:

2 Bolt NAS1304-3 Item 46

2 Washer A2824028520000 Item 52

1 Washer AN960PD416 Item 53

2 Nut NSA5474-4K7 Item 20

4 At each diffuser support bracket, where it is attached to the structure, prepare

the bonding area around the bolt hole in the bracket only and install:

2 Nut NSA5472-5K7 Item 49

or

2 Nut NSA5472-4K7 Item 4

(b) Calibration Sensor Config. 04 Aircraft.

Kit 286064B21R01

Refer to Figure 30, Sheet 1, Detail C

1 At the sensor bracket, remove:

- one nut, Item (16), discard.

- one bolt, Item (17), discard.

2 At the support bracket, remove:

- one nut, Item (16), discard.

- one bolt, Item (77), discard.

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

1 Bolt NSA5020-3-3 Item 17

1 Nut NSA5474-3K7 Item 16

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

1 Bolt NSA5041VBV3-8 Item 77

1 Nut NSA5474-3K7 Item 16

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 64

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

(8) Rib Bay 5-6

Kit 286064B03R03 All Aircraft

Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

(a) Slat Track Canister 3

Kit 286064B03R03 All Aircraft

Refer to Figure 31, Sheet 1

1 At one of the canister attachment bracket positions (refer to Detail C), remove:

- two nuts, Item (4), discard.

- one washer, Item (5), discard.

- one bolt, Item (6), discard.

- one nut, Item (16), discard.

- one bolt, Item (2), discard.

retain any packing that you may find.

NOTE : The bolts that attach the support bracket to the structure are an

interference fit through the wing skin and are therefore bonded,

do not remove.

2 At the canister attachment bracket prepare the bonding areas. At the support

bracket, where it is attached to the structure, prepare the bonding area around

the bolt hole only. Together with any retained packing, install:

1 Bolt NSA5041VBV4-2 Item 6

1 Washer AN960C416L Item 5

2 Nut NSA5472-4K7 Item 4

1 Bolt NSA5020-3-6 Item 2

1 Nut NSA5474-3K7 Item 16

1 Bolt NSA5020-3-2 Item 70

NOTE : If there is no spacer installed with Item 2 then use the alternate

bolt, Item 70.

(b) Canister Drain Config. 02 Aircraft

Kit 286064B02R02 or Kit 286064B26R01

Refer to Figure 31, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (4), discard.

- four washers, Item (13), discard.

- the two piece plate, Item (10), discard.

- four bolts, Item (11), retain.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 65

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

2 At the canister drain install the one piece plate, LH or RH, as applicable:

1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:

- 3 retained bolts, Item (11).

3 Nut NSA5472-4K7 Item 4

NOTE : If Service Bulletin A300-57-6026 has been embodied, increase

the bolt holes diameter in the new plate, Item 9 or 10, to between

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

bolts, Item (11).

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

countersink only. Install:

- 1 retained bolt, Item (11).

1 Washer NAS1252-416L Item 13

1 Nut NSA5472-4K7 Item 4

4 Apply Sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant

around the new plate to seal.

(9) Rib Bay 8-9

Kit 286064B04R03 All Aircraft

Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

(a) Slat Track Canister 4

Kit 286064B04R03

Refer to Figure 32, Sheet 1

1 At one of the canister attachment bracket positions (refer to Detail B), remove:

- two nuts, Item (4), discard.

- one washer, Item (5), discard.

- one bolt, Item (30), discard.

- one nut, Item (16), discard.

- one bolt, Item (17), discard.

- one washer, Item (88), discard.

retain any packing that you may find.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 66

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

2 At the canister attachment bracket prepare the bonding areas.

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

interference fit in the skin and is therefore bonded, prepare only

around the bolt hole in the bracket at this position.

Install (together with any retained packing) :

1 Bolt NSA5041VBV4-3 Item 30

1 Washer AN960C416L Item 5

2 Nut NSA5472-4K7 Item 4

1 Bolt NSA5020-3-3 Item 17

1 Nut NSA5474-3K7 Item 16

1 Washer AN960KD10 Item 88

(b) Canister Drain Config. 02 Aircraft

Kit 286064B02R02 or Kit 286064B26R01

Refer to Figure 31, Sheet 2

1 At the canister drain remove:

- four nuts, Item (4), discard.

- four washers, Item (13), discard.

- the two piece plate, Item (10), discard.

- four bolts, Item (11), retain.

2 At the canister drain install:

1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:

- 3 retained bolts, Item (11).

3 Nut NSA5472-4K7 Item 4

NOTE : If Service Bulletin A300-57-6026 has been embodied, increase

the bolt holes diameter in the new plate, Item 9 or 10, to between

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

bolts, Item (11).

3 Prepare the bonding area.

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 67

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- one retained bolt, Item (11).

1 Washer NAS1252-416L Item 13

1 Nut NSA5472-4K7 Item 4

4 Apply Sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant

around the new plate to seal.

(c) MLI

Kit 286064B04R03

Refer to Figure 25, Sheet 1, Detail B

1 At the base of the MLI, remove:

- one nut, Item (25), discard.

- one bolt, Item (24), retain.

2 Prepare the bonding area.

NOTE : For the bolt through the wing skin prepare the countersink.

Install:

- 1 retained bolt, Item (24).

1 Nut H19200C4 Item 25

(10) Rib Bay 9-10

Kit 286064B05R01 All Aircraft

Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

(a) Screwjack Canister 3

Kit 286064B05R01

Refer to Figure 33, Sheet 1

1 At the rib adjacent to the canister flange (refer to Detail B), remove:

- one nut, Item (4), discard.

- one bolt, Item (3), discard.

2 At the canister flange, remove:

- one nut, Item (4), discard.

- one bolt, Item (19), discard.

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

1 Lead E0088-40-100 Item 1

1 Bolt ABS0114-4-18 Item 19

1 Washer AN960C416L Item 5

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 68

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

1 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the

bolt, Item 19, is installed from the front spar side and the nut is

installed inside the fuel tank. This will give easier access at some

flanges to torque tighten the nut.

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

the bonding lead, Item 1, with:

1 Bolt NSA5041VBV4-11 Item 3

1 Nut NSA5472-4K7 Item 4

5 Torque tighten the bonding lead nut, Item 4, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

6 At the canister attachment bracket, remove:

- two nuts, Item (16), discard.

- one bolt, Item (31), discard.

- one bolt, Item (7), discard.

retain any packing that you may find.

7 At the canister attachment bracket prepare the bonding areas and install

(together with any retained packing) :

1 Bolt NAS1303-10 Item 31

1 Bolt NSA5041VBV3-5 Item 7

2 Nut NSA5474-3K7 Item 16

(b) Canister Drain Config. 02 Aircraft

Kit 286064B02R02 or Kit 286064B26R01

Refer to Figure 33, Sheet 2, Detail C

1 At the canister drain remove:

- four nuts, Item (4), discard.

- four washers, Item (13), discard.

- the two piece plate, Item 10), discard.

- four bolts, Item (11), retain.

2 At the canister drain install the one piece plate (LH or RH, as applicable) :

1 Plate LH A5715206420000 Item 9

or

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 69

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

1 Plate RH A5715206420100 Item 10

with:

- three retained bolts, Item (11).

3 Nut NSA5472-4K7 Item 4

NOTE : If Service Bulletin A300-57-6026 has been embodied, increase

the bolt holes diameter in the new plate, Item 9 or 10, to between

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

bolts, Item (11).

3 Prepare the bonding area

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- one retained bolt, Item (11).

1 Washer NAS1252-416L Item 13

1 Nut NSA5472-4K7 Item 4

4 Apply Sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant

around the new plate to seal.

(c) Water Drain Valve

Kit 286064B05R01

Refer to Figure 23, Sheet 1, Detail C

1 At the base of the water drain valve, remove:

- one nut, Item (20), discard.

- one bolt, Item (19), retain.

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

1 Clamp AN742D6 Item 15

1 Lead E0088-41-160 Item 14

1 Bolt NSA5020-3-3 Item 17

1 Nut NSA5474-3K7 Item 16

3 Torque tighten the bonding lead nut, Item 16 to between 0.34-0.40 mdaN

(30-35 lbf.in.).

4 At the base of the water drain valve prepare the bonding area

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 70

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- one retained bolt, Item (19).

- the other end of bonding lead, Item 14.

1 Nut NSA5474-4K7 Item 20

(11) Rib Bay 10-11

Kit 286064B06R03 All Aircraft

Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

(a) Slat Track Canister 5

Kit 286064B06R03

Refer to Figure 34, Sheet 1

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

- one nut, Item (4), discard.

- one bolt, Item (32), discard.

2 At the canister flange, remove:

- one nut, Item (4), discard.

- one bolt, Item (40), discard.

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

1 Lead E0088-40-100 Item 1

1 Bolt ABS0114-4-16 Item 40

1 Washer AN960C416L Item 5

1 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the

bolt, Item 40, is installed from the front spar side and the nut is

installed inside the fuel tank. This will give easier access at some

flanges to torque tighten the nut.

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

the bonding lead, Item 1, with:

1 Bolt NSA5041VBV4-9 Item 32

1 Nut NSA5472-4K7 Item 4

5 Torque tighten the bonding lead nut, Item (4), to between 0.68-0.79 mdaN

(60-70 lbf.in.).

6 At the canister attachment bracket (refer to Detail C), remove:

- one nut, Item (4), discard.

- one nut, Item (18), discard.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 71

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- one washer, Item (28), discard.

- one bolt, Item (33), discard.

- one nut, Item (16), discard.

- one bolt, Item (70), discard.

retain any packing that you may find.

7 At the canister attachment bracket prepare the bonding areas.

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

interference fit in the skin and is therefore bonded, prepare only

around the bolt hole in the bracket at this position.

Install:

1 Nut NSA5472-4K7 Item 4

1 Bolt NSA5041VBV3-3 Item 33

1 Washer AN960C10L Item 28

1 Nut NSA5472-3K7 Item 18

1 Bolt NSA5020-3-2 Item 70

1 Nut NSA5474-3K7 Item 16

(b) Canister Drain Config. 02 Aircraft

Kit 286064B02R02 or Kit 286064B26R01

Refer to Figure 31, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (4), discard.

- four washers, Item (13), discard.

- the two piece plate, Item (10), discard.

- four bolts, Item (11), retain.

2 At the canister drain install the one piece plate (LH or RH, as applicable) :

1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:

- three retained bolts, Item (11).

3 Nut NSA5472-4K7 Item 4

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 72

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

NOTE : If Service Bulletin A300-57-6026 has been embodied, increase

the bolt holes diameter in the new plate, Item 9 or 10, to between

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

bolts, Item (11).

3 Prepare the bonding area

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- one retained bolt, Item (11).

1 Washer NAS1252-416L Item 13

1 Nut NSA5472-4K7 Item 4

4 Apply Sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant

around the new plate to seal.

(12) Rib Bay 11-12 (RH Wing Only)

Kit 286064B07R01 All Aircraft

(a) Cadensicon

Refer to Figure 35, Sheet 1

1 At the mounting plate attachment to the front spar (refer to Detail A and B)

remove:

- one nut, Item (20), discard.

- one bolt (Post. Mod. 04741), Item (55), discard.

or:

- one bolt (Pre. Mod. 04741), Item (58), discard.

2 At the cadensicon mounting plate, remove:

- one nut, Item (16), discard.

- one bolt, Item (56), discard.

3 At the cadensicon pipe prepare the bonding area and install:

1 Clamp AN742D8 Item 50

1 Lead E0088-41-100 Item 39

1 Screw NAS1100-3-7 Item 51

1 Nut NSA5474-3K7 Item 16

4 Torque tighten the bonding lead nut, Item 16, to between 0.34-0.40 mdaN

(30-35 lbf.in.).

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 73

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

5 At the front spar prepare the bonding area and attach the bonding lead, Item 39,

to the front spar with (Post Mod. 04741) :

1 Bolt NAS1304-11 Item 55

or Pre Mod. 04741 :

1 Bolt NAS1304-14 Item 58

with:

1 Nut NSA5474-4K7 Item 20

6 At the cadensicon mounting plate prepare the bonding area and install:

1 Bolt NAS1303-7 Item 56

1 Nut NSA5474-3K7 Item 16

(13) Rib Bay 12-13

Kit 286064B08R03 All Aircraft

Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

(a) Slat Track Canister 6

Kit 286064B08R03

Refer to Figure 36, Sheet 1

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

- one nut, Item (4), discard.

- one bolt, Item (32), discard.

2 At the canister flange, remove:

- one nut, Item (4), discard.

- one bolt, Item (44), discard.

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

1 Lead E0088-40-190 Item 89

1 Bolt ABS0114-4-15 Item 44

1 Washer AN960C416L Item 5

1 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the

bolt, Item 44, is installed from the front spar side and the nut is

installed inside the fuel tank. This will give easier access at some

flanges to torque tighten the nut.

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

the bonding lead, Item 1, with:

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 74

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

1 Bolt NSA5041VBV4-9 Item 32

1 Nut NSA5472-4K7 Item 4

5 Torque tighten the bonding lead nut, Item 4, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

6 At the canister attachment bracket, remove:

- one nut, Item (4), discard.

- two nuts, Item (16), discard.

- one washer, Item (28), discard.

- one bolt, Item (41), discard.

- one bolt, Item (42), discard.

retain any packing that you may find.

7 At the canister attachment bracket prepare the bonding areas.

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

interference fit in the skin and is therefore bonded, prepare only

around the bolt hole in the bracket at this position.

Install:

1 Nut NSA5472-4K7 Item 4

1 Bolt NSA5041VBV3-2 Item 41

1 Washer AN960C10L Item 28

2 Nut NSA5474-3K7 Item 16

1 Bolt NAS1303-1 Item 42

(b) Canister Drain Config. 02 Aircraft

Kit 286064B02R02 or Kit 286064B26R01

Refer to Figure 31, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (4), discard.

- four washers, Item (13), discard.

- the two piece plate, Item (10), discard.

- four bolts, Item (11), retain.

2 At the canister drain install the one piece plate (LH or RH, as applicable) :

1 Plate LH A5715206420000 Item 9

or:

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 75

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

1 Plate RH A5715206420100 Item 10

with:

- three retained bolts, Item (11).

3 Nut NSA5472-4K7 Item 4

NOTE : If Service Bulletin A300-57-6026 has been embodied, increase

the bolt holes diameter in the new plate, Item 9 or 10, to between

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

bolts, Item (11).

3 Prepare the bonding area.

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- one retained bolt, Item (11).

1 Washer NAS1252-416L Item 13

1 Nut NSA5472-4K7 Item 4

4 Apply Sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant

around the new plate to seal.

(14) Rib Bay 13-14

Kit 286064B09R04 All Aircraft

(a) MLI

Kit 286064B09R04

Refer to Figure 25, Sheet 1, Detail B

1 At the base of the MLI, remove:

- one nut, Item (25), discard.

- one bolt, Item (24), retain.

2 At the base of the MLI prepare the bonding area.

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- one retained bolt, Item (24).

1 Nut H19200C4 Item 25

(b) Refuel/Defuel Valve - All Aircraft

Kit 286064B09R04

Refer to Figure 37, Sheet 1, Sheet 2

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 76

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

1 If necessary remove and retain the heat shield.

2 On each valve at the front spar, remove:

- one nut, Item (20), discard.

NOTE : Remove and discard any bonding lead tags that may be installed

under the nuts, Item (20).

3 On the valves prepare the bonding areas and install:

2 Lead E0088-41-304 Item 59

2 Nut NSA5474-4K7 Item 20

NOTE : In some instances the bonding lead may be too short to connect to

the fastener shown because of interference from the heat shield.

In this case connect the bonding leads to the fasteners that are

diagonally opposite.

4 Torque tighten the nuts, Item 20, to between 0.68-0.79 mdaN (60-70 lbf.in.).

5 At the two bonding lead tag positions on the front spar, attach the bonding

leads, Item 59, with:

2 Screw NAS1100-3-7 Item 51

2 Nut NSA5474-3K7 Item 16

NOTE : It is Mandatory to put the heat shield in its installation position (if

removed) before you attach the bonding leads, Item 59, to the

bonding tags, (Refer to Sheet 2)

6 Torque tighten the nuts, Item 16, to between 0.34-0.40 mdaN (30-35 lbf.in.).

7 Complete the installation of the heat shield.

(c) High Level Fuel Sensor - All Aircraft

Kit 286064B09R04

Refer to Figure 30, Sheet 1, Detail B

1 At the sensor bracket, remove:

- one nut, Item (16), discard.

- one bolt, Item (70), discard.

2 At the support bracket, remove:

- one nut, Item (16), discard.

- one bolt, Item (17), discard.

or

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 77

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- one bolt, Item (90), discard.

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

1 Bolt NSA5020-3-2 Item 70

1 Nut NSA5474-3K7 Item 16

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

1 Nut NSA5474-3K7 Item 16

1 Bolt NSA5020-3-3 Item 17

or

1 Bolt NSA5020-3-5 Item 90

NOTE : If bolt, Item 17, is too short the bolt, item 90, may be used as

an alternative.

(d) Overwing Refuel Panel

No Kit

Refer to Figure 39, Sheet 1 and AMM 28-25-21, Page block 401

1 Put protective material or masking tape on the wing skin, around the

refuel/defuel panels.

2 At the refuel panels loosen the bolts and lift the panel.

3 Put the panel on the protective material.

4 At the contact surfaces of the panel and the wing skin opening (Refer to the

Figure) use abrasive paper grade 1 or Emery cloth, grade 320, to remove

any protective coating. Clean the prepared surfaces with Cleaning agent

(Mat. No. 11-026).

5 Apply Alodine (Mat. No. 13-002) to the contact surfaces of the panel and

the wing skin.

6 Apply sealant (Mat. No. 09-018) to the contact surface of the wing skin.

7 Align the panel offset bolt and put the panel into the wing skin opening. Make

sure that the panel attachment chain is clear of the bolt holes.

8 Tighten the bolts.

9 Remove any unwanted sealant.

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

11 If necessary, apply paint to the heads of the bolts and the panel and/or wing skin

(Refer to SRM 51-75-10).

(15) Rib Bay 14-15

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 78

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Kit 286064B10R01 All Aircraft

Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

Kit 286064B25R01 Config. 07 Aircraft

(a) Screwjack Canister 4

Kit 286064B10R01

Refer to Figure 40, Sheet 1

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

- one nut, Item (4), discard.

- one bolt, Item (54), discard.

2 At the canister flange, remove:

- one nut, Item (4), discard.

- one bolt, Item (57), discard.

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

1 Lead E0088-40-100 Item 1

1 Bolt ABS0114-4-14 Item 57

1 Washer AN960C416L Item 5

1 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the

bolt, Item 57, is installed from the front spar side and the nut is

installed inside the fuel tank. This will give easier access at some

flanges to torque tighten the nut.

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

the bonding lead, Item 1, with:

1 Bolt NSA5041VBV4-7 Item 54

1 Nut NSA5472-4K7 Item 4

5 Torque tighten the bonding lead nut, Item 4, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

6 At the canister attachment bracket, remove:

- one nut, Item (7), discard.

- one bolt, Item (18), discard.

retain any packing that you may find.

7 At the canister attachment to the structure, remove:

- one nut, Item (18), discard.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 79

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- one bolt, Item (26), discard.

retain any packing that you may find.

8 At the canister attachment to the structure prepare the bonding area and install

(together with any retained packing) :

1 Bolt NSA5041VBV3-7 Item 26

1 Nut NSA5472-3K7 Item 18

9 At the canister bracket prepare the bonding area and install (together with

any retained packing)

1 Bolt NSA5041VBV3-5 Item 7

1 Nut NSA5472-3K7 Item 18

(b) Canister Drain Config. 02 Aircraft

Kit 286064B02R02 or Kit 286064B26R01

Refer to Figure 33, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (4), discard.

- four washers, Item (13), discard.

- the two piece plate, Item (10), discard.

- four bolts, Item (11), retain.

2 At the canister drain install the one piece plate (LH or RH, as applicable) :

1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:

- three retained bolts, Item (11).

3 Nut NSA5472-4K7 Item 4

NOTE : If Service Bulletin A300-57-6026 has been embodied, increase

the bolt holes diameter in the new plate, Item 9 or 10, to between

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

bolts, Item (11).

3 Prepare the bonding area.

NOTE : For the bolt through the wing skin prepare the countersink only.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 80

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Install:

- one retained bolt, Item (11).

1 Washer NAS1252-416L Item 13

1 Nut NSA5472-4K7 Item 4

4 Apply Sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant

around the new plate to seal.

(c) Water Drain Valve - All Aircraft

Kit 286064B10R01

Refer to Figure 23, Sheet 1, Sheet 2

1 At the water drain pipe (refer to Sheet 2, Detail A) disconnect the bonding lead,

Item (84) from the bonding lug, remove:

- one nut, Item (80), discard.

- one bolt, Item (81), discard.

CAUTION : DO NOT REMOVE AND DISCARD ANY OTHER BONDING LEADS

FROM RIB 14.

2 At the bonding leads attachment to rib 14 (adjacent to the compensator), remove:

- one nut, Item (16), discard.

- one bolt, Item (22), retain.

- one bonding lead, Item (84), discard.

NOTE : If necessary, temporarily remove any other bonding leads to get

access to the bonding lead, Item (84) at rib 14.

3 At the bonding leads attachment to rib 14, install (together with any other

bonding leads that you temporarily removed for access) :

- one retained bolt, Item (22).

1 Nut NSA5474-3K7 Item 16

4 At the bonding leads attachment to rib 14, apply protective coating over the

fastener and the bonding leads terminals (refer to AMM 20-28-11, Page block 1).

5 At the water drain pipe, apply Sealant (Mat. No. 09-001) over the bonding lug.

6 At the base of the water drain valve (refer to Sheet 1 Detail A), remove:

- one nut, Item (20), discard.

- one bolt, Item (19), retain.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 81

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

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

1 Clamp AN742D6 Item 15

1 Lead E0088-41-160 Item 14

1 Bolt NSA5020-3-3 Item 17

1 Nut NSA5474-3K7 Item 16

8 At the base of the water drain valve prepare the bonding area.

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- one retained bolt, Item (19).

- the other end of the lead, Item 14.

1 Nut NSA5474-4K7 Item 20

9 Torque tighten the bonding lead nut, Item 16, to between 0.34-0.40 mdaN

(30-35 lbf.in.).

(d) Low Fuel Pressure Switches

Kit 286064B10R01

Refer to Figure 27, Sheet 2, Detail D

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

- one nut, Item (16), discard.

- one bolt, Item (69), discard.

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

2 Clamp NSA5519-2B Item 35

2 Lead E0088-10-100 Item 38

2 Nut NSA5474-3K7 Item 16

2 Bolt NAS1303-2 Item 37

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

and attach the bonding leads, Item 38, with:

2 Bolt NSA5041VBV3-6 Item 69

2 Nut NSA5474-3K7 Item 16

4 Torque tighten the bonding lead nuts, Item 16, to between 0.34-0.40 mdaN

(30-35 lbf.in.).

(e) Fuel Booster Pumps

Kit 286064B10R01

Refer to Figure 41, Sheet 1

1 At each canister flange, remove from the positions shown in the figure:

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 82

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- two bolts, Item (45), discard.

CAUTION : BOLTS THAT GO THROUGH THE FAIRING ARE NOT TO BE USED

AS BONDING POINTS.

2 At the canister flanges prepare the bonding areas and for the bolts through the

wing skin prepare the countersink only.

Install:

4 Bolt NSA5022-4-21 Item 45

3 At each of the fuel pump canisters, adjacent to the existing bonding lead,

(refer to Detail C) remove:

- one nut, Item (20), discard.

- one bolt, Item (43), retain.

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

2 Clamp NSA5519-2B Item 35

2 Lead E0088-41-100 Item 39

2 Bolt NAS1303-2 Item 37

2 Nut NSA5474-3K7 Item 16

5 Torque tighten the bonding lead nuts, Item 16, to between 0.34-0.40 mdaN

(30-35 lbf.in.).

6 At the two fuel pump canisters, adjacent to the existing bonding lead, (refer to

Detail C) prepare the bonding areas and attach the bonding leads, Item 39, with:

- 2 retained bolts, Item (43).

2 Nut NSA5474-4K7 Item 20

7 Torque tighten the nuts, Item 20, to between 0.68-0.79 mdaN (60-70 lbf.in.).

(f) Fuel Jettison System - Blanking Plates

Kit 286064B25R01 Config. 07 Aircraft

Refer to Figure 38, Sheet 1, Detail A and B

NOTE : Access to rib bays 13-14 and 15-16 is also necessary.

1 At the blanking plate at rib 14 (refer to Detail A), remove:

- one nut, Item (20), discard.

- one bolt, Item (62), discard.

2 At the blanking plate prepare the bonding area and install:

1 Bolt NSA5041VBV4-6 Item 62

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 83

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

1 Nut NSA5474-4K7 Item 20

3 At the blanking plate at rib 15 (refer to Detail B), remove:

- one nut, Item (16), discard.

- one bolt, Item (69), discard.

4 At the blanking plate prepare the bonding area and install:

1 Bolt NSA5041VBV3-6 Item 69

1 Nut NSA5474-3K7 Item 16

(16) Rib Bay 15-16

Kit 286064B11R05 All Aircraft

Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

(a) Slat Track Canister 7

Kit 286064B11R05

Refer to Figure 42, Sheet 1

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

- one nut, Item (4), discard.

- one bolt, Item (29), discard.

2 At the canister flange, remove:

- one nut, Item (4), discard.

- one bolt, Item (85), discard

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

1 Lead E0088-40-100 Item 1

1 Bolt ABS0114-4-13 Item 85

1 Washer AN960C416L Item 5

1 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the

bolt, Item 85, is installed from the front spar side and the nut is

installed inside the fuel tank. This will give easier access at some

flanges to torque tighten the nut.

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

bonding lead, Item 1, with:

1 Bolt NSA5041VBV4-8 Item 29

1 Nut NSA5472-4K7 Item 4

5 Torque tighten the bonding lead nut, Item 4, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 84

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

6 At the canister attachment bracket position (refer to Detail C), remove:

- one nut, Item (4), discard.

- two nuts, Item (18), discard.

- one washer, Item (28), discard.

- one bolt, Item (33), discard.

- one bolt, Item (70), discard.

retain any packing that you may find.

7 At the canister attachment bracket prepare the bonding areas.

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

interference fit in the skin and therefore bonded, prepare only

around the bolt hole in the bracket at this position.

Install:

1 Nut NSA5472-4K7 Item 4

1 Bolt NSA5041VBV3-3 Item 33

1 Washer AN960C10L Item 28

2 Nut NSA5472-3K7 Item 18

1 Bolt NSA5020-3-2 Item 70

(b) Canister Drain Config. 02 Aircraft

Kit 286064B02R02 or Kit 286064B26R01

Refer to Figure 31, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (4), discard.

- four washers, Item (13), discard.

- the two piece plate, Item (10), discard.

- four bolts, Item (11), retain.

2 At the canister drain install the one piece plate (LH or RH, as applicable) :

1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:

- three retained bolts, Item (11).

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 85

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

3 Nut NSA5472-4K7 Item 4

NOTE : If Service Bulletin A300-57-6026 has been embodied, increase

the bolt holes diameter in the new plate, Item 9 or 10, to between

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

bolts, Item (11).

3 Prepare the bonding area.

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- one retained bolt, Item (11).

1 Washer NAS1252-416L Item 13

1 Nut NSA5472-4K7 Item 4

4 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant

around the new plate to seal.

(c) Diffuser - All Aircraft

Kit 286064B11R05

Refer to Figure 29, Sheet 3

1 At the diffuser attachment brackets remove:

- two nuts, Item (20), discard.

- two washers, Item (52) (if installed), discard.

- two bolts, Item (46), discard.

- one washer if fitted, Item (53), discard.

2 At the diffuser attachment to the structure, remove:

- two nuts, Item (49), discard.

or

- two nuts, Item (4), discard.

3 At the diffuser prepare the bonding areas and install:

2 Bolt NAS1304-3 Item 46

2 Washer A2824028520000 Item 52

1 Washer AN960PD416 Item 53

2 Nut NSA5474-4K7 Item 20

4 At the diffuser attachment to the structure prepare the bonding areas and install:

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 86

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

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

interference fit in the skin and are therefore bonded, prepare only

around the bolt hole in the bracket at this position.

2 Nut NSA5472-5K7 Item 49

or

2 Nut NSA5472-4K7 Item 4

(d) Water Drain Valve - All Aircraft

Kit 286064B11R05

Refer to Figure 23, Sheet 1

1 At the base of the water drain valve, (refer to Detail A) remove:

- one nut, Item (20), discard.

- one bolt, Item (19), retain.

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

1 Clamp AN742D6 Item 15

1 Lead E0088-41-160 Item 14

1 Bolt NSA5020-3-3 Item 17

1 Nut NSA5474-3K7 Item 16

3 Torque tighten the bonding lead nut, Item 16, to between 0.34-0.40 mdaN

(30-35 lbf.in.).

4 At the base of the water drain valve prepare the bonding area.

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- one retained bolt, Item (19).

- the other end of bonding lead, Item 14.

1 Nut NSA5474-4K7 Item 20

5 Torque tighten the nut, Item 20, to between 0.68-0.79 mdaN (60-70 lbf.in.)

(17) Rib Bay 16-17

Kit 286064B12R01 All Aircraft

(a) Fuel Level Sensor

Refer to Figure 30, Sheet 2, Detail D

1 At the sensor bracket, remove:

- one nut, Item (16), discard.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 87

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- one bolt, Item (70), discard.

2 At the support bracket, remove:

- one nut, Item (16), discard.

- one bolt, Item (71), discard.

3 at the sensor bracket prepare the bonding area and install:

1 Bolt NSA5020-3-2 Item 70

1 Nut NSA5474-3K7 Item 16

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

1 Bolt NSA5020-3-4 Item 71

1 Nut NSA5474-3K7 Item 16

(18) Rib Bay 17-18

Kit 286064B25R01

Refer to Figure 38, Sheet 1

(a) Fuel Jettison System Blanking Plates

1 At the blanking plates, remove:

- one bolt, Item (66), discard.

- one bolt, Item (68), discard.

- one nut, Item (16), discard.

- one nut, Item (20), discard.

2 At the blanking plates prepare the bonding areas and install:

1 Bolt NAS1153-12 Item 66

1 Nut NSA5474-3K7 Item 16

1 Bolt NSA5041VBV4-14 Item 68

1 Nut NSA5474-4K7 Item 20

(19) Rib Bay 18-19

Kit 286064B13R03 All Aircraft

Kit 286064B02R02 or Kit 286064B26R01 for Config. 01 and Config. 02 aircraft.

(a) Slat Track Canister 8

Kit 286064B13R03

Refer to Figure 43, Sheet 1

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

- one nut, Item (4), discard.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 88

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- one bolt, Item (29), discard.

2 At the canister flange, remove:

- one nut, Item (4), discard.

- one bolt, Item (61), discard.

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

1 Lead E0088-40-100 Item 1

1 Bolt ABS0114-4-12 Item 61

1 Washer AN960C416L Item 5

1 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the

bolt, Item 61, is installed from the front spar side and the nut is

installed inside the fuel tank. This will give easier access at some

flanges to torque tighten the nut.

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

the bonding lead, Item 1, with:

1 Bolt NSA5041VBV4-8 Item 29

1 Nut NSA5472-4K7 Item 4

5 Torque tighten the bonding lead nut, Item 4, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

6 At the canister attachment brackets (refer to Detail C) remove:

- one nut, Item (4), discard.

- one bolt, Item (33), discard.

- one washer, Item (28), discard.

- one nut, Item (18), discard.

- one nut, Item (16), discard.

- one bolt, Item (42), discard.

retain any packing that you may find.

7 At the canister attachment bracket prepare the bonding areas

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

interference fit in the skin and is therefore bonded, prepare only

around the bolt hole in the bracket at this position.

Install (together with any retained packing) :

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 89

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

1 Nut NSA5472-4K7 Item 4

1 Bolt NAS1303-1 Item 42

1 Nut NSA5474-3K7 Item 16

1 Bolt NSA5041VBV3-3 Item 33

1 Washer AN960C10L Item 28

1 Nut NSA5472-3K7 Item 18

(b) Canister Drain Config. 01 and Config. 02 aircraft.

Kit 286064B02R02 or Kit 286064B26R01

Refer to Figure 31, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (4), discard.

- four washers, Item (13), discard.

- the two piece plate, Item (10), discard.

- four bolts, Item (11), retain.

2 At the canister drain install the one piece plate (Item 9 LH or Item 10 RH,

as applicable) :

1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:

- three retained bolts, Item (11).

3 Nut NSA5472-4K7 Item 4

NOTE : If Service Bulletin A300-57-6026 has been embodied, increase

the bolt holes diameter in the new plate, Item 9 or 10, to between

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

bolts, Item (11).

3 Prepare the bonding area.

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- one retained bolt, Item (11).

1 Washer NAS1252-416L Item 13

1 Nut NSA5472-4K7 Item 4

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 90

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

4 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant

around the new plate to seal.

(20) Rib Bay 20-21

Kit 286064B14R02 All Aircraft

Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

(a) Screwjack Canister 5

Kit 286064B14R02

Refer to Figure 44, Sheet 1

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

- one nut, Item (4), discard.

- one bolt, Item (54), discard.

2 At the canister flange, remove:

- one nut, Item (4), discard.

- one bolt, Item (63), discard.

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

1 Lead E0088-40-100 Item 1

1 Bolt ABS0114-4-10 Item 63

1 Washer AN960C416L Item 5

1 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the

bolt, Item 63, is installed from the front spar side and the nut is

installed inside the fuel tank. This will give easier access at some

flanges to torque tighten the nut.

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

the bonding lead, Item 1, with:

1 Bolt NSA5041VBV4-7 Item 54

1 Nut NSA5472-4K7 Item 4

5 At the canister attachment bracket, remove:

- one nut, Item (4), discard.

- one bolt, Item (12), discard.

6 At the bracket attachment to the structure, remove:

- one nut, Item (16), discard.

- one bolt, Item (69), discard.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 91

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

7 At the canister attachment bracket prepare the bonding area and install:

1 Bolt NSA5041VBV4-5 Item 12

1 Nut NSA5472-4K7 Item 4

8 At the bracket attachment to the structure prepare the bonding area and install:

1 Bolt NSA5041VBV3-6 Item 69

1 Nut NSA5474-3K7 Item 16

(b) Canister Drain Config. 02 Aircraft

Kit 286064B02R02 or Kit 286064B26R01

Refer to Figure 33, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (4), discard.

- four washers, Item (13), discard.

- the two piece plate, Item (10), discard.

- four bolts, Item (11), retain.

2 At the canister drain install the one piece plate (Item 9 LH or Item 10 RH,

as applicable) :

1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:

- three retained bolts, Item (11).

3 Nut NSA5472-4K7 Item 4

NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the

bolt holes diameter in the new plate, Item 9 or 10, to between

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

Item (11).

3 Prepare the bonding area.

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- one retained bolt, Item (11).

1 Washer NAS1252-416L Item 13

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 92

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

1 Nut NSA5472-4K7 Item 4

4 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant

around the new plate to seal.

(c) MLI - All Aircraft

Kit 286064B14R02

Refer to Figure 25, Sheet 1, Detail B

1 At the base of the MLI, remove:

- one nut, Item (25), discard.

- one bolt, Item (24), retain.

2 At the base of the MLI prepare the bonding area.

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- one retained bolt, Item (24).

1 Nut H19200C4 Item 25

(21) Rib Bay 21-22

Kit 286064B15R04 All Aircraft

Kit 286064B02R02 or Kit 286064B26R01 for Config. 01 and Config. 02 aircraft.

(a) Slat Track Canister 9

Kit 286064B15R04

Refer to Figure 45, Sheet 1

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

- one nut, Item (64), discard.

- one bolt, Item (12), discard.

2 At the canister flange, remove:

- one nut, Item (64), discard.

- one bolt, Item (86), discard.

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

1 Lead E0088-40-100 Item 1

1 Bolt ABS0114-4-9 Item 86

1 Washer AN960C416L Item 5

1 Nut NSA5475-4K7 Item 64

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 93

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

NOTE : The washer, Item 5, is only necessary under the nut, Item 64, if

the bolt, Item 86, is installed from the front spar side and the nut is

installed inside the fuel tank. This will give easier access at some

flanges to torque tighten the nut.

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

the bonding lead, Item 1, with:

1 Bolt NSA5041VBV4-5 Item 12

1 Nut NSA5475-4K7 Item 64

5 Torque tighten the bonding lead nut, Item 2, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

6 At the inboard canister attachment bracket position (refer to Detail C), remove:

- one nut, Item (4), discard.

- two nuts, Item (16), discard.

- one bolt, Item (41), discard.

- one bolt, Item (42), discard.

- one washer, Item (28), discard.

retain any packing that you may find.

7 At the canister attachment bracket prepare the bonding areas.

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

interference fit in the skin and is therefore bonded, prepare only

around the bolt hole in the bracket at this position.

Install (together with any retained packing) :

1 Nut NSA5472-4K7 Item 4

1 Bolt NAS1303-1 Item 42

2 Nut NSA5474-3K7 Item 16

1 Bolt NSA5041VBV3-2 Item 41

1 Washer AN960C10L Item 28

(b) Canister Drain Config. 01 and Config. 02 Aircraft.

Kit 286064B02R02 or Kit 286064B26R01

Refer to Figure 31, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (4), discard.

- four washers, Item (13), discard.

- the two piece plate, Item (10), discard.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 94

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- four bolts, Item (11), retain.

2 At the canister drain install the plate (Item 9 LH or Item 10 RH, as applicable) :

1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:

- three retained bolts, Item (11).

3 Nut NSA5472-4K7 Item 4

NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the

bolt holes diameter in the new plate, Item 9 or 10, to between

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

Item (11).

3 Prepare the bonding area.

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- one retained bolt, Item (11).

1 Washer NAS1252-416L Item 13

1 Nut NSA5472-4K7 Item 4

4 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant

around the new plate to seal.

(22) Rib Bay 24-25

Kit 286064B16R03 All Aircraft

Kit 286064B02R02 or Kit 286064B26R01 for Config. 01 and Config. 02 Aircraft.

(a) Slat Track Canister 10

Kit 286064B16R03

Refer to Figure 46, Sheet 1

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

- one nut, Item (64), discard.

- one bolt, Item (62), discard.

2 At the canister flange, remove:

- one nut, Item (64), discard.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 95

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- one bolt, Item (91), discard.

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

1 Lead E0088-40-100 Item 1

1 Bolt ABS0114-4-6 Item 91

1 Washer AN960C416L Item 5

1 Nut NSA5475-4K7 Item 64

NOTE : The washer, Item 5, is only necessary under the nut, Item 64, if

the bolt, Item 91, is installed from the front spar side and the nut is

installed inside the fuel tank. This will give easier access at some

flanges to torque tighten the nut.

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

the bonding lead, Item 1, with:

1 Bolt NSA5041VBV4-6 Item 62

1 Nut NSA5475-4K7 Item 64

5 Torque tighten the bonding lead nut, Item 2, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

6 At the canister attachment bracket (refer to Detail A), remove:

- two nuts, Item (16), discard.

- one washer, Item (28), discard.

- one bolt, Item (27), discard.

- one washer, Item (87), discard.

- one bolt, Item (7), discard.

retain any packing that you may find.

7 At the canister attachment bracket prepare the bonding areas and install

(together with any retained packing) :

1 Bolt NSA5041VBV3-5 Item 7

1 Washer DHS1085-4 Item 87

1 Bolt NSA5041VBV3-4 Item 27

1 Washer AN960C10L Item 28

2 Nut NSA5474-3K7 Item 16

(b) Canister Drain, Config. 01 and Config. 02 Aircraft.

Kit 286064B02R02 or Kit 286064B26R01

Refer to Figure 31, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (4), discard.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 96

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- four washers, Item (13), discard.

- the two piece plate, Item (10), discard.

- four bolts, Item (11), retain.

2 At the canister drain install the plate (Item 9 LH or Item 10 RH, as applicable) :

1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:

- three retained bolts, Item (11).

3 Nut NSA5472-4K7 Item 4

NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the bolt

hole diameter in the new plate item 9 or 10, to between 7.142-7.193mm

(0.2812-0.2832in) for the second oversize bolts, Item (11).

3 Prepare the bonding area.

NOTE : For the bolt through the skin prepare the countersink only.

Install:

- one retained bolt, Item (11).

1 Washer NAS1252-416L Item 13

1 Nut NSA5472-4K7 Item 4

4 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant

around the new plate to seal.

(23) Rib Bay 25-26

Kit 286064B19R02 - All Aircraft

(a) Fuel Level Sensor

Refer to Figure 30, Sheet 1, Detail A

1 At the sensor bracket, remove:

- one bolt, Item (71), discard.

2 At the support bracket, remove:

- one nut, Item (16), discard.

- one bolt, Item (17), discard.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 97

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

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

1 Bolt NSA5020-3-4 Item 71

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

1 Bolt NSA5020-3-3 Item 17

1 Nut NSA5474-3K7 Item 16

(24) Rib Bay 26-27

Kit 286064B17R01 All Aircraft

Kit 286064B27R01 or Kit 286064B28R01 Config. 02 Aircraft

(a) Screwjack Canister 6

Kit 286064B17R01

Refer to Figure 47, Sheet 1.

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

- one nut, Item (4), discard.

- one bolt, Item (12), discard.

2 At the canister flange, remove:

- one nut, Item (4), discard.

- one bolt, Item (67), discard.

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

1 Lead E0088-40-100 Item 1

1 Bolt ABS0114-4-5 Item 67

1 Washer AN960C416L Item 5

1 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the

bolt, Item 67, is installed from the front spar side and the nut is

installed inside the fuel tank. This will give easier access at some

flanges to torque tighten the nut.

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

the bonding lead, Item 1, with:

1 Bolt NSA5041VBV4-5 Item 12

1 Nut NSA5472-4K7 Item 4

5 Torque tighten the bonding lead nut, Item 4, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

6 At the canister attachment bracket (refer to Detail A), remove

- one nut, Item (18), discard.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 98

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- one washer, Item (28), discard.

- one bolt, Item (72), discard.

retain any packing that you may find.

7 At the canister attachment bracket prepare the bonding area and install:

1 Bolt ABS0114-3-6 Item 72

1 Washer AN960C10L Item 28

1 Nut NSA5472-3K7 Item 18

(b) Canister Drain Config. 02 Aircraft

Kit 286064B27R01 (LH) or Kit 286064B28R01 (RH)

Refer to Figure 47, Sheet 2

1 At the canister drain remove:

- four nuts, Item (4), discard.

- the two piece plate, Item (10), discard.

- four bolts, Item (12), discard.

- packing, Item (6), retain.

2 At the drain spacer, Item (7) attachment to the wing skin, remove:

- one nut, Item (4), discard.

- one bolt, Item (5), retain.

3 At the drain spacer, Item (7) attachment to the wing skin prepare the bonding

area.

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- 1 retained bolt, Item (5).

1 Nut NSA5472-4K7 Item 4

4 At the canister drain install the plate (Item 9 LH or Item 10 RH, as applicable) :

1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 99

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- retained packing, Item (6)

3 Bolt NSA5041VBV4-5 Item 12

3 Nut NSA5472-4K7 Item 4

5 Prepare the bonding area and install:

1 Bolt NSA5041VBV4-5 Item 12

1 Washer NAS1252-416L Item 13

1 Nut NSA5472-4K7 Item 4

6 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant

around the new plate to seal, Also repair any sealant on the bottom flange of

the spacer, Item (7).

(c) MLI

Kit 286064B17R01

Refer to Figure 25, Sheet 1, Detail A

1 At the attachment of the MLI No.6 to the manhole cover, remove:

- seven nuts, Item (16), discard.

- seven bolts, Item (22), retain.

- the protective support tube, retain.

2 At the base of the MLI, remove:

- one nut, Item (20), discard.

- one bolt, Item (24), retain.

3 At the base of the MLI prepare the bonding area and install:

- one retained bolt, Item (24).

1 Nut NSA5474-4K7 Item 20

4 Put the protective tube in position over the MLI and install:

- six retained bolts, Item (22).

6 Nut NSA5474-3K7 Item 16

5 Prepare the bonding area.

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- one retained bolt, Item (22).

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 100

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

1 Nut NSA5474-3K7 Item 16

(d) Overwing Refuel Panel

No Kit

Refer to Figure 39 and AMM 28-25-21, Page block 401

1 Put protective material or masking tape on the wing skin, around the

refuel/defuel panels.

2 At the refuel panels loosen the bolts and lift the panel.

3 Put the panel on the protective material.

4 At the contact surfaces of the panel and the wing skin opening (Refer to the

Figure) use abrasive paper grade 1 or Emery cloth, grade 320, to remove

any protective coating. Clean the prepared surfaces with Cleaning agent

(Mat. No. 11-026).

5 Apply Alodine (Mat. No. 13-002) to the contact surfaces of the panel and

the wing skin.

6 Apply sealant (Mat. No. 09-018) to the contact surface of the wing skin.

7 Align the panel offset bolt and put the panel into the wing skin opening. Make

sure that the panel attachment chain is clear of the bolt holes.

8 Tighten the bolts.

9 Remove any unwanted sealant.

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

11 If necessary, apply paint to the heads of the bolts and the panel and/or wing skin

(Refer to SRM 51-75-10).

(25) Rib Bay 27-28

Kit 286064B18R04 All Aircraft

Kit 286064B02R02 or Kit 286064B26R01 for Config. 01 and Config. 02 Aircraft.

(a) Slat Track Canister 11

Kit 286064B18R04

Refer to Figure 48, Sheet 1

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

- one nut, Item (64), discard.

- one bolt, Item (78), discard.

2 At the canister flange, remove:

- one nut, Item (64), discard.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 101

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- one bolt, Item (79), discard.

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

1 Lead E0088-40-100 Item 1

1 Bolt ABS0114-4-4 Item 79

1 Washer AN960C416L Item 5

1 Nut NSA5475-4K7 Item 64

NOTE : The washer, Item 5, is only necessary under the nut, Item 64, if

the bolt, Item 79, is installed from the front spar side and the nut is

installed inside the fuel tank. This will give easier access at some

flanges to torque tighten the nut.

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

the bonding lead, Item 1, with:

1 Bolt NSA5041VBV4-4 Item 78

1 Nut NSA5475-4K7 Item 64

5 Torque tighten the bonding lead nut, Item 2, to between 0.68-0.79 mdaN

(60-70 lbf.in.).

6 At the canister attachment bracket, remove:

- one nut, Item (16), discard.

- one washer, Item (87), discard.

- one bolt, Item (7), discard.

7 At the bracket attachment to the structure, remove:

- one nut, Item (16), discard.

- one washer, Item (65), discard.

- one bolt, Item (7), discard.

retain any packing that you may find.

8 At the bracket attachment to the structure prepare the bonding area and install

(together with any retained packing) :

1 Bolt NSA5041VBV3-5 Item 7

1 Washer DHS783-63-18 Item 65

1 Nut NSA5474-3K7 Item 16

9 At the canister attachment bracket prepare the bonding area and install:

1 Bolt NSA5041VBV3-5 Item 7

1 Washer DHS1085-4 Item 87

1 Nut NSA5474-3K7 Item 16

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 102

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

(b) Canister Drain, Config. 01 and Config. 02 Aircraft.

Kit 286064B02R02 or Kit 286064B26R01

Refer to Figure 31, Sheet 2

1 At the canister drain, remove:

- four nuts, Item (4), discard.

- four washers, Item (13), discard.

- the two piece plate, Item (10), discard.

- four bolts, Item (11), retain.

2 At the canister drain install the plate (Item 9 LH or Item 10 RH, as applicable) :

1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:

- three retained bolts, Item (11).

3 Nut NSA5472-4K7 Item 4

NOTE : If Service Bulletin A300-57-6026 has been embodied, increase

the bolt holes diameter in the new plate, Item 9 or 10, to between

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

bolts, Item (11).

3 Prepare the bonding area.

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- one retained bolt, Item (11).

1 Washer NAS1252-416L Item 13

1 Nut NSA5472-4K7 Item 4

4 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant

around the new plate to seal.

(c) Water Drain

Kit 286064B18R04

Refer to Figure 23, Sheet 1, Detail B

1 At the water drain, remove:

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 103

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

- one nut, Item (20), discard.

- one bolt, Item (19), retain.

2 At the water drain prepare the bonding area and install:

- one retained bolt, Item (19).

1 Nut NSA5474-4K7 Item 20

(d) Fuel Overflow Sensor

Kit 286064B18R04

Refer to Figure 30, Sheet 4

NOTE : Access to Rib Bay 26-27 is also necessary.

1 At the sensor bracket, remove:

- one nut, Item (16), discard.

- one bolt, Item (7), discard.

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

1 Bolt NSA5041VBV3-5 Item 7

1 Nut NSA5474-3K7 Item 16

(e) Overpressure Protector

Kit 286064B18R04

Refer to Figure 49, Sheet 1

1 At the flange of the overpressure protector, remove:

- two bolts, Item (30), discard.

2 Prepare the bonding areas and install:

2 Bolt NAS1304-4 Item 30

(26) Wings Fuel Tank Equipment - Rib Bay 1-2 Config. 08 Aircraft

Kit 286064B20R06

(a) Forward Rib Bay Water Drain Valve

Refer to Figure 23, Sheet 1, Detail D

1 At the water drain valve, remove:

- one nut, Item (20), discard.

- one bolt, Item (19), retain.

2 At the base of the water drain valve prepare the bonding area.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 104

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- 1 retained bolt, Item (19).

1 Nut NSA5474-4K7 Item 20

(b) Aft Rib Bay Water Drain Valve.

Refer to Figure 23, Sheet 1, Detail A

1 At the water drain valve, remove:

- one nut, Item (20), discard.

- one bolt, Item (19), retain.

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

1 Clamp AN742D6 Item 15

1 Lead E0088-41-160 Item 14

1 Bolt NSA5020-3-3 Item 17

1 Nut NSA5474-3K7 Item 16

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

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- one retained bolt, Item (19)

- the other end of the lead, Item 14.

1 Nut NSA5474-4K7 Item 20

(c) Water Scavenge Pipe.

Refer to Figure 24, Sheet 2

1 At the support bracket and pipe clamp positions (Refer to Detail A, Detail B

and Detail C) remove:

- Four nuts, Item (16), discard.

- Four bolts, Item (37), discard.

- Four clamps, Item (22), retain.

2 On the support brackets and pipe clamp positions, (refer to Detail A, Detail B

and C) , prepare the bonding areas and install:

- four retained clamps, Item (22)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 105

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

4 Bolt NAS1303-2 Item 37

4 Nut NSA5474-3K7 Item 16

(d) MLI

Refer to Figure 25, Sheet 1, Detail B

1 At the base of the MLI, remove:

- one nut, Item (25), discard.

- one bolt, Item (24), retain.

2 At the base of the MLI prepare the bonding area.

NOTE : For the bolt through the wing skin prepare the countersink only.

Install:

- one retained bolt, Item (24).

1 Nut H19200C4 Item 25

(e) Fuel Feed Pipe Support

Refer to Figure 26, Sheet 1

1 At the fuel pipe support bracket, upper section, remove:

- one nut, Item (16), discard.

- one bolt, Item (27), discard.

2 At the fuel pipe support bracket, lower section, remove:

- one nut, Item (16), discard.

- one bolt, Item (77), discard.

- one washer, Item (28), if installed, discard.

3 At the fuel pipe support bracket, upper section, prepare the bonding area

and install:

1 Bolt NSA5041VBV3-4 Item 27

1 Nut NSA5474-3K7 Item 16

4 At the fuel pipe support bracket, lower section, prepare the bonding area and

install:

1 Bolt NSA5041VBV3-8 Item 77

1 Nut NSA5474-3K7 Item 16

and, if applicable :

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 106

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

1 Washer AN960C10L Item 28

(f) Low Fuel Pressure Switches

Refer to Figure 27, Sheet 1

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

- one nut, Item (16), discard.

- one bolt, Item (34), discard.

2 At the two pressure switch pipes prepare the bonding areas and install:

2 Clamp NSA5519-2B Item 35

2 Lead E0088-10-100 Item 38

2 Bolt NAS1303-2 Item 37

2 Nut NSA5474-3K7 Item 16

3 At the two pressure switch attachments to the rear spar prepare the bonding

areas and attach the bonding leads, Item 38, with:

2 Bolt NSA5041VBV3-10 Item 34

2 Nut NSA5474-3K7 Item 16

4 Torque tighten the bonding lead nuts, Item 16, to between 0.34-0.40 mdaN

(30-35 lbf.in.).

(g) Fuel Booster Pump Canisters

Refer to Figure 28, Sheet 1

1 At each canister flange, remove from the positions shown in the figure:

- two bolts, Item (45), discard.

CAUTION : BOLTS THAT GO THROUGH THE FAIRING ARE NOT TO BE USED

AS BONDING POINTS.

2 At the two canister flanges prepare the bonding areas.

NOTE : For the bolts through the wing skin prepare the countersinks only.

Install:

4 Bolt NSA5022-4-21 Item 45

3 At each of the fuel pump canisters, adjacent to the existing bonding lead,

(refer to Detail C) remove:

- one nut, Item (20), discard.

- one bolt, Item (43), retain.

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

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2 Clamp NSA5519-2B Item 35

2 Lead E0088-41-100 Item 39

2 Bolt NAS1303-2 Item 37

2 Nut NSA5474-3K7 Item 16

5 Torque tighten the bonding leads nuts, Item 16, to between 0.34-0.40 mdaN

(30-35 lbf.in.).

6 At each of the fuel pump canisters, adjacent to the existing bonding lead, (refer to

Detail C) prepare the bonding areas and attach the bonding leads, Item 39, with:

- one retained bolts, Item (43).

2 Nut NSA5474-4K7 Item 20

7 Torque tighten the nut, Item 20 to between 0.68-0.70 mdaN (60-70 lbf.in.).

(h) Diffuser

Refer to Figure 29, Sheet 4, Detail B

1 At the diffuser, remove:

- one nut, Item (20), discard.

- one washer, Item (52), discard.

- two bolts, Item (46), discard.

- two washers, Item (53), discard.

2 At the diffuser prepare the bonding areas and install:

2 Bolt NAS1304-3 Item 46

2 Washer AN960PD416 Item 53

1 Washer A2824028520000 Item 52

1 Nut NSA5474-4K7 Item 20

(i) Low Level Fuel Sensor

Refer to Figure 30, Sheet 3, Detail E

NOTE : It is not necessary to disconnect the sensor for this modification.

1 At the sensor bracket, remove:

- one nut, Item (16), discard

- one washer, Item (74), discard.

- one bolt, Item (17), discard.

2 At the support bracket of the FQI Probe No.2, remove:

- one nut, Item (16), discard.

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- one washer, Item (74), discard.

- one bolt, Item (17), discard.

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

1 Bolt NSA5020-3-3 Item 17

1 Washer AN960KD10L Item 74

1 Nut NSA5474-3K7 Item 16

4 At the support bracket of the FQI Probe No.2 prepare the bonding areas and

install:

1 Bolt NSA5020-3-3 Item 17

1 Washer AN960KD10L Item 74

1 Nut NSA5474-3K7 Item 16

(27) ADDITIONAL WORK (Introduced by Rev 01)

This additional work is necessary if this Service Bulletin, at the original issue, has been

embodied on aircraft which were not Config. 05 aircraft.

(a) Refuel/Defuel Valve LH Wing - Rib Bay 13-14

Kit 286064B39R00

Refer to Figure 37, Sheet 1, Sheet 2

1 Get access to Rib Bay 13-14 refer to para 3.A (1) Preparation.

2 If necessary remove and retain the heat shield.

3 On each valve at the front spar, remove:

- one nut, Item (20), discard.

NOTE : Remove and discard any bonding lead tags that may be installed

under the nuts, Item (20).

4 On the valves prepare the bonding areas and install:

2 Lead E0088-41-304 Item 59

2 Nut NSA5474-4K7 Item 20

5 Torque tighten the nuts, Item 20, to between 0.68-0.79 mdaN (60-70 lbf.in.).

6 At the two bonding lead tag positions on the front spar, attach the bonding

leads, Item 59, with:

2 Screw NAS1100-3-7 Item 51

2 Nut NSA5474-3K7 Item 16

NOTE : It is Mandatory to put the heat shield in its installation position (if

removed) before you attach the bonding leads, Item 59, to the

bonding tags, (Refer to Sheet 2)

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7 Torque tighten the nuts, Item 16, to between 0.34-0.40 mdaN (30-35 lbf.in.).

8 Complete the installation of the heat shield.

(28) ADDITIONAL WORK

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

NOTE : In Fuel Center Tank, the modification consists in :

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

Figure 50, Sheet 1.

For each point identified check the presence of blue coat :

- If blue coat present, no further action.

- If no blue coat then :

Measure the electrical resistance between part and the structure, (Refer

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

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

- If the ohmic resistance >10mhm, do the bonding, (Refer to AMM

20-28-11, Page block 001).

1 Check the bonding points Item 25 on the rib 1 (LH side).

Refer to Figure 50, Sheet 1, (General location)

Refer to Figure 51, Sheets 1 and 2, (Detailed location)

Refer to Figure 52, Sheet 1, (Result table)

C. TEST

(1) Wings Fuel Tanks

(a) After the worksteps in para. D. CLOSE UP, (1) (a) thru (d) have been completed, do

a leak test of the wings fuel tanks (Refer to AMM 28-11-00, Page block 501).

NOTE : Fuel leaks are not permitted.

(2) Center Tank

(a) Close the access doors 147AZ and 148AZ (Refer to AMM 28-11-29, Page block 401).

(b) Refuel the center tank (Refer to AMM 28-25-00, Page block 301).

(c) Connection of the batteries :

- For the job set-up, refer to the removal/installation of the batteries (Refer to AMM

24-31-11, Page block 401).

- Remove the blanking caps from the disconnected electrical connectors.

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- Make sure that the electrical connectors are clean and in correct condition.

- Connect the connectors on the batteries.

- Turn the knurled nut a quarter turn.

(3) Preliminary Tests:

(a) Initial conditions

1 On each connectors that you disconnected, do a visual check as defined by

ESPM 20-51-10 to make sure that.

- The label of the plug is the same as the label on the receptacle.

- The plug is correctly locked.

(b) Perform the secondary electrical bonding of panels (Refer to AMM 20-28-11, Page

block 001).

NOTE : Use the procedure corresponding to the components which are modified

during the accomplishment of the Service Bulletin.

(c) Do the Functional Test of the Instrument and Panel Integral Lighting (Refer to AMM

33-13-00, Page block 501).

(d) Do the Operational Test of the Annunciator Light Test (Refer to AMM 33-14-00,

Page block 501).

(4) ADDITIONAL WORK (Introduced by Rev 01)

(a) After the worksteps in para. D. CLOSE UP, (1) (a) thru (d) have been completed, do

a leak test of the wings fuel tanks (Refer to AMM 28-11-00, Page block 501).

(b) Preliminary Tests:

1 Initial conditions

a On each connectors that you disconnected, do a visual check as defined by

ESPM 20-51-10 to make sure that.

- The label of the plug is the same as the label on the receptacle.

- The plug is correctly locked.

2 Do the Functional Test of the Instrument and Panel Integral Lighting (Refer

to AMM 33-13-00, Page block 501).

3 Do the Operational Test of the Annunciator Light Test (Refer to AMM 33-14-00,

Page block 501).

4 Do the Operational Test of the Quantity Indicating System (Refer to AMM

28-42-00, Page block 501).

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5 Do the test after the Disconnection/Reconnection of plugs 1076VC and 2022VC

(If necessary).

(5) ADDITIONAL WORK

(a) Test

1 Preparation

a Close the access doors 147AZ and 148AZ (Refer to AMM 28-11-29,

Page block 401).

b Install the manhole covers (Refer to AMM 28-11-22, Page block 401).

c Refuel the center fuel tank and wing fuel tanks (Refer to AMM 28-25-00,

Page block 301).

d Connection of the batteries :

- For the job set-up, refer to the removal/installation of the batteries (Refer

to AMM 24-31-11, Page block 401).

- Remove the blanking caps from the disconnected electrical connectors.

- Make sure that the electrical connectors are clean and in correct condition.

- Connect the connectors on the batteries

- Turn the knurled nut a quarter turn.

2 Preliminary Tests:

a Initial conditions

- On each connectors that you disconnected, do a visual check as defined

by ESPM 20-51-10 to make sure that.

. The label of the plug is the same as the label on the receptacle.

. The plug is correctly locked.

b Perform the secondary electrical bonding of panels (Refer to AMM 20-28-11,

Page block 001).

NOTE : Use the procedure corresponding to the components which are

modified during the accomplishment of the Service Bulletin.

c Do the Functional Test of the Instrument and Panel Integral Lighting (Refer

to AMM 33-13-00, Page block 501).

d Do the Operational Test of the Annunciator Light Test (Refer to AMM

33-14-00, Page block 501).

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D. CLOSE UP

(1) Wings Fuel Tanks

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the heat shields (Refer to AMM 57-23-11, Page block 401).

(c) Install the wings fuel tanks manhole covers and access doors/panels (Refer to AMM

28-11-22, Page block 401 and AMM 28-11-29, Page block 401).

(d) Remove all the warning notices.

(e) Close the Main Landing Gear (MLG) doors (Refer to AMM 32-12-11, Page block 301).

(f) Refuel the wings fuel tanks (Refer to AMM 28-25-00, Page block 1).

(g) Remove the safety clips and tags and close these circuit breakers :

PANEL DESIGNATION FIN LOCATION

22VU FUEL/TK LO LVL AND CAL/L OUTR &

R INR & CTR R

1QJ 208/B26

22VU FUEL/TK LO LVL AND CAL/R OUTR &

L INR & CTR L

2QJ 208/B27

132VU FUEL/FUELING HI LVL 6QJ 321/P57

132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58

132VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 321/P56

132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59

132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60

132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

or

PANEL DESIGNATION FIN LOCATION

22VU FUEL/TK LO LVL AND CAL/L OUTR &

R INR & CTR R

1QJ 208/B26

22VU FUEL/TK LO LVL AND CAL/R OUTR &

L INR & CTR L

2QJ 208/B27

128VU FUEL/FUELING HI LVL 6QJ 805/L87

128VU FUEL/FUELING OVERFLOW AND CAL 5QJ 805/L86

128VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 805/L88

128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83

128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84

128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85

(h) Remove the access platforms.

(i) Put the aircraft and the systems in a normal operating condition.

(2) ADDITIONAL WORK (Introduced by Rev 01)

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(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the heat shields (Refer to AMM 57-23-11, Page block 401).

(c) Install the wings fuel tanks manhole covers and access doors/panels (Refer to AMM

28-11-22, Page block 401 and AMM 28-11-29, Page block 401).

(d) Refuel the wings fuel tanks (Refer to AMM 28-25-00, Page block 1).

(e) Remove the access platforms.

(f) Put the aircraft and the systems in a normal operating condition.

(3) ADDITIONAL WORK

(a) Close-up

1 Make sure that the work areas are clean and clear of tools and other items

of equipment.

2 Remove all the warning notices.

3 Close the Main Landing Gear (MLG) doors (Refer to AMM 32-12-11, Page

block 301).

4 Remove the safety clips and tags and close these circuit breakers :

Depending on aircraft configuration

PANEL DESIGNATION FIN LOCATION

22VU FUEL/TK LO LVL AND CAL/L OUTR &

R INR & CTR R

1QJ 208/B26

22VU FUEL/TK LO LVL AND CAL/R OUTR &

L INR & CTR L

2QJ 208/B27

132VU FUEL/FUELING HI LVL 6QJ 321/P57

132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58

132VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 321/P56

132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59

132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60

132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

or

PANEL DESIGNATION FIN LOCATION

22VU FUEL/TK LO LVL AND CAL/L OUTR &

R INR & CTR R

1QJ 208/B26

22VU FUEL/TK LO LVL AND CAL/R OUTR &

L INR & CTR L

2QJ 208/B27

128VU FUEL/FUELING HI LVL 6QJ 805/L87

128VU FUEL/FUELING OVERFLOW AND CAL 5QJ 805/L86

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 114

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SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION

128VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 805/L88

128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83

128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84

128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85

5 Remove the access platforms.

6 Restore the systems and the aircraft to normal operating condition.

E. DOCUMENTATION

Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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Figure 1, Sheet 1

Decomposition of the Center Tank

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Figure 2, Sheet 1

Location of the Bonding Points at FR44

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Figure 2, Sheet 2

Location of the Bonding Points at FR44

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SERVICE BULLETIN

Figure 2, Sheet 3

Location of the Bonding Points at FR44

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SERVICE BULLETIN

Figure 2, Sheet 4

Location of the Bonding Points at FR44

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SERVICE BULLETIN

Figure 2, Sheet 5

Location of the Bonding Points at FR44

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SERVICE BULLETIN

Figure 2, Sheet 6

Location of the Bonding Points at FR44

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SERVICE BULLETIN

Figure 3, Sheet 1

Bonding Points to Check at FR44

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SERVICE BULLETIN

Figure 4, Sheet 1

Location of the Bonding Points at FR47

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SERVICE BULLETIN

Figure 4, Sheet 2

Location of the Bonding Points at FR47

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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SERVICE BULLETIN

Figure 4, Sheet 3

Location of the Bonding Points at FR47

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REVISION No. : 03 - Dec 15/08 Page : 126

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SERVICE BULLETIN

Figure 4, Sheet 4

Location of the Bonding Points at FR47

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SERVICE BULLETIN

Figure 4, Sheet 5

Location of the Bonding Points at FR47

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SERVICE BULLETIN

Figure 4, Sheet 6

Location of the Bonding Points at FR47

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SERVICE BULLETIN

Figure 4, Sheet 7

Location of the Bonding Points at FR47

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SERVICE BULLETIN

Figure 4, Sheet 8

Location of the Bonding Points at FR47

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SERVICE BULLETIN

Figure 4, Sheet 9

Location of the Bonding Points at FR47

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SERVICE BULLETIN

Figure 4, Sheet 10

Location of the Bonding Points at FR47

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SERVICE BULLETIN

Figure 4, Sheet 11

Location of the Bonding Points at FR47

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SERVICE BULLETIN

Figure 4, Sheet 12

Location of the Bonding Points at FR47

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SERVICE BULLETIN

Figure 4, Sheet 13

Location of the Bonding Points at FR47

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SERVICE BULLETIN

Figure 4, Sheet 14

Location of the Bonding Points at FR47

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SERVICE BULLETIN

Figure 4, Sheet 15

Location of the Bonding Points at FR47

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SERVICE BULLETIN

Figure 4, Sheet 16

Location of the Bonding Points at FR47

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SERVICE BULLETIN

Figure 4, Sheet 17

Location of the Bonding Points at FR47

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SERVICE BULLETIN

Figure 5, Sheet 1

Bonding Points to Check at FR47

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SERVICE BULLETIN

Figure 6, Sheet 1

Location of the Bonding Points on the Rib 1 (LH side)

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Figure 6, Sheet 2

Location of the Bonding Points on the Rib 1 (LH side)

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REVISION No. : 03 - Dec 15/08 Page : 143

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SERVICE BULLETIN

Figure 6, Sheet 3

Location of the Bonding Points on the Rib 1 (LH side)

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SERVICE BULLETIN

Figure 7, Sheet 1

Bonding Points to check on the Rib 1 (LH side)

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REVISION No. : 03 - Dec 15/08 Page : 145

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SERVICE BULLETIN

Figure 8, Sheet 1

Location of the Bonding Points on the Intrados Panel

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Figure 8, Sheet 2

Location of the Bonding Points on the Intrados Panel

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Figure 8, Sheet 3

Location of the Bonding Points on the Intrados Panel

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Figure 8, Sheet 4

Location of the Bonding Points on the Intrados Panel

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SERVICE BULLETIN

Figure 8, Sheet 5

Location of the Bonding Points on the Intrados Panel

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Figure 8, Sheet 6

Location of the Bonding Points on the Intrados Panel

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SERVICE BULLETIN

Figure 8, Sheet 7

Location of the Bonding Points on the Intrados Panel

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Figure 8, Sheet 8

Location of the Bonding Points on the Intrados Panel

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 153

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 8, Sheet 9

Location of the Bonding Points on the Intrados Panel

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 154

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 8, Sheet 10

Location of the Bonding Points on the Intrados Panel

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 155

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 9, Sheet 1

Bonding Points to check on the Intrados Panel

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 156

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 10, Sheet 1

Location of the Bonding Points on the Rib 1 (RH side)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 157

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 10, Sheet 2

Location of the Bonding Points on the Rib 1 (RH side)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 158

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 10, Sheet 3

Location of the Bonding Points on the Rib 1 (RH side)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 159

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 10, Sheet 4

Location of the Bonding Points on the Rib 1 (RH side)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 160

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 10, Sheet 5

Location of the Bonding Points on the Rib 1 (RH side)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 161

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 10, Sheet 6

Location of the Bonding Points on the Rib 1 (RH side)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 162

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 11, Sheet 1

Bonding Points to check on the Rib 1 (RH side)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 163

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 12, Sheet 1

Location of the Bonding Points on the Extrados Panel

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 164

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 12, Sheet 2

Location of the Bonding Points on the Extrados Panel

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 165

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 12, Sheet 3

Location of the Bonding Points on the Extrados Panel

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 166

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 12, Sheet 4

Location of the Bonding Points on the Extrados Panel

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 167

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 12, Sheet 5

Location of the Bonding Points on the Extrados Panel

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 168

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 12, Sheet 6

Location of the Bonding Points on the Extrados Panel

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 169

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 12, Sheet 7

Location of the Bonding Points on the Extrados Panel

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 170

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 12, Sheet 8

Location of the Bonding Points on the Extrados Panel

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 171

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 13, Sheet 1

Bonding Points to check on the Extrados Panel

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 172

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 14, Sheet 1

Modification of the Refueling Pipes on LH side between FR44 and FR47 (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 173

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 14, Sheet 2

Modification of the Refueling Pipes on LH side between FR44 and FR47 (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 174

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 14, Sheet 3

Modification of the Refueling Pipes on LH side between FR44 and FR47 (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 175

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 15, Sheet 1

Modification of the TTS pipes (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 176

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 15, Sheet 2

Modification of the TTS pipes (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 177

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 15, Sheet 3

Modification of the TTS pipes (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 178

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 15, Sheet 4

Modification of the TTS pipes (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 179

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 15, Sheet 5

Modification of the TTS pipes (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 180

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 15, Sheet 6

Modification of the TTS pipes (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 181

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 15, Sheet 7

Modification of the TTS pipes (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 182

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 15, Sheet 8

Modification of the TTS pipes (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 183

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 16, Sheet 1

Modification of the Feed Pipes (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 184

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 16, Sheet 2

Modification of the Feed Pipes (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 185

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 16, Sheet 3

Modification of the Feed Pipes (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 186

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 17, Sheet 1

Modification of the Cross Feed Pipe (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 187

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 17, Sheet 2

Modification of the Cross Feed Pipe (Kit 286064A01R05)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 188

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 18, Sheet 1

Modification of the Refueling Pipes on LH side between FR44 and FR47 (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 189

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 18, Sheet 2

Modification of the Refueling Pipes on LH side between FR44 and FR47 (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 190

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 18, Sheet 3

Modification of the Refueling Pipes on LH side between FR44 and FR47 (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 191

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 19, Sheet 1

Modification of the TTS pipes (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 192

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 19, Sheet 2

Modification of the TTS pipes (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 193

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 19, Sheet 3

Modification of the TTS pipes (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 194

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 19, Sheet 4

Modification of the TTS pipes (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 195

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 19, Sheet 5

Modification of the TTS pipes (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 196

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 19, Sheet 6

Modification of the TTS pipes (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 197

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 19, Sheet 7

Modification of the TTS pipes (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 198

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 19, Sheet 8

Modification of the TTS pipes (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 199

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 20, Sheet 1

Modification of the Feed Pipes (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 200

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 20, Sheet 2

Modification of the Feed Pipes (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 201

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 20, Sheet 3

Modification of the Feed Pipes (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 202

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 21, Sheet 1

Modification of the Cross Feed Pipe (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 203

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 21, Sheet 2

Modification of the Cross Feed Pipe (Kit 286064A02R02)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 204

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 22, Sheet 1

Electrical Bonding of the Canister Pumps (Kit 286064A03R00)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 205

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 22, Sheet 2

Electrical Bonding of the Canister Pumps (Kit 286064A03R00)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 206

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 22, Sheet 3

Electrical Bonding of the Canister Pumps (Kit 286064A03R00)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 207

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 23, Sheet 1

Water Drains and Water Drain Valves Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 208

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 23, Sheet 2

Water Drains and Water Drain Valves Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 209

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 24, Sheet 1

Water Scavenge Pipes Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 210

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 24, Sheet 2

Water Scavenge Pipes Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 211

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 25, Sheet 1

Magnetic Level Indicators Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 212

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 26, Sheet 1

Fuel Feed Pipe- Support Bracket Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 213

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 27, Sheet 1

Fuel Booster Pumps - Low Pressure Warning Switches Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 214

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 27, Sheet 2

Fuel Booster Pumps - Low Pressure Warning Switches Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 215

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 28, Sheet 1

Fuel Booster Pumps Canisters - Inner Tanks Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 216

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 29, Sheet 1

Fuel Diffusers - Inner and Outer Tanks Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 217

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 29, Sheet 2

Fuel Diffusers - Inner and Outer Tanks Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 218

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 29, Sheet 3

Fuel Diffusers - Inner and Outer Tanks Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 219

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 29, Sheet 4

Fuel Diffusers - Inner and Outer Tanks Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 220

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 30, Sheet 1

Wings - Fuel Level Sensors Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 221

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 30, Sheet 2

Wings - Fuel Level Sensors Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 222

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 30, Sheet 3

Wings - Fuel Level Sensors Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 223

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 30, Sheet 4

Wings - Fuel Level Sensors Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 224

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 31, Sheet 1

Slat Track Canister 3 and Typical Canister Drain Attachment Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 225

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 31, Sheet 2

Slat Track Canister 3 and Typical Canister Drain Attachment Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 226

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 32, Sheet 1

Slat Track Canister 4 Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 227

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 33, Sheet 1

Screwjack Canister 3 and Typical Canister Drain Attachment Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 228

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 33, Sheet 2

Screwjack Canister 3 and Typical Canister Drain Attachment Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 229

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 34, Sheet 1

Slat Track Canister 5 Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 230

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 35, Sheet 1

Cadensicon (RH Wing only) Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 231

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 36, Sheet 1

Slat Track Canister 6 Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 232

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 37, Sheet 1

Refuel/Defuel Valves Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 233

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 37, Sheet 2

Refuel/Defuel Valves Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 234

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 38, Sheet 1

Provision for a Fuel Jettison System - Blanking Plates Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 235

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 39, Sheet 1

Overwing Refuel/Defuel Panels Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 236

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 40, Sheet 1

Screwjack Canister 4 Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 237

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 41, Sheet 1

Fuel Booster Pumps Canisters - Outer Tanks Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 238

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A300-600 A300-600

SERVICE BULLETIN

Figure 42, Sheet 1

Slat Track Canister 7 Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 239

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 43, Sheet 1

Slat Track Canister 8 Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 240

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 44, Sheet 1

Screwjack Canister 5 Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 241

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 45, Sheet 1

Slat Track Canister 9 Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 242

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 46, Sheet 1

Slat Track Canister 10 Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 243

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 47, Sheet 1

Screwjack Canister 6 Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 244

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 47, Sheet 2

Screwjack Canister 6 Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 245

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 48, Sheet 1

Slat Track Canister 11 Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 246

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 49, Sheet 1

Overpressure Protector Electrical Bonding

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 247

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A300-600 A300-600

SERVICE BULLETIN

Figure 50, Sheet 1

Decomposition of the Center Tank (Additional work)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 248

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A300-600 A300-600

SERVICE BULLETIN

Figure 51, Sheet 1

Location of the Bonding Points on the Rib 1 (LH side) (Additional work)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 249

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A300-600 A300-600

SERVICE BULLETIN

Figure 51, Sheet 2

Location of the Bonding Points on the Rib 1 (LH side) (Additional work)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 250

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A300-600 A300-600

SERVICE BULLETIN

Figure 52, Sheet 1

Bonding Points to check on the Rib 1 (LH side) (Additional work)

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 251

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A300-600 A300-600

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 252

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SERVICE BULLETIN

REPORTING SHEET

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

ELECTRICAL BONDING

MODIFICATION No. : 12495H5555

Please complete the appropriate item (A or B):

A - SB WILL BE embodied .................................................................. YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiement:

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

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

B - SB HAS BEEN embodied on aircraft: ............................................................................................................

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

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

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

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

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

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

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

Signature:..................... Date: .....................................................

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next

normal revision or prior to SB embodiment, please indicate required service(s):

Either : Advance data................................................................................... YES/NO

Or : Intermediate/Temporary revision ..................................................... YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational documentation

if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible

revision, this will result in

- updating of maintenance documentation to show pre and post SB data.

- updating of maintenance and operational documentation to show post SB data

after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include

them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SEDCC1 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

Or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 1 of 1

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

REPORTING QUALITY

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

ELECTRICAL BONDING

MODIFICATION No. : 12495H5555

Use this form to tell us what is your perception of the quality of this Service Bulletin.The reported data that you

provide us will be used to analyse areas of difficulties and to take corrective action to futher improve the quality

of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

-Quality rating of this SB 4 3 2 1

-Quality rating of the Accomplishment Instructions 4 3 2 1

-Quality rating of the Illustrations 4 3 2 1

-Is this SB easy to understand ? Y / N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short

description of the issue.

Planning Material Instructions

X Effectivity X Kit Content X Preparation

X Reason X List of Materials X Mod/Inspection

X Manpower Operator Supplied X Test

X References X Re-identification X Close-up

X Publication X Tooling X Illustrations

Comments :

Operator : Date:

Name/Title :

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SEMB Service Bulletins Management

FAX: (+33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 03 - Dec 15/08 Page : 1 of 1

Printed in France © AIRBUS 2008 All rights reserved