PubTeX output 2010.09.27:1608 - ltt-onlinetraining.de · a300-600 service bulletin revision transmittal sheet airbus ... title : fuel - general - modify the equipment in the fuel

A300-600A300-600SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEX FRANCETel : (33) 5 61 93 33 33Telex : AIRBU 530526FFax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 28

TITLE : FUEL - GENERAL - MODIFY THE EQUIPMENT IN THE FUEL TANKS FOR ADDITIONALELECTRICAL BONDING

MODIFICATION No. : 12495H5555

This page transmits Revision No. 05 of Service Bulletin No. A300-28-6064

ADDITIONAL WORK

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

REASON

Revision 05 has been issued to inform operators that:

- The test reference has been clarified for connectors 1076VC and 2022VC.

- An option to install a second washer at certain locations has been added.

- CB’s have been clarified for Config. 07.

- Installation of the bonding leads on the refueling pipes on LH side between FR44 and FR47 isupdated for Kit A01 and Kit A02

- Installation of the bonding leads on the TTS pipes is updated for Kit A01 and Kit A02.

- Procedure for removal of rivets is included.

- Figure 4, Sheets 1 and 14 thru 16 have been revised to clarify bonding.

- Figure 8, Sheet 2 has been revised to clarify bonding.

- Figure 12, Sheets 3 and 6 thru 8 have been revised to clarify bonding.

- Figure 14, Sheet 2 and 3 have been revised to clarify bonding.


- Figure 16, Sheet 3 has been revised to clarify validity.


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

REVISION No. : 05 - Sep 27/10 Page : 1 of 8

Printed in France © AIRBUS 2008 All rights reserved




- Figure 23, Sheet 2 has been revised to remove a bonding lead.

- Figure 33, Sheet 2 and Figure 47, Sheet 2 have been revised to add missing washers.

- Figures 35, 37, 39, 40, 42, 43, 45, 46, 47, 48, 49, 50 and 51 have been revised to correct references.

CHANGES

SUMMARY :

- EFFECTIVITY

. Operators CSN and EGN deleted. Operators 66U, IRM and UZB added.

- MANPOWER

. Introduced by Rev 04 has been added.

PLANNING INFORMATION :

- EFFECTIVITY

. 1.A. Effectivity Updated. Kit/Configurations have been changed from None to ALL.

- DESCRIPTION

. 1.D.(8) Introduced by Rev 04 has been added.


- COMPLIANCE

- Accomplishment Timescale

. 1.E.(2)(a) Standard sentence has been updated.

- MANPOWER

. 1.G. Introduced by Rev 04 has been added.

- REFERENCES

. 1.J. Reference added.

MATERIAL INFORMATION :

- MATERIAL - PRICE AND AVAILABILITY

- Material

. 2.A.(1) AIRBUS address has been amended.


REVISION No. : 05 - Sep 27/10 Page : 2




- LIST OF COMPONENTS

. 2.C. Item 5 in kit A02, quantity changed. PN has changed from E0088-10-160 to E0088-16-200.

. 2.C. Quantity of item 5 changed to 19. PN has changed from E0088-10-160 to E0088-16-200.

. 2.C. PN has been changed from E0088-10-160 to E0088-16-200.

ACCOMPLISHMENT INSTRUCTIONS :

- Preparation

. 3.A.(1) CB title corrected for Config. 07.

. 3.A.(1)(p) Introduced by Rev 04 has been added.

. 3.A.(1)(p)5 CB title corrected.

- MODIFICATION

. 3.B. Washer quantities changed and Notes added. Installation of the bonding leads on therefueling pipes on LH side between FR44 and FR47 updated for Kit A01 and Kit A02. Installationof the bonding leads on the TTS pipes updated for Kit A01 and Kit A02.

. 3.B.(2) Workstep has been removed.

. 3.B.(2)(a)3 Mod. statement added.

. 3.B.(2)(a)4c Workstep has been added.

. 3.B.(3)(a)1c Part numbers updated.

. 3.B.(3)(a)3a Part numbers updated.

. 3.B.(3)(a)3f Part numbers updated.

. 3.B.(5)(a) Introduced at Rev 01 has been added.

. 3.B.(8)(b) Washer quantity changed and Note added.

. 3.B.(8)(b)3 Washer quantity changed and Note added.



. 3.B.(11)(a)6 Figure reference updated.



. 3.B.(13) Item numbers corrected.






. 3.B.(13)(a)4 Item number corrected.

. 3.B.(13)(a)6 New workstep added.

. 3.B.(13)(a)7 Workstep added.


. 3.B.(13)(a)9 Items and quantities changed.









. 3.B.(16)(a)9 Items and quantities changed.







. 3.B.(19)(a)9 Item numbers revised.


















. 3.B.(29) Introduced by Rev 04 has been added.

. 3.B.(30) Introduced by Rev 04 has been added.

- TESTS

. 3.C. AMM Reference added for test.

. 3.C.(3)(c)4 AMM Reference added.

. 3.C.(5) Introduced by Rev 04 has been added.

. 3.C.(6) Introduced by Rev 04 has been added.

- CLOSE-UP

. 3.D. CB’s corrected for Config. 07.



. 3.D.(6)(a) CB’s corrected.

. 3.D.(6)(a)4 CB’s corrected.

- Figure 1

. Figure 1, Sheet 1 updated.

- Figure 4

. Sheets 1 and 14 thru 16 revised.

- Figure 8

. Figure 8, Sheet 2

- Figure 12

. Sheet 3 and 6 thru 8 revised.






- Figure 14

. Sheets 2 and 3 revised.

- Figure 15

. Figure 15, Sheets 4, 5 and 7 modified.

- Figure 16

. Sheet 3 revised.

- Figure 18


- Figure 19


- Figure 23

. Sheet 2 revised to remove one bonding lead

- Figure 32

. Figure reference changed.

- Figure 33

. Sheet 2 Revised.

- Figure 34

. Sheet 2 revised.

- Figure 36

. Washer quantity changed.

- Figure 40


- Figure 42


- Figure 43


- Figure 44







- Figure 45


- Figure 46


- Figure 47


- Figure 48


- Figure 50

. Sheet 2 revised.

- Figure 51

. Sheet 2 revised.

- Figure 52

. Washer quantity changed.

FILING INSTRUCTIONS

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

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

HISTORY OF PREVIOUS REVISIONS

Revision 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 duringaccomplishment.

Revision No. 03 was issued to include improvements further to discrepancies found duringaccomplishment.

Revision 04 was issued to inform operators that:

- for access reasons, the location of the bonding lead on Figure 44 was changed.

- Kit B26, Qty 4 were necessary for Config. 01.

- Additional Work was added for Config. 07.

- Other additional work was also required by this revision for Config. 03 (using Kit A03).

REVISION SEQUENCE

ORIGINAL : Jul 28/05REVISION No. : 01 - Apr 03/07REVISION No. : 02 - Mar 10/08REVISION No. : 03 - Dec 15/08REVISION No. : 04 - Aug 24/09REVISION No. : 05 - Sep 27/10





SUMMARY


This summary is for information only and isnot approved for modification of the aircraft


ATA SYSTEM : 28



REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

As part of the Fuel Safety Assessment program, AIRBUS has carried out investigations of the electricalbonding in the aircraft fuel tanks.

As a result of these investigations this Service Bulletin has been issued for additional electrical bonding of theequipment in the fuel tanks. This modification consists of installing additional bonding leads and electricalbonding points in the wings fuel tanks and center tank.

The accomplishment of this Service Bulletin provides improved electrical bonding to ensure continuouselectrical bonding protection of all the equipment in the fuel tanks for the design life goal of the aircraft.

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





SUMMARY

As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structuralstrength, reliability, operational characteristics, affecting the airworthiness of the product. All other changesare Major changes.

EFFECTIVITY

This Service Bulletin is applicable to these operators:

66U AAL AAW ABD AMU CES DLH F2I FDX G8E IRA IRM JAL KAC KAL LAA MNB MON MSR MXUOHY QTR SUD TAR THA UPS UZB

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






SUMMARY






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

TOTAL MANHOURS 20


LH and RH Wing Fuel Tanks - All other Aircraft

TOTAL MANHOURS 226.0*


NOTE(*) Subject to aircraft configuration. Refer to para. 1.G. MANPOWER in the Service Bulletin for thebreakdown of the wings manhours. The manhours are given by rib bay and aircraft configuration.

ADDITIONAL WORK (Introduced by Rev 01)

TOTAL MANHOURS 2.0



TOTAL MANHOURS 62.5



TOTAL MANHOURS 4.0







SUMMARY

TOTAL MANHOURS 4.0



TOTAL MANHOURS 64.5


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:

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

NOTE : Kit 286064B24R01 has not been used.


Wings Fuel Tanks Equipment - Kit 286064B39R00:

Bonding leads, nuts and screws.

APPENDICES

None







ATA SYSTEM : 28



This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the propertyof AIRBUS; no intellectual property right or license is granted by AIRBUS in connection with any informationcontained in it. It is delivered on the express condition that said document and the information contained init shall be treated as confidential, shall not be used for any purpose other than that for which it is herebydelivered. 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 suchdocument 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 03580361 0365 0368 0380 0388 0398 0401 0405 0408 0411 0414 0417 0423 0459-04660469 0470 0474 0477 0479 0505-0518 0521 0525 0529 0530 0532 0536 0540 05430546 0553-0561 0563 0566 0569 0572 0575 0577 0579 0581 0582 0584 0601-06190621 0623 0625-0633 0635 0637 0639 0641 0643 0645 0657 0659 0662 0664 06660668 0670 0673 0675 0677 0679 0681 0683 0685 0688 0692 0694 0696 0699 07010703 0705 0707 0709 0711 0713 0715 0717 0719 0721-0750 0752-0764 0766-07750777-0794 0797 0799-0841

(b) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at thetime of issue in accordance with the information available to AIRBUS. Any future





changes resulting from transfer of an aircraft from one operator to another will not bereflected in this list unless the Service Bulletin is revised for another reason.

OPERATOR MSN

66U 0733 0734 0739 0750 0756 0762

AAL 0423 0459 0460 0461 0463 0466 0469 0470 0474 0506 0507 05080509 0510 0511 0512 0513 0514 0515 0516 0517 0606 0610 06120615 0619 0626 0639 0643 0645 0675

AAW 0354

ABD 0529 0557 0755

AMU 0677 0743

CES 0521 0525 0532 0707 0725 0732 0741 0746 0754 0763

DLH 0380 0401 0405 0408 0618 0623 0701 0773

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

FDX 0358 0361 0365 0388 0417 0477 0479 0530 0536 0543 0555 05590572 0575 0579 0581 0611 0613 0625 0630 0633 0657 0659 06640668 0688 0709 0713 0715 0726 0728 0735 0736 0738 0742 07450748 0752 0757 0759 0760 0761 0766 0768 0769 0771 0772 07740777 0778 0779 0780 0781 0789 0790 0791 0792 0793 0794 07990800 0801 0802 0803 0804

G8E 0462 0465

IRA 0632 0696 0723 0727

IRM 0411 0414 0546 0553 0608

JAL 0602 0617 0621 0637 0641 0670 0679 0683 0703 0711 0724 07290730 0737 0740 0753 0770 0783 0797 0836 0837 0838

KAC 0344 0673 0694 0699 0719 0721

KAL 0582 0609 0627 0631 0662 0685 0692 0731

LAA 0601 0616

MNB 0758

MON 0540 0556 0604 0605

MSR 0561 0607

MXU 0767 0788





OPERATOR MSN

OHY 0584 0603 0744 0747 0749 0764

QTR 0554 0560 0614

SUD 0666 0775

TAR 0505 0558 0563

THA 0368 0398 0464 0518 0566 0569 0577 0628 0629 0635 0681 07050782 0784 0785 0786 0787

UPS 0805 0806 0807 0808 0809 0810 0811 0812 0813 0814 0815 08160817 0818 0819 0820 0821 0822 0823 0824 0825 0826 0827 08280829 0830 0831 0832 0833 0834 0835 0839 0840 0841

UZB 0717 0722

(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 0469-0470 0474 0506-0518 0529 0536 0540 0555-0557 0559 05610566 0569 0572 0575 0577 0579 0581-0582 0584 0603-0610 0612 0615 06190625-0629 0631-0632 0635 0639 0643 0645 0657 0659 0662 0666 0673 0675 06770681 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 inthe 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 byRevision 00 or 01 or 02. This additional work was introduced atrevision 03.

NOTE(03) Config. 01 is valid for aircraft on which Mod. No. 04801H5078 (FUEL -INSTALL TRIM TANK SYSTEM) is embodied.


0477 0479 0505 0521 0525 0530 0532 0543 0546 0553-0554 0558 0560 05630601-0602 0611 0613-0614 0616-0618 0621 0623 0630 0633 0637 0641 0664 06680670 0679 0683 0688 0696 0699 0703 0707 0709 0711 0713 0715 0719 0721 0724






286064A01R05 1 01

286064A03R00 1 01



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 inthe center tank and is valid for aircraft on which Mod. No. 12315S22009(FUEL - FUEL PUMP SYSTEM - ADD BONDING LEAD ON RH ANDLH CENTER TANK BOOSTER PUMP CANISTERS) is not embodiedand for aircraft on which Mod. No. 12314H5524 (FUEL - FUEL PUMPSYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMPCANISTERS) or Mod. No. 13041H5657 (FUEL - FUEL PUMPSYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMPCANISTERS) are not embodied or Service Bulletin No. A300-28-6069or A300-28-6089 are not accomplished.


0252 0284 0294 0301 0307 0312 0317 0321 0336 0341 0344 0348 0351 0354 03580361 0365 0368 0380 0388 0398 0405 0408 0411 0414 0417


286064A01R05 1 02

286064A03R00 1 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 inthe center tank and is valid for aircraft on which Mod. No. 12315S22009(FUEL - FUEL PUMP SYSTEM - ADD BONDING LEAD ON RH ANDLH CENTER TANK BOOSTER PUMP CANISTERS) is not embodiedand for aircraft on which Mod. No. 12314H5524 (FUEL - FUEL PUMPSYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMPCANISTERS) or Mod. No. 13041H5657 (FUEL - FUEL PUMPSYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMPCANISTERS) are not embodied or Service Bulletin No. A300-28-6069or A300-28-6089 are not accomplished.


0727 0731 0733-0734 0739 0741 0743-0744 0747 0749-0750 0755-0756 07580762-0764 0767-0773 0775 0782 0784-0788 0794 0805-0841


286064A02R02 1 None

NOTE(01) Kit 286064A02R02 concerns the modification of the electrical bonding inthe center tank and is valid for aircraft on which Mod. No. 8692S20032(FUEL - SECTION - INTRODUCE MOULDED PARTS ON A300/600)is embodied.



0726 0728-0730 0732 0735-0738 0740 0742 0745-0746 0748 0752-0754 07570759-0761 0766 0774 0777-0781 0783 0789-0793 0797 0799-0804


286064A02R02 1 None

286064A03R00 1 03

NOTE(01) Kit 286064A02R02 concerns the modification of the electrical bonding inthe center tank and is valid for aircraft on which Mod. No. 8692S20032(FUEL - SECTION - INTRODUCE MOULDED PARTS ON A300/600)is embodied.


NOTE(03) Config. 03Kit 286064A03R00 concerns the modification of the electrical bonding inthe 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 embodiedand for aircraft on which Mod. No. 12314H5524 (FUEL - FUEL PUMPSYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMPCANISTERS) or Mod. No. 13041H5657 (FUEL - FUEL PUMPSYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMPCANISTERS) are not embodied or Service Bulletin No. A300-28-6069or A300-28-6089 are not accomplished.

NOTE(04) Additional work is required by this revision for Config. 03 aircraft (usingKit A03) modified by Revision 00 or 01 or 02. This additional workwas introduced at revision 04.


0252 0284 0294 0301 0307 0312 0317 0321 0336 0341 0344 0348 0351 0354 03580361 0365 0368 0380 0388 0398 0405 0408 0411 0414 0417 0423 0459-04660469-0470 0474 0477 0479 0505-0518 0521 0525 0529-0530 532 0536 0540 05430546 0553-0561 0563 0566 0569 0572 0575 0577 0579 0581-0582 0584 0601-06190621 0623 0625-0633 0635 0637 0639 0641 0643 0645 0657 0659 0662 0664 06660668 0670 0673 0675 0677 0679 0681 0683 0685 0688 0692 0694 0696 0699 07010703 0705 0707 0709 0711 0713 0715 0717 0719 0721-0750 0752-0764 0766-07750777-0794 0797 0799-0804


286064B01R05 2 ALL

286064B02R02 4 01

286064B02R02 12 02

286064B03R03 2 ALL

286064B04R03 2 ALL

286064B05R01 2 ALL

286064B06R03 2 ALL

286064B07R01 1 ALL

286064B08R03 2 ALL






286064B09R04 2 ALL

286064B10R01 2 ALL

286064B11R05 2 ALL

286064B12R01 2 ALL

286064B13R03 2 ALL

286064B14R02 2 ALL

286064B15R04 2 ALL

286064B16R03 2 ALL

286064B17R01 2 ALL

286064B18R04 2 ALL

286064B19R02 2 ALL

286064B21R01 2 04

286064B22R05 2 03

286064B23R01 2 06

286064B25R01 2 07

286064B26R01 4 01

286064B26R01 12 02

286064B27R01 1 02

286064B28R01 1 02

286064B39R00 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 - Post Mod. 04607 aircraft.Kit 286064B39R00

NOTE : Where configurations are listed as ALL, then these kits are necessaryfor all aircraft.






0805-0811


286064B20R06 2 08

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

NOTE : Mod. No. 12365H5540 (FUEL - GENERAL - REVISE ELECTRICALBONDING OF EQUIPMENT IN INNER WING FUEL TANKS) isembodied 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 ofthe 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 additionalelectrical bonding of the equipment in the fuel tanks.

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

(3) Advantages

The accomplishment of this Service Bulletin provides extra electrical bonding to ensurecontinuous electrical bonding protection of all the equipment in the fuel tanks for thedesign 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

(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.




(a) Install the bonding points.

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

NOTE : Kit 286064B24R01 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 thruto 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 on LH wing tank (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 on center tank (Introduced by Rev 03)





(a) Preparation

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

(c) Test

(d) Close-up

(8) ADDITIONAL WORK on center tank (For Config. 03 using Kit A03 only) (Introduced byRev 04)

(a) Preparation

(b) Install the bonding points.

(c) Install :

(d) Test

(e) Close-up

(9) ADDITIONAL WORK on wings tanks (For Config. 07 only)(Introduced by Rev 04)

(a) Preparation

(b) Do the bonding of the Fuel Jettison System - Blanking Plates

(c) Test

(d) Close-up

E. COMPLIANCE

(1) Classification

Mandatory

(2) Accomplishment Timescale

(a) Accomplishment of this Service Bulletin has been rendered mandatory by the issueof an Airworthiness Directive (AD) published by the European Aviation SafetyAgency (EASA). The AD must be used as the reference document for the mandatoryaccomplishment timescale.

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 AIRBUSorigin, which affects the content of this Service Bulletin, the operator is responsible for obtainingapproval by its airworthiness authority for any adaptation necessary before incorporation ofthe Service Bulletin.





G. MANPOWER

The manpower estimates given in this Service Bulletin are based on direct labor cost to do thework. These estimates assume that the work will be done by experienced personnel, and mayneed to be revised upwards to suit operators circumstances. The estimates do not include thetime to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, dryingtimes 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

Test 1.5

Close-up 30.0




Get access 30.0


Modification/install the bonding points 13.0

Test 1.5

Close-up 30.0




Get access 30.0


Install the bonding points 3.0

Test 1.5

Close-up 30.0







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


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


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

Modification 6.0

TOTAL MANHOURS 6.0



Modification 2.0

TOTAL MANHOURS 2.0



Modification 6.0

TOTAL MANHOURS 6.0







Modification 6.0

TOTAL MANHOURS 6.0



Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0


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

Modification 4.0

TOTAL MANHOURS 4.0



Get access 1.0

Modification 6.0

Close up 1.0

TOTAL MANHOURS 8.0



Modification 4.0

TOTAL MANHOURS 4.0



Get access 1.0

Modification 6.0





Close up 1.0

TOTAL MANHOURS 8.0



Modification 4.0

TOTAL MANHOURS 4.0



Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0



Modification 4.0

TOTAL MANHOURS 4.0



Get access 1.0

Modification 2.0

Close up 1.0

TOTAL MANHOURS 4.0



Get access 1.0

Modification 4.0

Close up 1.0





TOTAL MANHOURS 6.0



Modification 4.0

TOTAL MANHOURS 4.0


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

Get access 1.0

Modification 6.0

Close up 1.0

TOTAL MANHOURS 8.0



Get access 1.0

Modification 14.0

Close up 1.0

TOTAL MANHOURS 16.0



Modification 4.0

TOTAL MANHOURS 4.0



Modification 2.0

TOTAL MANHOURS 2.0







Get access 1.0

Modification 8.0

Close up 1.0

TOTAL MANHOURS 10.0



Modification 4.0

TOTAL MANHOURS 4.0



Get access 1.0

Modification 2.0

Close up 1.0

TOTAL MANHOURS 4.0



Get access 1.0

Modification 1.0

Close up 1.0

TOTAL MANHOURS 3.0



Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0






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

Modification 4.0

TOTAL MANHOURS 4.0



Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0



Modification 4.0

TOTAL MANHOURS 4.0



Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0


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

Modification 4.0

TOTAL MANHOURS 4.0







Get access 1.0

Modification 4.0

Close up 1.0

TOTAL MANHOURS 6.0



Modification 4.0

TOTAL MANHOURS 4.0



Get access 1.0

Modification 1.0

Close up 1.0

TOTAL MANHOURS 3.0



Get access 1.0

Modification 5.0

Close up 1.0

TOTAL MANHOURS 7.0



Modification 5.0

TOTAL MANHOURS 5.0



Get access 1.0





Modification 8.0

Close up 1.0

TOTAL MANHOURS 10.0



Modification 4.0

TOTAL MANHOURS 4.0


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 allowtwo hours for fuel leak tests.

ADDITIONAL WORK on LH wing tank (Introduced by Rev 01)


Get access 0.5

Modification 1.0

Close up 0.5

TOTAL MANHOURS 2.0


ADDITIONAL WORK on center tank (Introduced by Rev 03)

Get access 30.0


Test 1.5

Close-up 30.0

TOTAL MANHOURS 62.5


ADDITIONAL WORK on wings tanks (Introduced by Rev 04)






Get access 1.0

Modification 2.0

Close up 1.0

TOTAL MANHOURS 4.0


ADDITIONAL WORK on wings tanks (Introduced by Rev 04)


Get access 1.0

Modification 2.0

Close up 1.0

TOTAL MANHOURS 4.0


ADDITIONAL WORK on center tank (For aircraft using Kit A03 only)

Get access 30.0

Install the bonding points 3.0

Test 1.5

Close-up 30.0

TOTAL MANHOURS 64.5


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 24-31-1124-41-00 27-80-00 28-00-00 28-10-0028-11-00 28-11-22 28-11-29 28-25-0028-25-21 28-42-00 33-13-00 33-14-0057-20-43 57-23-11

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 51-43-0051-75-10 51-76-10 51-76-20

Consumable Materials List (CML)

Service Bulletin (SB) : A300-28-6028 A300-28-6069A300-28-6089 A300-57-6026A300-57-6070

K. PUBLICATIONS AFFECTED

Aircraft Maintenance Manual (AMM) : 28-11-21 28-12-15 28-21-13 28-21-2128-25-15 28-25-21 28-42-23 28-42-2428-42-35 28-42-36 28-42-44 28-42-4528-43-21 28-46-21 28-46-22 57-20-43

Illustrated Parts Catalogue (IPC) : 28-11-05 28-11-11 28-11-12 28-21-1328-21-21 28-25-03 28-25-05 28-25-1228-26-03 28-42-44 28-43-05 57-20-43

L. INTERCHANGEABILITY/MIXABILITY

None





This Page Intentionally Left Blank





2. MATERIAL INFORMATION

A. MATERIAL - PRICE AND AVAILABILITY

(1) Material

Operators with aircraft shown in the effectivity of this Service Bulletin should submit apurchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:

AIRBUS Material Logistics and SuppliersWeg beim Jaeger 150P.O. Box 630262D-22335 HAMBURGGERMANYFor ordering by internet: http://spares.airbus.comFor ordering by fax: +49 40 50 76 25 90

(2) Price and Availability

Kit 286064A01R05

Cost : 181,00 US dollars

Availability : 30 calendar days from receipt of order

The sales terms (Cost and Availability) are estimated in relation to economic conditionsat the issue date of this Service Bulletin.

Kit 286064A02R02



The sales terms (costs and availability) are estimated in relation to economic conditionsat the issue date of the Service Bulletin.

Kit 286064A03R00



The sales terms (costs and availability) are estimated in relation to economic conditionsat the issue date of the Service Bulletin.

Kit 286064B01R05








Kit 286064B02R02




Kit 286064B03R03




Kit 286064B04R03




Kit 286064B05R01




Kit 286064B06R03




Kit 286064B07R01








Kit 286064B08R03




Kit 286064B09R04




Kit 286064B10R01




Kit 286064B11R05




Kit 286064B12R01




Kit 286064B13R03








Kit 286064B14R02




Kit 286064B15R04




Kit 286064B16R03




Kit 286064B17R01




Kit 286064B18R04




Kit 286064B19R02








Kit 286064B20R06




Kit 286064B21R01




Kit 286064B22R05




Kit 286064B23R01




Kit 286064B25R01




Kit 286064B26R01








Kit 286064B27R01




Kit 286064B28R01




NOTE : The kits availability given above is the standard lead time from the date of yourpurchase order. If you require the Kits before this time, please include yourretrofit planning schedule with your order so that we can try to comply withyour requirements.


Kit 286064B39R00




NOTE : The kits availability given above is the standard lead time from the date of yourpurchase order. If you require the Kits before this time, please include yourretrofit planning schedule with your order so that we can try to comply withyour requirements.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this 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 Bolt3 NAS1149F0332P 2 Washer4 NAS1726-4E 2 Nut5 NAS1726-3E 14 Nut7 E0088-10-125 1 Lead8 NSA5519-2B 3 Clamp13 AN735D40 8 Clamp14 NAS1801-3-8 8 Screw15 E0088-10-80 7 Lead16 E0088-10-200 3 Lead17 NAS1303-2 2 Bolt

NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardwarecomponents in the related kit(s) which you cannot identify in the LIST OFCOMPONENTS of this Service Bulletin. The SM will give you the correct part numberto part number relationship.

Kit 286064A02R02


2 NAS1303-3 2 Bolt3 NAS1149F0332P 1 Washer4 NAS1726-4E 1 Nut5 NAS1726-3E 19 Nut7 E0088-10-125 1 Lead8 NSA5519-2B 3 Clamp9 NSA5050-4 1 Nut13 AN735D40 8 Clamp14 NAS1801-3-8 8 Screw15 E0088-10-80 7 Lead16 E0088-10-200 3 Lead17 NAS1303-2 1 Bolt


Kit 286064A03R00


2 NAS1303-3 2 Bolt3 NAS1149F0332P 2 Washer5 NAS1726-3E 2 Nut10 E0088-10-200 2 Lead






11 ASNA2050DCJ3215 4 Rivet12 A9242127720000 2 Angle

Kit 286064B01R05


4 NSA5472-4K7 4 Nut14 E0088-41-160 1 Lead15 AN742D6 1 Clamp16 NSA5474-3K7 11 Nut17 NSA5020-3-3 3 Bolt20 NSA5474-4K7 7 Nut25 H19200C4 1 Nut27 NSA5041VBV3-4 1 Bolt28 AN960C10L 1 Washer34 NSA5041VBV3-10 2 Bolt35 NSA5519-2B 4 Clamp37 NAS1303-2 4 Bolt38 E0088-10-100 2 Lead39 E0088-41-100 2 Lead45 NSA5022-4-21 4 Screw46 NAS1304-3 4 Bolt49 NSA5472-5K7 5 Nut52 A2824028520000 3 Washer53 AN960PD416 3 Washer74 AN960KD10L 2 Washer77 NSA5041VBV3-8 1 Bolt

Kit 286064B02R02


4 NSA5472-4K7 4 Nut9 A5715206420000 1 Plate13 NAS1252-416L 1 Washer

Kit 286064B03R03


2 NSA5020-3-6 1 Bolt4 NSA5472-4K7 2 Nut5 AN960C416L 1 Washer6 NSA5041VBV4-2 1 Bolt16 NSA5474-3K7 1 Nut70 NSA5020-3-2 1 Bolt





Kit 286064B04R03


4 NSA5472-4K7 2 Nut5 AN960C416L 1 Washer16 NSA5474-3K7 1 Nut17 NSA5020-3-3 1 Bolt25 H19200C4 1 Nut30 NSA5041VBV4-3 1 Bolt88 AN960KD10 1 Washer

Kit 286064B05R01


1 E0088-40-100 1 Lead3 NSA5041VBV4-11 1 Bolt4 NSA5472-4K7 2 Nut5 AN960C416L 1 Washer7 NSA5041VBV3-5 1 Bolt14 E0088-41-160 1 Lead15 AN742D6 1 Clamp16 NSA5474-3K7 3 Nut17 NSA5020-3-3 1 Bolt19 ABS0114-4-18 1 Bolt20 NSA5474-4K7 1 Nut31 NAS1303-10 1 Bolt

Kit 286064B06R03


1 E0088-40-100 1 Lead4 NSA5472-4K7 3 Nut5 AN960C416L 1 Washer16 NSA5474-3K7 1 Nut18 NSA5472-3K7 1 Nut28 AN960C10L 1 Washer32 NSA5041VBV4-9 1 Bolt33 NSA5041VBV3-3 1 Bolt40 ABS0114-4-16 1 Bolt70 NSA5020-3-2 1 Bolt

Kit 286064B07R01


16 NSA5474-3K7 2 Nut20 NSA5474-4K7 1 Nut39 E0088-41-100 1 Lead50 AN742D8 1 Clamp51 NAS1100-3-7 1 Screw






55 NAS1304-11 1 Bolt56 NAS1303-7 1 Bolt58 NAS1304-14 1 Bolt

Kit 286064B08R03


4 NSA5472-4K7 3 Nut5 AN960C416L 1 Washer16 NSA5474-3K7 2 Nut28 AN960C10L 1 Washer32 NSA5041VBV4-9 1 Bolt41 NSA5041VBV3-2 1 Bolt42 NAS1303-1 1 Bolt44 ABS0114-4-15 1 Bolt89 E0088-40-190 1 Lead

Kit 286064B09R04


16 NSA5474-3K7 4 Nut17 NSA5020-3-3 1 Bolt20 NSA5474-4K7 2 Nut25 H19200C4 1 Nut51 NAS1100-3-7 2 Screw59 E0088-41-304 2 Lead70 NSA5020-3-2 1 Bolt90 NSA5020-3-5 1 Bolt

Kit 286064B10R01


1 E0088-40-100 1 Lead4 NSA5472-4K7 2 Nut5 AN960C416L 1 Washer7 NSA5041VBV3-5 1 Bolt14 E0088-41-160 1 Lead15 AN742D6 1 Clamp16 NSA5474-3K7 8 Nut17 NSA5020-3-3 1 Bolt18 NSA5472-3K7 2 Nut20 NSA5474-4K7 3 Nut26 NSA5041VBV3-7 1 Bolt35 NSA5519-2B 4 Clamp37 NAS1303-2 4 Bolt38 E0088-10-100 2 Lead39 E0088-41-100 2 Lead






45 NSA5022-4-21 4 Screw54 NSA5041VBV4-7 1 Bolt57 ABS0114-4-14 1 Bolt69 NSA5041VBV3-6 2 Bolt

Kit 286064B11R05


1 E0088-40-100 1 Lead4 NSA5472-4K7 5 Nut5 AN960C416L 1 Washer14 E0088-41-160 1 Lead15 AN742D6 1 Clamp16 NSA5474-3K7 1 Nut17 NSA5020-3-3 1 Bolt18 NSA5472-3K7 2 Nut20 NSA5474-4K7 3 Nut28 AN960C10L 1 Washer29 NSA5041VBV4-8 1 Bolt33 NSA5041VBV3-3 1 Bolt46 NAS1304-3 2 Bolt49 NSA5472-5K7 2 Nut52 A2824028520000 2 Washer53 AN960PD416 1 Washer70 NSA5020-3-2 1 Bolt85 ABS0114-4-13 1 Bolt

Kit 286064B12R01


16 NSA5474-3K7 2 Nut70 NSA5020-3-2 1 Bolt71 NSA5020-3-4 1 Bolt

Kit 286064B13R03


1 E0088-40-100 1 Lead4 NSA5472-4K7 3 Nut5 AN960C416L 1 Washer16 NSA5474-3K7 1 Nut18 NSA5472-3K7 1 Nut28 AN960C10L 1 Washer29 NSA5041VBV4-8 1 Bolt33 NSA5041VBV3-3 1 Bolt42 NAS1303-1 1 Bolt61 ABS0114-4-12 1 Bolt





Kit 286064B14R02


1 E0088-40-100 1 Lead4 NSA5472-4K7 3 Nut5 AN960C416L 1 Washer12 NSA5041VBV4-5 1 Bolt16 NSA5474-3K7 1 Nut25 H19200C4 1 Nut54 NSA5041VBV4-7 1 Bolt63 ABS0114-4-10 1 Bolt69 NSA5041VBV3-6 1 Bolt

Kit 286064B15R04


1 E0088-40-100 1 Lead4 NSA5472-4K7 1 Nut5 AN960C416L 1 Washer12 NSA5041VBV4-5 1 Bolt16 NSA5474-3K7 2 Nut28 AN960C10L 1 Washer41 NSA5041VBV3-2 1 Bolt42 NAS1303-1 1 Bolt64 NSA5475-4K7 2 Nut86 ABS0114-4-9 1 Bolt

Kit 286064B16R03


1 E0088-40-100 1 Lead5 AN960C416L 1 Washer7 NSA5041VBV3-5 1 Bolt16 NSA5474-3K7 2 Nut27 NSA5041VBV3-4 1 Bolt28 AN960C10L 1 Washer62 NSA5041VBV4-6 1 Bolt64 NSA5475-4K7 2 Nut87 DHS1085-4 1 Washer91 ABS0114-4-6 1 Bolt

Kit 286064B17R01


1 E0088-40-100 1 Lead4 NSA5472-4K7 2 Nut5 AN960C416L 1 Washer12 NSA5041VBV4-5 1 Bolt16 NSA5474-3K7 8 Nut






18 NSA5472-3K7 1 Nut20 NSA5474-4K7 1 Nut28 AN960C10L 1 Washer67 ABS0114-4-5 1 Bolt72 ABS0114-3-6 1 Bolt

Kit 286064B18R04


1 E0088-40-100 1 Lead5 AN960C416L 1 Washer7 NSA5041VBV3-5 3 Bolt16 NSA5474-3K7 3 Nut20 NSA5474-4K7 1 Nut30 NAS1304-4 2 Bolt64 NSA5475-4K7 2 Nut65 DHS783-63-18 1 Washer78 NSA5041VBV4-4 1 Bolt79 ABS0114-4-4 1 Bolt87 DHS1085-4 1 Washer

Kit 286064B19R02


16 NSA5474-3K7 1 Nut17 NSA5020-3-3 1 Bolt71 NSA5020-3-4 1 Bolt

Kit 286064B20R06


14 E0088-41-160 1 Lead15 AN742D6 1 Clamp16 NSA5474-3K7 15 Nut17 NSA5020-3-3 3 Bolt20 NSA5474-4K7 5 Nut25 H19200C4 1 Nut27 NSA5041VBV3-4 1 Bolt28 AN960C10L 1 Washer34 NSA5041VBV3-10 2 Bolt35 NSA5519-2B 4 Clamp37 NAS1303-2 8 Bolt38 E0088-10-100 2 Lead39 E0088-41-100 2 Lead45 NSA5022-4-21 4 Screw46 NAS1304-3 2 Bolt52 A2824028520000 1 Washer






53 AN960PD416 2 Washer74 AN960KD10L 2 Washer77 NSA5041VBV3-8 1 Bolt

Kit 286064B21R01


16 NSA5474-3K7 2 Nut17 NSA5020-3-3 1 Bolt77 NSA5041VBV3-8 1 Bolt

Kit 286064B22R05


16 NSA5474-3K7 7 Nut23 NAS1303-8 1 Bolt37 NAS1303-2 4 Bolt82 NSA5480PN3-5 2 Bolt

Kit 286064B23R01


16 NSA5474-3K7 1 Nut17 NSA5020-3-3 1 Bolt38 E0088-10-100 1 Lead83 NSA5519-4B 1 Clamp

Kit 286064B25R01


16 NSA5474-3K7 2 Nut20 NSA5474-4K7 2 Nut62 NSA5041VBV4-6 1 Bolt66 NAS1153-12 1 Screw68 NSA5041VBV4-14 1 Bolt69 NSA5041VBV3-6 1 Bolt

Kit 286064B26R01


4 NSA5472-4K7 4 Nut10 A5715206420100 1 Plate13 NAS1252-416L 1 Washer





Kit 286064B27R01


4 NSA5472-4K7 5 Nut9 A5715206420000 1 Plate12 NSA5041VBV4-5 4 Bolt13 NAS1252-416L 1 Washer

Kit 286064B28R01


4 NSA5472-4K7 5 Nut10 A5715206420100 1 Plate12 NSA5041VBV4-5 4 Bolt13 NAS1252-416L 1 Washer

Kit 286064B39R00 (ADDITIONAL WORK Introduced by Rev 01)


16 NSA5474-3K7 2 Nut20 NSA5474-4K7 2 Nut51 NAS1100-3-7 2 Screw59 E0088-41-304 2 Lead


D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISPMAT No.

Sealant Mat. No. 09-001 As requiredSealant Mat. No. 09-002 As requiredLow Density Fuel Tank Sealant Mat. No. 09-002D As requiredCorrosion Inhibiting BrushConsistency

Mat. No. 09-013B As required

Corrosion Inhibiting FilletConsistency

Mat. No. 09-016B As required

Sealant Mat. No. 09-018 As requiredCorrosion Inhibiting SealantSprayable

Mat. No. 09-025 As required

Sealant Mat. No. 09-530 As requiredCleaning agent Mat. No. 11-026 As requiredAlodine Mat. No. 13-002 As requiredPrimer Mat. No. 16-001C As required





DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISPMAT No.

Varnish Mat. No. 16-021 As required

NOTE : To accomplish this Service Bulletin it is necessary to use the expendable partslisted in the AMM 28-25-21 P. Block 401.

(2) Components

Center Tank


EN6115V5-15 1 ScrewEN6115V5-16 1 ScrewNSA5041VP4-11 2 ScrewNSA5041-3-9 1 ScrewNSA5061-3 1 WasherNSA5061-4 5 WasherNSA5112-03 1 WasherNSA5112-04 3 WasherNSA5050-3 48 NutNSA5050-4 21 NutNSA5050-5 2 NutNSA5050-6 4 NutNSA5075-6 2 NutNSA5182-4 2 NutNSA5182-3 2 NutNAS1726-3E 1 NutNAS1726-4E 7 NutASNA2529-4 2 NutASNA2529-5 2 NutASNA2029-3 2 NutNSA5355-4CA 1 NutASNA2050DXJ4828 2 RivetASNA2050DCJ3215 54 RivetASNA2050DCJ4020 2 Rivet

Additional Work on center tank (Introduced by revision 03)


NSA5061-3 1 WasherNSA5112-04 1 Washer


17 NAS1303-2 1 Screw20 NAS1149D0316H 1 Washer





E. PARTS TO BE RE-IDENTIFIED BY THE OPERATOR

None

F. TOOLING - PRICE AND AVAILABILITY

None

G. SPECIAL TOOLS

None










3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL

WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONSINCLUDED IN THE REFERENCED PROCEDURES.

WARNING : MAKE SURE THAT ALL THE FLIGHT CONTROLS GROUND SAFETY LOCKSAND NOTICES ARE IN POSITION BEFORE YOU START THIS MODIFICATION.

WARNING : BEFORE YOU DO ANY WORK ON THE FUEL SYSTEM OBEY THE SAFETYPRECAUTIONS (REFER TO AMM 28-00-00 PAGE BLOCK 301).

WARNING : DO NOT DO ANY WORK IN THE FUEL TANKS UNTIL THE VAPORCONCENTRATION IS BELOW 20% OF THE LOWER EXPLOSION LIMIT (LEL).

WARNING : OBEY THE MANUFACTURER’S SAFETY INSTRUCTIONS WHEN YOU USESEALANTS, VARNISH AND CLEANING AGENTS IN THE FUEL TANKS.

CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICALWIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLYSERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS ORMODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS ANDTHE WORK AREA AS CLEAN AS POSSIBLE, TO DO THIS :

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; ASNECESSARY ON WIRING AND COMPONENTS

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHERCONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION ANDDAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

(1) Preparation

(a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page block 301).

(b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Pageblock 301).

WARNING : MAKE SURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF THETRAVEL RANGES OF THE SLATS/FLAPS.

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

(d) Put access platforms in position as necessary.





(e) Open, safety and tag these circuit breakers :

For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPIT DESIGN) isembodied.

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/P57132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58132VU FUEL/FUELING/XFR VALVE 2QU P55132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

or


22VU FUEL/TK LO LVL/L OUTR & R INR &CTR R

1QJ 208/B26

22VU FUEL/TK LO LVL/R OUTR & L INR &CTR L

2QJ 208/B27


For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPIT DESIGN) isnot embodied.



1QJ 208/B26

22VU FUEL/TK LO LVL OUTR & L INR & CTR L 2QJ 208/B27128VU FUEL/FUELING HI LVL 6QJ 805/L87128VU FUEL/FUELING OVERFLOW 5QJ 805/L86128VU FUEL/FUELING/TRANSFER VALVE 2QU P55128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85

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

(g) Defuel and ventilate the center fuel tanks and the wing fuel tanks (Refer to AMM28-10-00, Page block 301 and AMM 28-25-00, Page block 301).





(h) Remove additional wing manhole covers as necessary (Refer to AMM 28-11-22,Page block 401).

NOTE : The center tank manhole covers, 147AZ and 148AZ, are removedduring the ventilation process.

(i) For Slat Track Canisters and Screwjack Canisters it is necessary to remove theinboard heat shields (as applicable) to allow the removal/installation of the applicablecanister-flange nut (Refer to AMM 57-20-43, Page block 401).

(j) For some Track Cans/Jack Cans it may be difficult to get access to the modificationareas due to the small work area. If necessary these Track Cans/Jack Canscan be temporarily removed to allow access for bonding preparation. For theremoval/installation of Track Cans/Jack Cans, refer to AMM 57-20-43, Page block401.





(k) For Slat Track Canisters and Screwjack Canisters it is necessary to remove theinboard heat shields (as applicable) to allow the removal/installation of the applicablecanister-flange nut (Refer to AMM 57-20-43, Page block 401).

(l) ADDITIONAL WORK on center tank introduced by revision 01

1 De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page block301).

2 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 CLEAROF THE TRAVEL RANGES OF THE SLATS/FLAPS.

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

4 Put access platforms in position as necessary.

5 Open, safety and tag these circuit breakers :

For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPITDESIGN) is embodied.



1QJ 208/B26


2QJ 208/B27


6 or



1QJ 208/B26


2QJ 208/B27






7 For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPITDESIGN) is not embodied.



1QJ 208/B26


8 Defuel and ventilate the wing fuel tanks (Refer to AMM 28-25-00, Page block301).

9 Remove wing manhole covers as necessary (Refer to AMM 28-11-22, Pageblock 401).

(m) ADDITIONAL WORK LH wing tank (Introduced by Rev 01)

1 De-energise aircraft electrical circuits (Refer to AMM 24-41-00, Page block 301).


WARNING : MAKE SURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OFTHE TRAVEL RANGES OF THE SLATS/FLAPS.


4 Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-11, Pageblock 301).


6 Defuel and ventilate the center fuel tanks and the wing fuel tanks (Refer to AMM28-10-00, Page block 301 and AMM 28-25-00, Page block 301).

7 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.

8 For Slat Track Canisters and Screwjack Canisters it is necessary to remove theinboard heat shields (as applicable) to allow the removal/installation of theapplicable canister-flange nut (Refer to AMM 57-20-43, Page block 401).

9 For some Track Cans/Jack Cans it may be difficult to get access to themodification areas due to the small work area. If necessary these TrackCans/Jack Cans can be temporarily removed to allow access for bondingpreparation. For the removal/installation of Track Cans/Jack Cans (Refer to AMM57-20-43, Page block 401).





(n) ADDITIONAL WORK on center tank (Introduced by Rev 03)



3 Put the access platforms in position.

4 Make sure that the external connector(s) is (are) not connected to the aircraftreceptacle(s) EXT PWR.

5 Make sure that there is (are) warning notice(s) on the external powerreceptacle(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 onthe DISARM position.

7 In the flight compartment, on the overhead panel 51VU, release the BATpushbutton switch.

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

9 Display a warning notice on refuel/defuel panel 110VU to tell persons not tooperate the NORMAL BATTERY switch.

10 Display a warning notice in the cockpit to tell persons not to start the AuxiliaryPower Unit (APU).

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


Depending on aircraft configuration



1QJ 208/B26


2QJ 208/B27

132VU FUEL/FUELING HI LVL 6QJ 321/P57132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58132VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 321/P56132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

or







1QJ 208/B26


2QJ 208/B27

128VU FUEL/FUELING HI LVL 6QJ 805/L87128VU FUEL/FUELING OVERFLOW AND CAL 5QJ 805/L86128VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 805/L88128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85


14 Defuel and ventilate the center fuel tank and the wing fuel tanks (Refer to AMM28-10-00, Page block 301 and AMM 28-25-00, Page block 301).

15 Remove additional wing manhole covers as necessary (Refer to AMM 28-11-22,Page block 401).

16 Open the access doors 147AZ and 148AZ (Refer to AMM 28-11-29, Pageblock 401).

(o) ADDITIONAL WORK center tank (For Config. 03 using Kit A03 only)



3 Put the access platforms in position.





1QJ 208/B26


2QJ 208/B27






or



1QJ 208/B26


2QJ 208/B27


For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPITDESIGN) is not embodied.



1QJ 208/B26



6 Defuel and ventilate the center fuel tank (Refer to AMM 28-10-00, Page block301 and AMM 28-25-00, Page block 301).

7 Open the access doors 147AZ and 148AZ (Refer to AMM 28-11-29, Pageblock 401).

(p) ADDITIONAL WORK on the wing tanks (For Config. 07 only) (Introduced by Rev 04)



WARNING : MAKE SURE THAT PERSONNEL AND EQUIPMENT ARE CLEAROF THE TRAVEL RANGES OF THE SLATS/FLAPS.











1QJ 208/B26


2QJ 208/B27


or



1QJ 208/B26


2QJ 208/B27





1QJ 208/B26


2QJ 208/B27

128VU FUEL/FUELING HI LVL 6QJ 805/L87128VU FUEL/FUELING OVERFLOW 5QJ 805/L86128VU FUEL/FUELING/TRANSFER VALVE 2QU P55128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85

6 Defuel and ventilate the wing fuel tanks (Refer to AMM 28-25-00, Page block301).





7 Remove wing manhole covers as necessary (Refer to AMM 28-11-22, Pageblock 401).

(2) Standard Practices

(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 wingsfuel 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 bondingbolts.

- 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, (Referto 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 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.




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




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




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




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








(2) Kit 286064A01R05


1 Modify the refueling pipes on LH side between FR44 and FR47, valid for aircrafton which Mod. No. 04801H5078 (FUEL - INSTALL TRIM TANK SYSTEM) isembodied.Refer to Figure 14 Sheets 1 thru 3

a Remove :

1 screw Item (285) Retain1 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 thefigure 14 sheet 3

- Install on the sleeve item (268) :

1 Bonding Lead E0088-10-80 Item 151 Nut NAS1726-3E Item 51 Clamp AN735D40 Item 131 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 thedimensions given in the figure 14 sheet 3 detail E.



- Remove :

1 Screw Item (220) Retain1 Nut Item (4) Discard1 Screw Item (285) Retain1 Washer Item (3) Retain





- Install the bonding lead Item 15 with :

1 Screw Item (285)1 Washer Item (3)

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

- Install :

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, 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) Retain1 Washer Item (3) Retain


b On the sleeve item (268), do a stripping to the dimensions given in thefigure 15 sheet 3

c Install on the sleeve item (268) :


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



3 Modify the sleeves item (268), valid for aircraft on which Mod. No. 04801H5078(FUEL - INSTALL TRIM TANK SYSTEM) is embodied.Refer to Figure 15 Sheets 1, 4 thru 6

a Remove :

Refer to Figure 15 Sheet 4

2 Screw Item (2) Retain





2 Washer Item (3) Retain1 Screw Item (269) Retain1 Nut Item (4) Discard

- Disengage the bonding lead item (16).

b On the sleeves item (268), do strippings to the dimensions given in thefigure 15 sheet 6.

c On the tee pipe, do strippings to the dimensions given in the figure 15sheet 6.

d Install on the sleeves item (268) :


2 Bonding Lead E0088-10-160 Item 162 Clamp AN735D40 Item 132 Nut NAS1726-3E Item 52 Screw NAS1801-3-8 Item 14

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


f Install :

2 Screw Item (2)2 Washer Item (3)1 Screw Item (269)1 Nut NAS1726-4E Item 4

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

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 thefigure 15 sheet 8.

b Install on the sleeves item (268) :



c Attach the bonding lead Item 15 on the flange of tee pipe :






1 Bolt NAS1303-2 Item 171 Washer NAS1149D0316H Item 20

d Remove from the tee pipe :


2 Screw Item (569) Retain2 Nut Item (5) Discard

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


f Install on the tee pipe :Refer to Figure 15 Sheet 8



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 :


b On the tube item (333), do a stripping to the dimensions given in thefigure 16 sheet 2.

c Install :

1 Bonding Lead E0088-10-80 Item 151 Clamp NSA5519-2B Item 81 Bolt NAS1303-3 Item 21 Nut NAS1726-3E Item 51 Screw Item (285)1 Washer Item (413)


d Remove from RH side :

1 Screw Item (285) Retain1 Washer Item (413) Retain1 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 thefigure 16 sheet 3.

f Install :

1 Bonding Lead E0088-10-160 Item 161 Clamp NSA5519-2B Item 81 Bolt NAS1303-3 Item 21 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


6 Install new bonding lead on the cross feed pipe between FR46 and FR47Refer to Figure 17 Sheets 1 and 2

a Remove :


- 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 52 Bolt NAS1303-2 Item 172 Washer NAS1149F0332P Item 31 Bonding Lead E0088-10-125 Item 71 Clamp NSA5519-2B Item 8

- Install the bonding leads with :



(3) Kit 286064A02R02


1 Modify the refueling pipes on LH side between FR44 and FR47.Refer to Figure 18 Sheets 1 thru 3

a Remove :







- On the sleeve item (268), do a stripping to the dimensions given in thefigure 18 sheet 3



b Install the bonding leads item (281) and 15 with :1 Screw Item (285)1 Washer Item (3)


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 thedimensions given in the figure 18 sheet 3 detail E.



- Remove :

1 Screw Item (220) Retain1 Nut Item (4) Discard1 Screw Item (285) Retain1 Washer Item (3) Retain

- Install the bonding lead Item 15 with :


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

- Install :



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





Refer to Figure 19 Sheets 1 thru 3

a Remove :




b On the sleeve item (268), do a stripping to the dimensions given in thefigure 19 sheet 3

c Install on the sleeve item (268) :


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



3 Modify the sleeves item (268).Refer to Figure 19 Sheets 1, 4 thru 6

a Remove :


2 Screw Item (1) Retain2 Nut Item (5) Discard1 Screw Item (255) Retain1 Nut Item (9) Discard

- Disengage the bonding leads item (249).

b On the sleeves item (268), do strippings to the dimensions given in thefigure 19 sheet 6.

c On the tee pipe, do strippings to the dimensions given in the figure 19sheets 4 and 6.

d Install on the sleeves item (268) :


2 Bonding Lead E0088-10-160 Item 16





2 Clamp AN735D40 Item 132 Nut NAS1726-3E Item 52 Screw NAS1801-3-8 Item 14

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


f Install :

2 Screw Item (1)2 Nut NAS1726-3E Item 51 Screw Item (255)1 Nut NSA5050-4 Item 9


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 thefigure 19 sheet 8.

b Install on the sleeves item (268) :



c Remove from the tee pipe :



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


e Install on the tee pipe :Refer to Figure 19 Sheet 8


NOTE : Items (569) were retained at removal.

5 Modify the feed pipes.Refer to Figure 20 Sheets 1 thru 3





a Remove from LH side :


b On the tube item (333), do a stripping to the dimensions given in thefigure 20 sheet 2.

c Install :

1 Bonding Lead E0088-10-80 Item 151 Clamp NSA5519-2B Item 81 Bolt NAS1303-3 Item 22 Nut NAS1726-3E Item 51 Screw Item (1)


d Remove from RH side :


Disengage the bonding lead without complete removal.

e On the tube item (334), do a stripping to the dimensions given in thefigure 20 sheet 3.

f Install :

1 Bonding Lead E0088-10-160 Item 161 Clamp NSA5519-2B Item 81 Bolt NAS1303-3 Item 21 Nut NAS1726-3E Item 5

Put the bonding leads in position with :



6 Install new bonding lead on the cross feed pipe between FR46 and FR47Refer to Figure 21 Sheets 1 and 2

a Remove :


- Disengage the bonding lead without complete removal.

b On the tube, do a stripping to the dimensions given in the figure 21 sheet 2.





c Install :

1 Nut NAS1726-3E Item 51 Bolt NAS1303-2 Item 171 Washer NAS1149F0332P Item 31 Bonding Lead E0088-10-125 Item 71 Clamp NSA5519-2B Item 8

- Install the bonding leads with :



(4) Kit 286064A03R00


1 Remove :2 Screw Item (206) Retain2 Washer Item (260) Retain

2 On the blanking plates item (310), do a stripping to the dimension given in thefigure 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 figure22, sheets 2 and 3.

5 Drill the structure to match the holes of the angle item 12 at the dimensionsgiven 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 102 Nut NAS1726-3E Item 52 Bolt NAS1303-3 Item 22 Washer NAS1149F0332P Item 3


(5) Wings Fuel Tanks





(a) The Tables that follow list all the equipment in the wings fuel tanks that are to bemodified for electrical bonding. The work is listed by rib bay. The detailed workstepsfor each rib bay is given in para. (6) thru (25) for pre Mod. 12226 aircraft andpara. (26) for Post Mod. 12226 aircraft.

Paragraph (27) refers to the ADDITIONAL WORK (Introduced by Rev 01) that isnecessary 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 thesame unless otherwise stated.

TABLE 1 - PRE. MOD. 12226 AIRCRAFT

LH AND RH WING

APPLICABLE RIB BAY

EQUIPMENT TOBE ELECTRICALLYBONDED

REFERENCEDFIGURES

APPLICABLE KIT

Rib Bay 1-2 Water Drain Valves.

Water Scavenge Pipes(Config. 03 aircraft).

MLI.

Fuel Feed Pipe.

Low Fuel PressureSwitches.

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 aircraftKit B22R05.


Rib Bay 2-3 Diffuser.

Calibration Sensor(Config. 04 aircraft)

Figure 29, Sheet 1

Figure 30, Sheet 1



Rib Bay 5-6 Slat Track Canister 3. Figure 31, Sheet 1,Sheet 2

Kit B03R03 all aircraftand Kit B02R02 orB26R01 for Config. 02aircraft

Rib Bay 8-9 Slat Track Canister 4.

MLI.

Figure 32, Sheet 1

Figure 31, Sheet 2

Figure 25, Sheet 1

Kit B04R03 all aircraftand Kit B02R02 orB26R01 for Config. 02aircraft.





LH AND RH WING

APPLICABLE RIB BAY


REFERENCEDFIGURES

APPLICABLE KIT

Rib Bay 9-10 Screwjack Canister 3.

Water Drain Valve.

Figure 33, Sheet 1,Sheet 2

Figure 23, Sheet 1


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

Figure 31, Sheet 2


Rib Bay 11-12 (RH Wingonly)

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


Rib Bay 13-14 MLI.

Refuel/Defuel Valves.

Fuel Level Sensor.

Overwing Refuel Panel.

Figure 25, Sheet 1

Figure 37, Sheet 1 andSheet 2

Figure 30, Sheet 1

Figure 39, Sheet 1



Water Drain Valve.


Fuel Booster Pumps.

Provision for FuelJettison System -Blanking plate (Config.07 aircraft).

Figure 40, Sheet 1

Figure 33, Sheet 2

Figure 23, Sheet 1,Sheet 2


Figure 41, Sheet 1

Figure 38, Sheet 1

Kit B10R01 all aircraftand Kit B02R02 orB26R01 for Config. 02aircraft. Kit B25R01 forConfig. 07 aircraft.


Diffuser.

Water Drain Valve.

Figure 42, Sheet 1

Figure 31, Sheet 2

Figure 29, Sheet 3

Figure 23, Sheet 1


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





LH AND RH WING

APPLICABLE RIB BAY


REFERENCEDFIGURES

APPLICABLE KIT

Rib Bay 17-18 Provision for a FuelJettison System -Blanking Plates (Config.07 aircraft).

Figure 38, Sheet1 Kit B25R01 for Config.07 aircraft.


Figure 31, Sheet 2

Kit B13R03 all aircraftand Kit B02R02 orB26R01 for Config 01and Config. 02 aircraft.


MLI

Figure 44, Sheet 1

Figure 33, Sheet 2

Figure 25, Sheet 1



Figure 31, Sheet 2

Kit B15R04 all aircraftand Kit B02R02 orB26R01 for Config 01and Config. 02 aircraft.

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

Figure 31, Sheet 2

Kit B16R03 all aircraftand Kit B02R02 orB26R01 for Config. 01and Config. 02 aircraft.

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


MLI.

Overwing Refuel Panel.

Figure 47, Sheet 1

Figure 25, Sheet 1

Figure 39, Sheet 1



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 aircraftand Kit B02R02 orB26R01 for Config. 01and Config. 02 aircraft.

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


Rib Bay 13-14

Additional Work

Refuel/Defuel Valves LHWing


Kit B39R00





TABLE 2 - CONFIG 08 POST Mod. 12226 AIRCRAFT ONLY

LH and RH WING -APPLICABLE RIB BAY


REFERENCE FIGURES APPLICABLE KIT

Rib Bay 1-2 Water Drain Valves.

Water Scavenge Pipe.

MLI.

Fuel Feed Pipe SupportBracket.


Fuel Booster PumpsCanisters.

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 1-2Kit 286064B01R05 all aircraftKit 286064B22R05 Config. 03 aircraftKit 286064B23R01 Config. 06 aircraft

(a) Forward Rib Bay Water Drain ValveKit 286064B01R05Refer 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 boltthrough 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 ValveKit 286064B01R05Refer to Figure 23, Sheet 1, Detail A








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

1 Clamp AN742D6 Item 151 Lead E0088-41-160 Item 141 Bolt NSA5020-3-3 Item 171 Nut NSA5474-3K7 Item 16

3 At the base of the water drain valve prepare the bonding area. For the boltthrough the wing skin also prepare the countersink. Install:


- the other end of bonding lead, Item 14.


(c) Water Scavenge Pipe - Config. 03 aircraftKit 286064B22R05Refer 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 clamp, Item (22) retain.

If the support bracket is attached by rivets, remove one of the rivets and increasethe diameter of the hole to 4.826-4-877mm (0.1900-0.1920in.) to allow for theinstallation of a bolt.

3 On the support bracket and pipe clamp position (refer to Detail B) preparethe bonding area and install:





- 1 retained clamp, Item (22).

1 Bolt NAS1303-2 Item 371 Bolt NAS1303-8 Item 232 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 823 Bolt NAS1303-2 Item 375 Nut NSA5474-3K7 Item 16

(d) MLIKit 286064B01R05Refer to Figure 25, Sheet 1, Detail B

1 At the base of the MLI, remove:


- 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 SupportKit 286064B01R05Refer to Figure 26, Sheet 1

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



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



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

3 At the fuel pipe support bracket, upper section, prepare the bonding areaand install:





1 Bolt NSA5041VBV3-4 Item 271 Nut NSA5474-3K7 Item 16

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


and if applicable:

1 Washer AN960C10L Item 28

(f) Low Fuel Pressure SwitchesKit 286064B01R05Refer to Figure 27, Sheet 1

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



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

2 Clamp NSA5519-2B Item 352 Lead E0088-10-100 Item 382 Bolt NAS1303-2 Item 372 Nut NSA5474-3K7 Item 16

3 At the two pressure switches attachments to the rear spar prepare the bondingareas and attach the bonding leads, Item 38, with:


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

(g) Fuel Booster Pumps Canisters - All AircraftKit 286064B01R05Refer to Figure 28, Sheet 1

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


CAUTION : BOLTS THAT GO THROUGH THE FAIRING ARE NOT TO BE USEDAS BONDING BOLTS.

2 At the two canister flanges prepare the bonding areas and for the bolts throughthe wing skin prepare the countersinks only and install:

4 Bolt NSA5022-4-21 Item 45





3 At each of the canisters, at the fuel outlet flange (adjacent to the existing bondinglead, refer to Detail C) remove:

- one nut (20), discard.


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


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

- two retained bolts, Item (43).



(h) Fuel Booster Pump Config. 06 aircraftKit 286064B23R01Refer to Figure 28, Sheet 1

1 At the rear of the outboard canister, on the canister housing (refer to DetailB), remove:


- one washer, Item (48), retain.

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

1 Clamp NSA5519-4B Item 831 Lead E0088-10-100 Item 381 Bolt NSA5020-3-3 Item 171 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).





(i) DiffuserKit 286064B01R05Refer to Figure 29, Sheet 2, Detail B

1 At the diffuser, remove:


- one washer, Item (52), discard.


- two washers, Item (53), discard.

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


or


NOTE : The bolts that attach the support brackets to the structure are aninterference 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 462 Washer AN960PD416 Item 531 Washer A2824028520000 Item 521 Nut NSA5474-4K7 Item 20

4 At the diffuser support bracket attachments to the structure, prepare the bondingareas around the bolt holes in the brackets only and install:


or


(j) Fuel Level SensorKit 286064B01R05Refer 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







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



- one bolt (17), discard.

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


NOTE : The bolt that attaches the support bracket to the structure is aninterference 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 bondingarea that surrounds the bolt hole and install:


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

1 Bolt NSA5020-3-3 Item 171 Washer AN960KD10L Item 741 Nut NSA5474-3K7 Item 16

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


(7) Rib Bay 2-3Kit 286064B01R05Kit 286064B21R01

(a) DiffuserKit 286064B01R05Refer to Figure 29, Sheet 1, Detail A




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






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


or


NOTE : The bolts that attach the support bracket to the structure are aninterference fit through the wing skin and are therefore bonded,do not remove.


2 Bolt NAS1304-3 Item 462 Washer A2824028520000 Item 521 Washer AN960PD416 Item 532 Nut NSA5474-4K7 Item 20

4 At each diffuser support bracket, where it is attached to the structure, preparethe bonding area around the bolt hole in the bracket only and install:


or


(b) Calibration Sensor Config. 04 Aircraft.Kit 286064B21R01Refer to Figure 30, Sheet 1, Detail C




2 At the support bracket, remove:




1 Bolt NSA5020-3-3 Item 171 Nut NSA5474-3K7 Item 16

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






(8) Rib Bay 5-6Kit 286064B03R03 All AircraftKit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft

(a) Slat Track Canister 3Kit 286064B03R03 All AircraftRefer to Figure 31, Sheet 1

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






retain any packing that you may find.

NOTE : The bolts that attach the support bracket to the structure are aninterference fit through the wing skin and are therefore bonded,do not remove.

2 At the canister attachment bracket prepare the bonding areas. At the supportbracket, where it is attached to the structure, prepare the bonding area aroundthe bolt hole only. Together with any retained packing, install:

1 Bolt NSA5041VBV4-2 Item 61 Washer AN960C416L Item 52 Nut NSA5472-4K7 Item 41 Bolt NSA5020-3-6 Item 21 Nut NSA5474-3K7 Item 161 Bolt NSA5020-3-2 Item 70

NOTE : If there is no spacer installed with Item 2 then use the alternatebolt, Item 70.

(b) Canister Drain Config. 02 AircraftKit 286064B02R02 or Kit 286064B26R01Refer 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:

- 3 retained bolts, Item (11).


NOTE : If Service Bulletin A300-57-6026 has been embodied, increasethe bolt holes diameter in the new plate, Item 9 or 10, to between7.142-7.193mm (0.2812-0.2832in.) for the second oversizebolts, Item (11).

3 Prepare the bonding area. For the bolt through the wing skin prepare thecountersink only. Install:


1* Washer NAS1252-416L Item 13

NOTE : * A second washer can be installed to allow correct installation ofbolt (11), if necessary.


4 Apply Sealant (Mat. No. 09-001) over the three nuts and a fillet of sealantaround the new plate to seal.


(a) Slat Track Canister 4Kit 286064B04R03Refer to Figure 32, Sheet 1

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












2 At the canister attachment bracket prepare the bonding areas.

NOTE : The bolt attaching the support bracket to the structure is aninterference fit in the skin and is therefore bonded, prepare onlyaround the bolt hole in the bracket at this position.

Install (together with any retained packing) :

1 Bolt NSA5041VBV4-3 Item 301 Washer AN960C416L Item 52 Nut NSA5472-4K7 Item 41 Bolt NSA5020-3-3 Item 171 Nut NSA5474-3K7 Item 161 Washer AN960KD10 Item 88


1 At the canister drain remove:





2 At the canister drain install:

1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:




3 Prepare the bonding area.





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

Install:






(c) MLIKit 286064B04R03Refer to Figure 25, Sheet 1, Detail B





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

Install:




(a) Screwjack Canister 3Kit 286064B05R01Refer to Figure 33, Sheet 1

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



2 At the canister flange, remove:







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

1 Lead E0088-40-100 Item 11 Bolt ABS0114-4-18 Item 191 Washer AN960C416L Item 51 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if thebolt, Item 19, is installed from the front spar side and the nut isinstalled inside the fuel tank. This will give easier access at someflanges to torque tighten the nut.

4 At the rib adjacent to the canister flange prepare the bonding area and attachthe bonding lead, Item 1, with:



6 At the canister attachment bracket, remove:





7 At the canister attachment bracket prepare the bonding areas and install(together with any retained packing) :

1 Bolt NAS1303-10 Item 311 Bolt NSA5041VBV3-5 Item 72 Nut NSA5474-3K7 Item 16

(b) Canister Drain Config. 02 AircraftKit 286064B02R02 or Kit 286064B26R01Refer to Figure 33, Sheet 2, Detail C




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






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 Prepare the bonding area


Install:


1 Washer NAS1252-416L Item 131 Nut NSA5472-4K7 Item 4


(c) Water Drain ValveKit 286064B05R01Refer to Figure 23, Sheet 1, Detail C

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



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


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


Install:






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






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





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 B), remove:










Install:

1 Nut NSA5472-4K7 Item 41 Bolt NSA5041VBV3-3 Item 331 Washer AN960C10L Item 281 Nut NSA5472-3K7 Item 181 Bolt NSA5020-3-2 Item 701 Nut NSA5474-3K7 Item 16








1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10





with:




3 Prepare the bonding area


Install:






(12) Rib Bay 11-12 (RH Wing Only)Kit 286064B07R01 All Aircraft

(a) CadensiconRefer to Figure 35, Sheet 1

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


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

or:

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

2 At the cadensicon mounting plate, remove:



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





1 Clamp AN742D8 Item 501 Lead E0088-41-100 Item 391 Screw NAS1100-3-7 Item 511 Nut NSA5474-3K7 Item 16


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 :


with:


6 At the cadensicon mounting plate prepare the bonding area and install:

1 Bolt NAS1303-7 Item 561 Nut NSA5474-3K7 Item 16



















6 At the canister attachment bracket, drill and remove one rivet.

7 Drill out the rivet hole to a finished size of 4.9 mm (0.1929 in.).

8 Deburr the hole.









Install:

1 Nut NSA5472-4K7 Item 41 Bolt NSA5041VBV3-2 Item 411 Washer AN960C10L Item 282 Nut NSA5474-3K7 Item 161 Bolt NAS1303-1 Item 42












1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:






Install:






(14) Rib Bay 13-14Kit 286064B09R04 All Aircraft

(a) MLIKit 286064B09R04Refer to Figure 25, Sheet 1, Detail B








2 At the base of the MLI prepare the bonding area.


Install:



(b) Refuel/Defuel Valve - All AircraftKit 286064B09R04Refer to Figure 37, Sheet 1, Sheet 2

1 If necessary remove and retain the heat shield.

2 On each valve at the front spar, remove:


NOTE : Remove and discard any bonding lead tags that may be installedunder the nuts, Item (20).

3 On the valves prepare the bonding areas and install:

2 Lead E0088-41-304 Item 592 Nut NSA5474-4K7 Item 20

NOTE : In some instances the bonding lead may be too short to connect tothe fastener shown because of interference from the heat shield.In this case connect the bonding leads to the fasteners that arediagonally opposite.


5 At the two bonding lead tag positions on the front spar, attach the bondingleads, Item 59, with:

2 Screw NAS1100-3-7 Item 512 Nut NSA5474-3K7 Item 16

NOTE : It is Mandatory to put the heat shield in its installation position (ifremoved) before you attach the bonding leads, Item 59, to thebonding tags, (Refer to Sheet 2)


7 Complete the installation of the heat shield.

(c) High Level Fuel Sensor - All AircraftKit 286064B09R04





Refer to Figure 30, Sheet 1, Detail B







or





1 Nut NSA5474-3K7 Item 161 Bolt NSA5020-3-3 Item 17

or


NOTE : If bolt, Item 17, is too short the bolt, item 90, may be used asan alternative.

(d) Overwing Refuel PanelNo KitRefer 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 therefuel/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 theFigure) use abrasive paper grade 1 or Emery cloth, grade 320, to removeany 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 andthe 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. Makesure 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 14-15Kit 286064B10R01 All AircraftKit 286064B02R02 or Kit 286064B26R01 Config. 02 AircraftKit 286064B25R01 Config. 07 Aircraft






















7 At the canister attachment to the structure, remove:




8 At the canister attachment to the structure prepare the bonding area and install(together with any retained packing) :


9 At the canister bracket prepare the bonding area and install (together withany retained packing)









1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10





with:






Install:






(c) Water Drain Valve - All AircraftKit 286064B10R01Refer 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:



CAUTION : DO NOT REMOVE AND DISCARD ANY OTHER BONDING LEADSFROM RIB 14.

2 At the bonding leads attachment to rib 14 (adjacent to the compensator), remove:



- one bonding lead, Item (84), discard.

NOTE : If necessary, temporarily remove any other bonding leads to getaccess to the bonding lead, Item (84) at rib 14.





3 At the bonding leads attachment to rib 14, install (together with any otherbonding leads that you temporarily removed for access) :



4 At the bonding leads attachment to rib 14, apply protective coating over thefastener 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:



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


8 At the base of the water drain valve prepare the bonding area.


Install:


- the other end of the lead, Item 14.



(d) Low Fuel Pressure SwitchesKit 286064B10R01Refer to Figure 27, Sheet 2, Detail D




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

2 Clamp NSA5519-2B Item 35





2 Lead E0088-10-100 Item 382 Nut NSA5474-3K7 Item 162 Bolt NAS1303-2 Item 37

3 At the pressure switches attachment to the rear spar prepare the bonding areasand attach the bonding leads, Item 38, with:



(e) Fuel Booster PumpsKit 286064B10R01Refer to Figure 41, Sheet 1

1 At each canister flange, remove from the positions shown in the figure:


CAUTION : BOLTS THAT GO THROUGH THE FAIRING ARE NOT TO BE USEDAS BONDING POINTS.

2 At the canister flanges prepare the bonding areas and for the bolts through thewing skin prepare the countersink only.

Install:


3 At each of the fuel pump canisters, adjacent to the existing bonding lead,(refer to Detail C) remove:



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



6 At the two fuel pump canisters, adjacent to the existing bonding lead, (refer toDetail C) prepare the bonding areas and attach the bonding leads, Item 39, with:








(f) Fuel Jettison System - Blanking PlatesKit 286064B25R01 Config. 07 AircraftRefer 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:



2 At the blanking plate prepare the bonding area and install:


3 At the blanking plate at rib 15 (refer to Detail B), remove:












- one bolt, Item (85), discard








4 At the rib adjacent to the canister prepare the bonding area and attach thebonding lead, Item 1, with:





8 Deburr the hole.

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







NOTE : The bolt attaching the support bracket to the structure is aninterference fit in the skin and therefore bonded, prepare onlyaround the bolt hole in the bracket at this position.

Install:

1 Nut NSA5472-4K7 Item 41 Bolt NSA5041VBV3-3 Item 331 Washer AN960C10L Item 282 Nut NSA5472-3K7 Item 181 Bolt NSA5020-3-2 Item 70

(b) Canister Drain Config. 02 AircraftKit 286064B02R02 or Kit 286064B26R01





Refer to Figure 31, Sheet 2







1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:






Install:





4 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealantaround the new plate to seal.

(c) Diffuser - All AircraftKit 286064B11R05Refer to Figure 29, Sheet 3





1 At the diffuser attachment brackets remove:


- two washers, Item (52) (if installed), discard.


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

2 At the diffuser attachment to the structure, remove:


or



2 Bolt NAS1304-3 Item 462 Washer A2824028520000 Item 521 Washer AN960PD416 Item 532 Nut NSA5474-4K7 Item 20

4 At the diffuser attachment to the structure prepare the bonding areas and install:

NOTE : The bolts attaching the support brackets to the structure are aninterference fit in the skin and are therefore bonded, prepare onlyaround the bolt hole in the bracket at this position.


or


(d) Water Drain Valve - All AircraftKit 286064B11R05Refer to Figure 23, Sheet 1

1 At the base of the water drain valve, (refer to Detail A) remove:



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









Install:




5 Torque tighten the nut, Item 20, to between 0.68-0.79 mdaN (60-70 lbf.in.)

(17) Rib Bay 16-17Kit 286064B12R01 All Aircraft

(a) Fuel Level SensorRefer to Figure 30, Sheet 2, Detail D







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




(18) Rib Bay 17-18Kit 286064B25R01Refer to Figure 38, Sheet 1

(a) Fuel Jettison System Blanking Plates

1 At the blanking plates, remove:









2 At the blanking plates prepare the bonding areas and install:

1 Bolt NAS1153-12 Item 661 Nut NSA5474-3K7 Item 161 Bolt NSA5041VBV4-14 Item 681 Nut NSA5474-4K7 Item 20

(19) Rib Bay 18-19Kit 286064B13R03 All AircraftKit 286064B02R02 or Kit 286064B26R01 for Config. 01 and Config. 02 aircraft.




















8 Deburr the hole.

9 At the canister attachment brackets (refer to Detail C) remove:







10 At the canister attachment bracket prepare the bonding areas



1 Nut NSA5472-4K7 Item 41 Bolt NAS1303-1 Item 421 Nut NSA5474-3K7 Item 161 Bolt NSA5041VBV3-3 Item 331 Washer AN960C10L Item 281 Nut NSA5472-3K7 Item 18

(b) Canister Drain Config. 01 and Config. 02 aircraft.Kit 286064B02R02 or Kit 286064B26R01Refer to Figure 31, Sheet 2










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:






Install:


























6 At the bracket attachment to the structure, remove:



7 At the canister attachment bracket prepare the bonding area and install:


8 At the bracket attachment to the structure prepare the bonding area and install:












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:



NOTE : If Service Bulletin A300-57-6026 has been embodied, increase thebolt holes diameter in the new plate, Item 9 or 10, to between7.142-7.193mm (0.2812-0.2832in.) for the second oversize bolts,Item (11).



Install:






(c) MLI - All AircraftKit 286064B14R02Refer to Figure 25, Sheet 1, Detail B










Install:



(21) Rib Bay 21-22Kit 286064B15R04 All AircraftKit 286064B02R02 or Kit 286064B26R01 for Config. 01 and Config. 02 aircraft.










NOTE : The washer, Item 5, is only necessary under the nut, Item 64, ifthe bolt, Item 86, is installed from the front spar side and the nut isinstalled inside the fuel tank. This will give easier access at someflanges to torque tighten the nut.




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














1 Nut NSA5472-4K7 Item 41 Bolt NAS1303-1 Item 422 Nut NSA5474-3K7 Item 161 Bolt NSA5041VBV3-2 Item 411 Washer AN960C10L Item 28

(b) Canister Drain Config. 01 and Config. 02 Aircraft.Kit 286064B02R02 or Kit 286064B26R01Refer to Figure 31, Sheet 2






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:







NOTE : If Service Bulletin A300-57-6026 has been embodied, increase thebolt holes diameter in the new plate, Item 9 or 10, to between7.142-7.193mm (0.2812-0.2832in.) for the second oversize bolts,Item (11).



Install:






(22) Rib Bay 24-25Kit 286064B16R03 All AircraftKit 286064B02R02 or Kit 286064B26R01 for Config. 01 and Config. 02 Aircraft.










NOTE : The washer, Item 5, is only necessary under the nut, Item 64, ifthe 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 someflanges to torque tighten the nut.




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







7 At the canister attachment bracket prepare the bonding areas and install(together with any retained packing) :

1 Bolt NSA5041VBV3-5 Item 71 Washer DHS1085-4 Item 871 Bolt NSA5041VBV3-4 Item 271 Washer AN960C10L Item 282 Nut NSA5474-3K7 Item 16

(b) Canister Drain, Config. 01 and Config. 02 Aircraft.Kit 286064B02R02 or Kit 286064B26R01Refer to Figure 31, Sheet 2







1 Plate LH A5715206420000 Item 9





or:

1 Plate RH A5715206420100 Item 10

with:



NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the bolthole 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).


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

Install:






(23) Rib Bay 25-26Kit 286064B19R02 - All Aircraft

(a) Fuel Level SensorRefer to Figure 30, Sheet 1, Detail A















(a) Screwjack Canister 6Kit 286064B17R01Refer to Figure 47, Sheet 1.













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










1 Bolt ABS0114-3-6 Item 721 Washer AN960C10L Item 281 Nut NSA5472-3K7 Item 18

(b) Canister Drain Config. 02 AircraftKit 286064B27R01 (LH) or Kit 286064B28R01 (RH)Refer to Figure 47, Sheet 2




- four bolts, Item (12), discard.

- packing, Item (6), retain.

2 At the drain spacer, Item (7) attachment to the wing skin, remove:



3 At the drain spacer, Item (7) attachment to the wing skin prepare the bondingarea.


Install:




1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:

- retained packing, Item (6)


5 Prepare the bonding area and install:





1 Bolt NSA5041VBV4-5 Item 121* Washer NAS1252-416L Item 13

NOTE : * A second washer can be installed to allow correct installation ofbolt 12, if necessary.


6 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealantaround the new plate to seal, Also repair any sealant on the bottom flange ofthe spacer, Item (7).

(c) MLIKit 286064B17R01Refer 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.




3 At the base of the MLI prepare the bonding area and install:



4 Put the protective tube in position over the MLI and install:

- six retained bolts, Item (22).




Install:



(d) Overwing Refuel Panel





No KitRefer to Figure 39 and AMM 28-25-21, Page block 401

1 Put protective material or masking tape on the wing skin, around therefuel/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 theFigure) use abrasive paper grade 1 or Emery cloth, grade 320, to removeany 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 andthe 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. Makesure 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 27-28Kit 286064B18R04 All AircraftKit 286064B02R02 or Kit 286064B26R01 for Config. 01 and Config. 02 Aircraft.














NOTE : The washer, Item 5, is only necessary under the nut, Item 64, ifthe bolt, Item 79, is installed from the front spar side and the nut isinstalled inside the fuel tank. This will give easier access at someflanges to torque tighten the nut.








7 At the bracket attachment to the structure, remove:





8 At the bracket attachment to the structure prepare the bonding area and install(together with any retained packing) :

1 Bolt NSA5041VBV3-5 Item 71 Washer DHS783-63-18 Item 651 Nut NSA5474-3K7 Item 16


1 Bolt NSA5041VBV3-5 Item 71 Washer DHS1085-4 Item 871 Nut NSA5474-3K7 Item 16

(b) Canister Drain, Config. 01 and Config. 02 Aircraft.Kit 286064B02R02 or Kit 286064B26R01Refer to Figure 31, Sheet 2











1 Plate LH A5715206420000 Item 9

or:

1 Plate RH A5715206420100 Item 10

with:






Install:






(c) Water DrainKit 286064B18R04Refer to Figure 23, Sheet 1, Detail B

1 At the water drain, remove:







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



(d) Fuel Overflow SensorKit 286064B18R04Refer to Figure 30, Sheet 4

NOTE : Access to Rib Bay 26-27 is also necessary.






(e) Overpressure ProtectorKit 286064B18R04Refer to Figure 49, Sheet 1

1 At the flange of the overpressure protector, remove:


2 Prepare the bonding areas and install:


(26) Wings Fuel Tank Equipment - Rib Bay 1-2 Config. 08 AircraftKit 286064B20R06

(a) Forward Rib Bay Water Drain ValveRefer to Figure 23, Sheet 1, Detail D










Install:



(b) Aft Rib Bay Water Drain Valve.Refer to Figure 23, Sheet 1, Detail A




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




Install:

- one retained bolt, Item (19)

- the other end of the lead, Item 14.


(c) Water Scavenge Pipe.Refer to Figure 24, Sheet 2

1 At the support bracket and pipe clamp positions (Refer to Detail A, Detail Band 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 Band C) , prepare the bonding areas and install:

- four retained clamps, Item (22)





4 Bolt NAS1303-2 Item 374 Nut NSA5474-3K7 Item 16

(d) MLIRefer to Figure 25, Sheet 1, Detail B






Install:



(e) Fuel Feed Pipe SupportRefer to Figure 26, Sheet 1

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



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



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

3 At the fuel pipe support bracket, upper section, prepare the bonding areaand install:


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


and, if applicable :





1 Washer AN960C10L Item 28

(f) Low Fuel Pressure SwitchesRefer to Figure 27, Sheet 1




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


3 At the two pressure switch attachments to the rear spar prepare the bondingareas and attach the bonding leads, Item 38, with:



(g) Fuel Booster Pump CanistersRefer to Figure 28, Sheet 1

1 At each canister flange, remove from the positions shown in the figure:


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


3 At each of the fuel pump canisters, adjacent to the existing bonding lead,(refer to Detail C) remove:



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






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 toDetail C) prepare the bonding areas and attach the bonding leads, Item 39, with:

- one retained bolts, Item (43).


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

(h) DiffuserRefer to Figure 29, Sheet 4, Detail B







2 Bolt NAS1304-3 Item 462 Washer AN960PD416 Item 531 Washer A2824028520000 Item 521 Nut NSA5474-4K7 Item 20

(i) Low Level Fuel SensorRefer to Figure 30, Sheet 3, Detail E

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


- one nut, Item (16), discard



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










4 At the support bracket of the FQI Probe No.2 prepare the bonding areas andinstall:


(27) ADDITIONAL WORK on the LH wing tank (Introduced by Rev 01)This additional work is necessary if this Service Bulletin, at the original issue, has beenembodied on aircraft which were not Config. 05 aircraft.

(a) Refuel/Defuel Valve LH Wing - Rib Bay 13-14Kit 286064B39R00Refer 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:


NOTE : Remove and discard any bonding lead tags that may be installedunder the nuts, Item (20).

4 On the valves prepare the bonding areas and install:

2 Lead E0088-41-304 Item 592 Nut NSA5474-4K7 Item 20


6 At the two bonding lead tag positions on the front spar, attach the bondingleads, Item 59, with:

2 Screw NAS1100-3-7 Item 512 Nut NSA5474-3K7 Item 16

NOTE : It is Mandatory to put the heat shield in its installation position (ifremoved) before you attach the bonding leads, Item 59, to thebonding tags, (Refer to Sheet 2).






8 Complete the installation of the heat shield.

(28) ADDITIONAL WORK on the center tank (Introduced by Rev 03)

(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, (Referto 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 51, Sheets 1 and 2, (Detailed location)


(29) ADDITIONAL WORK on the center tank (For Config 03 aircraft using Kit A03 only)(Introduced by Rev 04)


1 Remove :2 Screw Item (206) Retain2 Washer Item (260) Retain

2 On the blanking plates item (310), do a stripping to the dimension given in thefigure 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 figure22, sheets 2 and 3.

5 Drill the structure to match the holes of the angle item 12 at the dimensionsgiven in the figure 22, sheet 3.

6 Install :





2 Angle A9242127720000 Item 12

with

4 Rivet ASNA2050DCJ3215 Item 11

(b) Install :2 Screw Item (206)2 Washer Item (260)2 Bonding Lead E0088-10-200 Item 102 Nut NAS1726-3E Item 52 Bolt NAS1303-3 Item 22 Washer NAS1149F0332P Item 3


(30) ADDITIONAL WORK on the wings tanks (For Config. 07 aircraft only) (Introduced byRev 04)

(a) Fuel Jettison System - Blanking PlatesKit 286064B25R01 Config. 07 AircraftRefer 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:





3 At the blanking plate at rib 15 (refer to Detail B), remove:





(b) Config. 07Rib Bay 17-18Kit 286064B25R01Refer to Figure 38, Sheet 1

1 Get access to Rib Bay 17-18 refer to para 3.A (1) Preparation.





2 Fuel Jettison System Blanking Plates

a At the blanking plates, remove:





b At the blanking plates prepare the bonding areas and install:

1 Bolt NAS1153-12 Item 661 Nut NSA5474-3K7 Item 161 Bolt NSA5041VBV4-14 Item 681 Nut NSA5474-4K7 Item 20

C. TEST


(a) Do a check of the electrical bonding (Refer to AMM 20-28-11, Page block 001).

NOTE : For maximum permissible resistance values : Refer to the table AMM20-28-11, Page block 001

(b) Preliminary Tests:

1 Initial conditions

a On each connectors that you disconnected, do a visual check as defined byESPM 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 (Referto 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 AMM28-42-00, Page block 501).

5 Do the test after the Disconnection/Reconnection of plugs 1076VC and 2022VC(If necessary).

(c) After the worksteps in para. D. CLOSE UP, (1) (a) thru (d) have been completed, doa 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



(b) Preliminary Tests:







4 Do the Operational Test of the Quantity Indicating System (Refer to AMM28-42-00, Page block 501).

5 Do the test after the Disconnection/Reconnection of plugs 1076VC and 2022VC(If necessary).

(c) After the worksteps in para. D. CLOSE UP, (1) (a) thru (d) have been completed, doa leak test of the center fuel tank (Refer to AMM 28-11-00, Page block 501).

NOTE : Fuel leaks are not permitted.

(3) ADDITIONAL WORK on the LH wing (Introduced by Rev 01)



(b) After the worksteps in para. D. CLOSE UP, (2) (a) thru (f) have been completed, do aleak test of the wings fuel tanks (Refer to AMM 28-11-00, Page block 501).

(c) Preliminary Tests:











4 Do the Operational (BITE) test after the reconnection of plugs 1076VC and2022VC (Refer to AMM 28-42-00, Page block 501).




(b) 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).

2 Preliminary Tests:

a Initial conditions

- On each connectors that you disconnected, do a visual check as definedby 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 Do the Functional Test of the Instrument and Panel Integral Lighting (Referto AMM 33-13-00, Page block 501).

c Do the Operational Test of the Annunciator Light Test (Refer to AMM33-14-00, Page block 501).

(5) ADDITIONAL WORK on the center tank (For Config. 03 aircraft using Kit A03 only)(Introduced by Rev 04)







(b) After the worksteps in para. D. CLOSE UP, (6) (a) have been completed, do a leaktest of the center fuel tanks (Refer to AMM 28-11-00, Page block 501).








(6) ADDITIONAL WORK on the wing tanks (For Config. 07 aircraft only) (Introduced by Rev 04)



(b) After the worksteps in para. D. CLOSE UP, (6) (a) have been completed, do a leaktest of the wings fuel tanks (Refer to AMM 28-11-00, Page block 501).








D. CLOSE UP

(1) Center Fuel Tank





(a) Make sure that the work areas are clean and clear of tools and other items ofequipment.

(b) Close the access doors 147AZ and 148AZ (Refer to AMM 28-11-29, Page block 401).

(c) Install the manhole covers (Refer to AMM 28-11-22, 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) Remove the safety clips and tags and close these circuit breakers :

CAUTION : IF OTHER TANKS HAVE BEEN OPENED ENSURE ALL TANKS ARE CLOSEDBEFORE YOU REMOVE THE SAFETY CLIPS, TAGS AND CLOSE THE CIRCUITBREAKERS.For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPITDESIGN) is embodied.



1QJ 208/B26


2QJ 208/B27


or



1QJ 208/B26


2QJ 208/B27


For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPIT DESIGN) isnot embodied.



1QJ 208/B26







(g) Remove the access platforms.

(h) Restore the systems and the aircraft to normal operating condition.



(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 AMM28-11-22, 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 center fuel tank and wing fuel tanks (Refer to AMM 28-25-00, Pageblock 301).

(g) Remove the safety clips and tags and close these circuit breakers :

WARNING : IF OTHER TANKS HAVE BEEN OPENED ENSURE ALL TANKS ARECLOSED BEFORE YOU REMOVE THE SAFETY CLIPS, TAGS ANDCLOSE THE CIRCUIT BREAKERS.



1QJ 208/B26


2QJ 208/B27


or







1QJ 208/B26


2QJ 208/B27


(h) Remove the access platforms.

(i) Put the aircraft and the systems in a normal operating condition.

(3) ADDITIONAL WORK on the LH wing tank (Introduced by Rev 01)




(d) Refuel the wings fuel tanks (Refer to AMM 28-25-00, Page block 1).

(e) Remove the safety clips and tags and close these circuit breakers :

WARNING : IF OTHER TANKS HAVE BEEN OPENED ENSURE ALL TANKS ARECLOSED BEFORE YOU REMOVE THE SAFETY CLIPS, TAGS ANDCLOSE THE CIRCUIT BREAKERS.



1QJ 208/B26


2QJ 208/B27


or








1QJ 208/B26


2QJ 208/B27


(f) Remove the access platforms.

(g) Put the aircraft and the systems in a normal operating condition.


(a) Close-up

1 Make sure that the work areas are clean and clear of tools and other itemsof equipment.

2 Remove all the warning notices.

3 Close the Main Landing Gear (MLG) doors (Refer to AMM 32-12-11, Pageblock 301).

4 Remove the safety clips and tags and close these circuit breakers:

WARNING : IF OTHER TANKS HAVE BEEN OPENED ENSURE ALL TANKS ARE CLOSEDBEFORE YOU REMOVE THE SAFETY CLIPS, TAGS AND CLOSE THECIRCUIT BREAKERS.Depending on aircraft configuration



1QJ 208/B26


2QJ 208/B27


or








1QJ 208/B26


2QJ 208/B27


5 Remove the access platforms.

6 Restore the systems and the aircraft to normal operating condition.

(5) ADDITIONAL WORK on the center tank (For aircraft using Kit A03 only) (Introduced byRev 04)




(d) Remove the safety clips and tags and close these circuit breakers:

CAUTION : IF OTHER TANKS HAVE BEEN OPENED ENSURE ALL TANKS ARE CLOSEDBEFORE YOU REMOVE THE SAFETY CLIPS, TAGS AND CLOSE THE CIRCUITBREAKERS.Depending on aircraft configuration



1QJ 208/B26


2QJ 208/B27


or



1QJ 208/B26







2QJ 208/B27


(e) Refuel the wings fuel tanks (Refer to AMM 28-25-00, Page block 1).

(f) Remove the access platforms.

(g) Put the aircraft and the systems in a normal operating condition.

(6) ADDITIONAL WORK on the wing tanks (For Config. 07 aircraft only) (Introduced by Rev 04)

(a) Close-up

1 Make sure that the work areas are clean and clear of tools and other itemsof equipment.

2 Install wing manhole covers as necessary (Refer to AMM 28-11-22, Pageblock 401).

3 Remove all the warning notices.

4 Remove the safety clips and tags and close these circuit breakers:




1QJ 208/B26


2QJ 208/B27


or








1QJ 208/B26


2QJ 208/B27





1QJ 208/B26


2QJ 208/B27

128VU FUEL/FUELING HI LVL 6QJ 805/L87128VU FUEL/FUELING OVERFLOW 5QJ 805/L86128VU FUEL/FUELING/TRANSFER VALVE 2QU P55128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85

5 Remove the access platforms.

6 Retract the slats (Refer to AMM 27-80-00, Page block 301).

7 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.





Figure 1, Sheet 1Decomposition of the Center TankDATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064




Figure 2, Sheet 1Location of the Bonding Points at FR44






























Figure 3, Sheet 1Bonding Points to Check at FR44


























































































Figure 5, Sheet 1Bonding Points to Check at FR47





Figure 6, Sheet 1Location of the Bonding Points on the Rib 1 (LH side)















Figure 7, Sheet 1Bonding Points to check on the Rib 1 (LH side)





Figure 8, Sheet 1Location of the Bonding Points on the Intrados Panel


















































Figure 9, Sheet 1Bonding Points to check on the Intrados Panel





Figure 10, Sheet 1Location of the Bonding Points on the Rib 1 (RH side)






























Figure 11, Sheet 1Bonding Points to check on the Rib 1 (RH side)





Figure 12, Sheet 1Location of the Bonding Points on the Extrados Panel








































Figure 13, Sheet 1Bonding Points to check on the Extrados Panel





Figure 14, Sheet 1Modification of the Refueling Pipes on LH side between FR44 and FR47 (Kit 286064A01R05)















Figure 15, Sheet 1Modification of the TTS pipes (Kit 286064A01R05)








































Figure 16, Sheet 1Modification of the Feed Pipes (Kit 286064A01R05)















Figure 17, Sheet 1Modification of the Cross Feed Pipe (Kit 286064A01R05)


























































































Figure 22, Sheet 1Electrical Bonding of the Canister Pumps (Kit 286064A03R00)















Figure 23, Sheet 1Water Drains and Water Drain Valves Electrical Bonding





Figure 23, Sheet 2Water Drains and Water Drain Valves Electrical Bonding





Figure 24, Sheet 1Water Scavenge Pipes Electrical Bonding





Figure 24, Sheet 2Water Scavenge Pipes Electrical Bonding





Figure 25, Sheet 1Magnetic Level Indicators Electrical Bonding





Figure 26, Sheet 1Fuel Feed Pipe- Support Bracket Electrical Bonding





Figure 27, Sheet 1Fuel Booster Pumps - Low Pressure Warning Switches Electrical Bonding





Figure 27, Sheet 2Fuel Booster Pumps - Low Pressure Warning Switches Electrical Bonding





Figure 28, Sheet 1Fuel Booster Pumps Canisters - Inner Tanks Electrical Bonding





Figure 29, Sheet 1Fuel Diffusers - Inner and Outer Tanks Electrical Bonding




















Figure 30, Sheet 1Wings - Fuel Level Sensors Electrical Bonding




















Figure 31, Sheet 1Slat Track Canister 3 and Typical Canister Drain Attachment Electrical Bonding





Figure 31, Sheet 2Slat Track Canister 3 and Typical Canister Drain Attachment Electrical Bonding





Figure 32, Sheet 1Slat Track Canister 4 Electrical Bonding





Figure 33, Sheet 1Screwjack Canister 3 and Typical Canister Drain Attachment Electrical Bonding





Figure 33, Sheet 2Screwjack Canister 3 and Typical Canister Drain Attachment Electrical Bonding










Figure 35, Sheet 1Cadensicon (RH Wing only) Electrical Bonding










Figure 37, Sheet 1Refuel/Defuel Valves Electrical Bonding





Figure 37, Sheet 2Refuel/Defuel Valves Electrical Bonding





Figure 38, Sheet 1Provision for a Fuel Jettison System - Blanking Plates Electrical Bonding





Figure 39, Sheet 1Overwing Refuel/Defuel Panels Electrical Bonding





Figure 40, Sheet 1Screwjack Canister 4 Electrical Bonding





Figure 41, Sheet 1Fuel Booster Pumps Canisters - Outer Tanks Electrical Bonding













































Figure 49, Sheet 1Overpressure Protector Electrical Bonding





Figure 50, Sheet 1Decomposition of the Center Tank (Additional work, Introduced by Rev 03)





Figure 51, Sheet 1Location of the Bonding Points on the Rib 1 (LH side) (Additional work, Introduced by Rev 03)





Figure 51, Sheet 2Location of the Bonding Points on the Rib 1 (LH side) (Additional work, Introduced by Rev 03)





Figure 52, Sheet 1Bonding Points to check on the Rib 1 (LH side) (Additional work, Introduced by Rev 03)









A300-600A300-600SERVICE BULLETINREPORTING SHEET



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 nextnormal revision or prior to SB embodiment, please indicate required service(s):Either : Advance data................................................................................... YES/NOOr : Intermediate/Temporary revision ..................................................... YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational documentationif this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasiblerevision, 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 dataafter embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically includethem in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEX FRANCE

Attn: SEDCC1 Technical Data and Documentation ServicesFAX: (+33) 5 61 93 28 06e-mail: [email protected] via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.





REPORTING QUALITY



Use this form to tell us what is your perception of the quality of this Service Bulletin.The reported data that youprovide us will be used to analyse areas of difficulties and to take corrective action to futher improve the qualityof 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 shortdescription of the issue.

Planning Material InstructionsX Effectivity X Kit Content X PreparationX Reason X List of Materials X Mod/InspectionX Manpower Operator Supplied X TestX References X Re-identification X Close-upX Publication X Tooling X Illustrations

Comments :

Operator : Date:

Name/Title :

Please return this form to:

AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEX FRANCE

Attn: SEMB Service Bulletins ManagementFAX: (+33) 5 61 93 42 51Or via your Resident Customer Support Office.




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PubTeX output 2010.09.27:1608 - ltt-onlinetraining.de · a300-600 service bulletin revision transmittal sheet airbus ... title : fuel - general - modify the equipment in the fuel