# A300-600 **A300-600** SERVICE BULLETIN REVISION TRANSMITTAL SHEET

**AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  **Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F**  **Fax : (33) 5 61 93 42 51** M A N DA TO RY M A N DA TO RY M A N DA TO RY M A N DA TO RY **ATA SYSTEM : 28 TITLE : FUEL - GENERAL - MODIFY THE EQUIPMENT IN THE FUEL TANKS FOR ADDITIONAL**  **ELECTRICAL BONDING MODIFICATION No. :**  12495H5555 This page transmits Revision No. 05 of Service Bulletin No. A300-28-6064 A D D I T I O N A L WO R K No additional work is required by this revision for aircraft modified by any previous issue. R E AS O N 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 is updated 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 15, Sheet 4 and 5 have been revised to clarify bonding. - Figure 16, Sheet 3 has been revised to clarify validity. - Figure 18, Sheet 2 and 3 have been revised to clarify bonding. 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

# A300-600 **A300-600** SERVICE BULLETIN REVISION TRANSMITTAL SHEET

- Figure 19, Sheet 4 and 5 have been revised to clarify bonding. - 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. C H A N G E S 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. . 1.D.(9) 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. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN REVISION TRANSMITTAL SHEET

- 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 the refueling pipes on LH side between FR44 and FR47 updated for Kit A01 and Kit A02. Installation of 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.(9)(b) Washer quantity changed and Note added. . 3.B.(9)(b)3 Washer quantity changed and Note added. . 3.B.(11)(a)6 Figure reference updated. . 3.B.(11)(b) Washer quantity changed and Note added. . 3.B.(11)(b)3 Washer quantity changed and Note added. . 3.B.(13) Item numbers corrected. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN REVISION TRANSMITTAL SHEET

. 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)8 Workstep added. . 3.B.(13)(a)9 Items and quantities changed. . 3.B.(13)(b) Washer quantity changed and Note added. . 3.B.(13)(b)3 Washer quantity changed and Note added. . 3.B.(15)(b) Washer quantity changed and Note added. . 3.B.(15)(b)3 Washer quantity changed and Note added. . 3.B.(16) Item numbers corrected. . 3.B.(16)(a)6 New workstep added. . 3.B.(16)(a)7 Workstep added. . 3.B.(16)(a)8 Workstep added. . 3.B.(16)(a)9 Items and quantities changed. . 3.B.(16)(b) Washer quantity changed and Note added. . 3.B.(16)(b)3 Washer quantity changed and Note added. . 3.B.(19) Item numbers corrected. . 3.B.(19)(a)6 New workstep added. . 3.B.(19)(a)7 Workstep added. . 3.B.(19)(a)8 Workstep added. . 3.B.(19)(a)9 Item numbers revised. . 3.B.(19)(b) Washer quantity changed and Note added. . 3.B.(19)(b)3 Washer quantity changed and Note added. . 3.B.(20)(b) Washer quantity changed and Note added. . 3.B.(20)(b)3 Washer quantity changed and Note added. . 3.B.(21)(b) Washer quantity changed and Note added. . 3.B.(21)(b)3 Washer quantity changed and Note added. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN REVISION TRANSMITTAL SHEET

. 3.B.(22)(b) Washer quantity changed and Note added. . 3.B.(22)(b)3 Washer quantity changed and Note added. . 3.B.(24)(b) Washer quantity changed and Note added. . 3.B.(24)(b)5 Washer quantity changed and Note added. . 3.B.(25)(b) Washer quantity changed and Note added. . 3.B.(25)(b)3 Washer quantity changed and Note added. . 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.(5) Introduced by Rev 04 has been added. . 3.D.(6) Introduced by Rev 04 has been added. . 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. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 5 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN REVISION TRANSMITTAL SHEET

- Figure 14

. Sheets 2 and 3 revised. - Figure 15

. Figure 15, Sheets 4, 5 and 7 modified. - Figure 16

. Sheet 3 revised. - Figure 18

. Sheets 2 and 3 revised. - Figure 19

. Sheets 4 and 5 revised. - 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 reference changed. - Figure 42

. Figure reference changed. - Figure 43

. Figure reference changed. - Figure 44 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 6 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN REVISION TRANSMITTAL SHEET

. Figure reference changed. - Figure 45

. Figure reference changed. - Figure 46

. Figure reference changed. - Figure 47

. Figure reference changed. - Figure 48

. Figure reference changed. - Figure 50

. Sheet 2 revised. - Figure 51

. Sheet 2 revised. - Figure 52

. Washer quantity changed. F I L I N G I N ST R U CT I O N S This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. H I STO RY O F P R E V I O U S R E V I S I O N S Revision 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.

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

REVISION No. : 05 - Sep 27/10 Page : 7 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN REVISION TRANSMITTAL SHEET

Revision No. 02 was issued to include improvements further to discrepancies found during accomplishment. Revision No. 03 was issued to include improvements further to discrepancies found during accomplishment. 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). R E V I S I O N S E Q U E N C E ORIGINAL : Jul 28/05 REVISION No. : 01 - Apr 03/07 REVISION No. : 02 - Mar 10/08 REVISION No. : 03 - Dec 15/08 REVISION No. : 04 - Aug 24/09 REVISION No. : 05 - Sep 27/10

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

REVISION No. : 05 - Sep 27/10 Page : 8 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN SUMMARY

**AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  **Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F**  **Fax : (33) 5 61 93 42 51** This summary is for information only and is not approved for modification of the aircraft M A N DA TO RY M A N DA TO RY M A N DA TO RY M A N DA TO RY **ATA SYSTEM : 28 TITLE : FUEL - GENERAL - MODIFY THE EQUIPMENT IN THE FUEL TANKS FOR ADDITIONAL**  **ELECTRICAL BONDING MODIFICATION No. :**  12495H5555 R E AS O N/D E S C R I PT I O N/O P E RA T I O N A L CO N S E Q U E N C E S As part of the Fuel Safety Assessment program, AIRBUS has carried out investigations of the electrical bonding in the aircraft fuel tanks. As a result of these investigations this Service Bulletin has been issued for additional electrical bonding of the equipment in the fuel tanks. This modification consists of installing additional bonding leads and electrical bonding points in the wings fuel tanks and center tank. The accomplishment of this Service Bulletin provides improved electrical bonding to ensure continuous electrical bonding protection of all the equipment in the fuel tanks for the design life goal of the aircraft. This Service Bulletin has been validated on A300-600 aircraft MSN 0569.

EVALUATION TABLE COMPLIANCE Mandatory CANCELS INSPECTION SB No POTENTIAL AD Yes A/C OPERATION AFFECTED No RELIABILITY AFFECTED No PAX COMFORT AFFECTED No COST SAVING No ETOPS AFFECTED No STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED No DEFUEL/VENTILATION Yes KIT PRICE (USD) Refer to SB

MODIFICATION CLASSIFICATION MAJOR None MINOR 12495H5555

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

REVISION No. : 05 - Sep 27/10 Page : 1 of 4 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN SUMMARY

As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics, affecting the airworthiness of the product. All other changes are Major changes. **E F**  **F E**  **C T** **I V**  **I T** **Y** 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 MXU OHY QTR SUD TAR THA UPS UZB C O N C U R R E N T R E Q U I R E M E N TS None R E F E R E N C E S/R E P E RC U S S I O N S TFU : None OEB : None AOT : None SIL : 28-072 LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No OTHERS : None N A T U R E O F T H E WO R K AIRCRAFT : Yes EQUIPMENT : No HARD : No SOFT : No OBRM : No M A N P OW E R Center Tank, Kit 286064A01R05

**TOTAL MANHOURS 114.5 ELAPSED TIME (HOURS) 73.0**  Center Tank, Kit 286064A02R02 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 2 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN SUMMARY

**TOTAL MANHOURS 114.5 ELAPSED TIME (HOURS) 73.0**  Center Tank, Kit 286064A03R00

**TOTAL MANHOURS 104.5 ELAPSED TIME (HOURS) 63.0**  LH and RH Wing Fuel Tanks - Config. 08 (Post Mod. 12226 Aircraft only)

**TOTAL MANHOURS 20 ELAPSED TIME (HOURS) 10.0**  LH and RH Wing Fuel Tanks - All other Aircraft

**TOTAL MANHOURS 226.0*** **ELAPSED TIME (HOURS) 114.5** NOTE(*) Subject to aircraft configuration. Refer to para. 1.G. MANPOWER in the Service Bulletin for the breakdown of the wings manhours. The manhours are given by rib bay and aircraft configuration. ADDITIONAL WORK (Introduced by Rev 01)

**TOTAL MANHOURS 2.0 ELAPSED TIME (HOURS) 2.0**  ADDITIONAL WORK (Introduced by Rev 03)

**TOTAL MANHOURS 62.5 ELAPSED TIME (HOURS) 31.0**  ADDITIONAL WORK (Introduced by Rev 04)

**TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  ADDITIONAL WORK (Introduced by Rev 04)

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

REVISION No. : 05 - Sep 27/10 Page : 3 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN SUMMARY

**TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  ADDITIONAL WORK (Introduced by Rev 04)

**TOTAL MANHOURS 64.5 ELAPSED TIME (HOURS) 31.0**  M A T E R I A L I N FO R M A T I O N 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. ADDITIONAL WORK (Introduced by Rev 01) Wings Fuel Tanks Equipment - Kit 286064B39R00: Bonding leads, nuts and screws. A P P E N D I C E S None

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

REVISION No. : 05 - Sep 27/10 Page : 4 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

**AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  **Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F**  **Fax : (33) 5 61 93 42 51** M A N DA TO RY M A N DA TO RY M A N DA TO RY M A N DA TO RY **ATA SYSTEM : 28 TITLE : FUEL - GENERAL - MODIFY THE EQUIPMENT IN THE FUEL TANKS FOR ADDITIONAL**  **ELECTRICAL BONDING MODIFICATION No. :**  12495H5555 This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or license is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or part to third parties and shall not be duplicated in any manner (except for the purpose of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. **1. P L** **A N**  **N I**  **N G**  **I N**  **F O**  **R M**  **A T** **I O**  **N A. E**  **F F**  **E C** **T I**  **V I**  **T Y**  (1) Models B4-601 B4-603 B4-605R B4-620 B4-622 B4-622R C4-605R/F C4-620 F4-605R F4-622R (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN: 0252 0284 0294 0301 0307 0312 0317 0321 0336 0341 0344 0348 0351 0354 0358 0361 0365 0368 0380 0388 0398 0401 0405 0408 0411 0414 0417 0423 0459-0466 0469 0470 0474 0477 0479 0505-0518 0521 0525 0529 0530 0532 0536 0540 0543 0546 0553-0561 0563 0566 0569 0572 0575 0577 0579 0581 0582 0584 0601-0619 0621 0623 0625-0633 0635 0637 0639 0641 0643 0645 0657 0659 0662 0664 0666 0668 0670 0673 0675 0677 0679 0681 0683 0685 0688 0692 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721-0750 0752-0764 0766-0775 0777-0794 0797 0799-0841 (b) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 1 of 267 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. OPERATOR MSN 66U 0733 0734 0739 0750 0756 0762 AAL 0423 0459 0460 0461 0463 0466 0469 0470 0474 0506 0507 0508 0509 0510 0511 0512 0513 0514 0515 0516 0517 0606 0610 0612 0615 0619 0626 0639 0643 0645 0675 AAW 0354 ABD 0529 0557 0755 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 0559 0572 0575 0579 0581 0611 0613 0625 0630 0633 0657 0659 0664 0668 0688 0709 0713 0715 0726 0728 0735 0736 0738 0742 0745 0748 0752 0757 0759 0760 0761 0766 0768 0769 0771 0772 0774 0777 0778 0779 0780 0781 0789 0790 0791 0792 0793 0794 0799 0800 0801 0802 0803 0804 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 0729 0730 0737 0740 0753 0770 0783 0797 0836 0837 0838 KAC 0344 0673 0694 0699 0719 0721 KAL 0582 0609 0627 0631 0662 0685 0692 0731 LAA 0601 0616 MNB 0758 MON 0540 0556 0604 0605 MSR 0561 0607 MXU 0767 0788 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 2 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

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 0705 0782 0784 0785 0786 0787 UPS 0805 0806 0807 0808 0809 0810 0811 0812 0813 0814 0815 0816 0817 0818 0819 0820 0821 0822 0823 0824 0825 0826 0827 0828 0829 0830 0831 0832 0833 0834 0835 0839 0840 0841 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 0561 0566 0569 0572 0575 0577 0579 0581-0582 0584 0603-0610 0612 0615 0619 0625-0629 0631-0632 0635 0639 0643 0645 0657 0659 0662 0666 0673 0675 0677 0681 0685 0692 0694 0701 0705 0717 0722-0723 0725 KIT No. QTY PER A/C CONFIGURATION 286064A01R05 1 01 NOTE(01) Kit 286064A01R05 concerns the modification of the electrical bonding in the center tank and is valid for aircraft on which Mod. No. 8692S20032 (FUEL - SECTION - INTRODUCE MOULDED PARTS ON A300/600) is not embodied. NOTE(02) Additional work is required by this revision for aircraft modified by Revision 00 or 01 or 02. This additional work was introduced at revision 03. NOTE(03) Config. 01 is valid for aircraft on which Mod. No. 04801H5078 (FUEL - INSTALL TRIM TANK SYSTEM) is embodied. The Kits and configurations applicable to these MSNs are given at the end of this list 0477 0479 0505 0521 0525 0530 0532 0543 0546 0553-0554 0558 0560 0563 0601-0602 0611 0613-0614 0616-0618 0621 0623 0630 0633 0637 0641 0664 0668 0670 0679 0683 0688 0696 0699 0703 0707 0709 0711 0713 0715 0719 0721 0724 KIT No. QTY PER A/C CONFIGURATION

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

REVISION No. : 05 - Sep 27/10 Page : 3 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

286064A01R05 1 01 286064A03R00 1 01 NOTE(01) Kit 286064A01R05 concerns the modification of the electrical bonding in the center tank and is valid for aircraft on which Mod. No. 8692S20032 (FUEL - SECTION - INTRODUCE MOULDED PARTS ON A300/600) is not embodied. NOTE(02) Additional work is required by this revision for aircraft modified by Revision 00 or 01 or 02. This additional work was introduced at revision 03. NOTE(03) Config. 01 is valid for aircraft on which Mod. No. 04801H5078 (FUEL - INSTALL TRIM TANK SYSTEM) is embodied. NOTE(04) Kit 286064A03R00 concerns the modification of the electrical bonding in the center tank and is valid for aircraft on which Mod. No. 12315S22009 (FUEL - FUEL PUMP SYSTEM - ADD BONDING LEAD ON RH AND LH CENTER TANK BOOSTER PUMP CANISTERS) is not embodied and for aircraft on which Mod. No. 12314H5524 (FUEL - FUEL PUMP SYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMP CANISTERS) or Mod. No. 13041H5657 (FUEL - FUEL PUMP SYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMP CANISTERS) are not embodied or Service Bulletin No. A300-28-6069 or A300-28-6089 are not accomplished. The Kits and configurations applicable to these MSNs are given at the end of this list 0252 0284 0294 0301 0307 0312 0317 0321 0336 0341 0344 0348 0351 0354 0358 0361 0365 0368 0380 0388 0398 0405 0408 0411 0414 0417 KIT No. QTY PER A/C CONFIGURATION 286064A01R05 1 02 286064A03R00 1 02 NOTE(01) Kit 286064A01R05 concerns the modification of the electrical bonding in the center tank and is valid for aircraft on which Mod. No. 8692S20032 (FUEL - SECTION - INTRODUCE MOULDED PARTS ON A300/600) is not embodied. NOTE(02) Additional work is required by this revision for aircraft modified by Revision 00 or 01 or 02. This additional work was introduced at revision 03. NOTE(03) Config. 02 is valid for aircraft on which Mod. No. 04801H5078 (FUEL - INSTALL TRIM TANK SYSTEM) is not embodied.

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

REVISION No. : 05 - Sep 27/10 Page : 4 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

NOTE(04) Kit 286064A03R00 concerns the modification of the electrical bonding in the center tank and is valid for aircraft on which Mod. No. 12315S22009 (FUEL - FUEL PUMP SYSTEM - ADD BONDING LEAD ON RH AND LH CENTER TANK BOOSTER PUMP CANISTERS) is not embodied and for aircraft on which Mod. No. 12314H5524 (FUEL - FUEL PUMP SYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMP CANISTERS) or Mod. No. 13041H5657 (FUEL - FUEL PUMP SYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMP CANISTERS) are not embodied or Service Bulletin No. A300-28-6069 or A300-28-6089 are not accomplished. The Kits and configurations applicable to these MSNs are given at the end of this list 0727 0731 0733-0734 0739 0741 0743-0744 0747 0749-0750 0755-0756 0758 0762-0764 0767-0773 0775 0782 0784-0788 0794 0805-0841 KIT No. QTY PER A/C CONFIGURATION 286064A02R02 1 None NOTE(01) Kit 286064A02R02 concerns the modification of the electrical bonding in the center tank and is valid for aircraft on which Mod. No. 8692S20032 (FUEL - SECTION - INTRODUCE MOULDED PARTS ON A300/600) is embodied. NOTE(02) Additional work is required by this revision for aircraft modified by Revision 00 or 01 or 02. This additional work was introduced at revision 03. The Kits and configurations applicable to these MSNs are given at the end of this list 0726 0728-0730 0732 0735-0738 0740 0742 0745-0746 0748 0752-0754 0757 0759-0761 0766 0774 0777-0781 0783 0789-0793 0797 0799-0804 KIT No. QTY PER A/C CONFIGURATION 286064A02R02 1 None 286064A03R00 1 03 NOTE(01) Kit 286064A02R02 concerns the modification of the electrical bonding in the center tank and is valid for aircraft on which Mod. No. 8692S20032 (FUEL - SECTION - INTRODUCE MOULDED PARTS ON A300/600) is embodied. NOTE(02) Additional work is required by this revision for aircraft modified by Revision 00 or 01 or 02. This additional work was introduced at revision 03. NOTE(03) Config. 03 Kit 286064A03R00 concerns the modification of the electrical bonding in the center tank and is valid for aircraft on which Mod. No. 12315S22009 (FUEL - FUEL PUMP SYSTEM - ADD BONDING LEAD ON RH AND DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 5 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

LH CENTER TANK BOOSTER PUMP CANISTERS) is not embodied and for aircraft on which Mod. No. 12314H5524 (FUEL - FUEL PUMP SYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMP CANISTERS) or Mod. No. 13041H5657 (FUEL - FUEL PUMP SYSTEM - INSTALL MODIFIED CENTER TANK BOOSTER PUMP CANISTERS) are not embodied or Service Bulletin No. A300-28-6069 or A300-28-6089 are not accomplished. NOTE(04) Additional work is required by this revision for Config. 03 aircraft (using Kit A03) modified by Revision 00 or 01 or 02. This additional work was introduced at revision 04. The Kits and configurations applicable to these MSNs are given at the end of this list 0252 0284 0294 0301 0307 0312 0317 0321 0336 0341 0344 0348 0351 0354 0358 0361 0365 0368 0380 0388 0398 0405 0408 0411 0414 0417 0423 0459-0466 0469-0470 0474 0477 0479 0505-0518 0521 0525 0529-0530 532 0536 0540 0543 0546 0553-0561 0563 0566 0569 0572 0575 0577 0579 0581-0582 0584 0601-0619 0621 0623 0625-0633 0635 0637 0639 0641 0643 0645 0657 0659 0662 0664 0666 0668 0670 0673 0675 0677 0679 0681 0683 0685 0688 0692 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721-0750 0752-0764 0766-0775 0777-0794 0797 0799-0804 KIT No. QTY PER A/C CONFIGURATION 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

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

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# A300-600 **A300-600** SERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION 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 necessary for all aircraft. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

The Kits and configurations applicable to these MSNs are given at the end of this list 0805-0811 KIT No. QTY PER A/C CONFIGURATION 286064B20R06 2 08 NOTE : Config. 08 - Post Mod. 12226 aircraft. NOTE : Mod. No. 12365H5540 (FUEL - GENERAL - REVISE ELECTRICAL BONDING OF EQUIPMENT IN INNER WING FUEL TANKS) is embodied on MSN 0812 and subsequent. (3) Spares None **B. C O**  **N C**  **U R**  **R E**  **N T**  **R E**  **Q U**  **I R**  **E M**  **E N**  **T S**  None **C. R E** **A S**  **O N**  (1) History As part of the Fuel Safety Assessment program, AIRBUS has carried out investigations of the electrical bonding in the aircraft fuel tanks. This Service Bulletin has been validated on A300-600 aircraft MSN 0569. (2) Objective/Action As a result of these investigations this Service Bulletin has been issued for additional electrical bonding of the equipment in the fuel tanks. This modification consists of installing additional bonding leads and electrical bonding points in the wings fuel tanks and center tank. (3) Advantages The accomplishment of this Service Bulletin provides extra electrical bonding to ensure continuous electrical bonding protection of all the equipment in the fuel tanks for the design life goal of the aircraft. (4) Operational/Maintenance Consequences None **D. D E**  **S C**  **R I**  **P T** **I O**  **N** To accomplish this Service Bulletin it is necessary to:

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

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# A300-600 **A300-600** SERVICE BULLETIN

(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. (3) Center Tank Kit 286064A02R02 (a) Modify or install the bonding points. (4) Center Tank Kit 286064A03R00 (a) Install the bonding points. (5) LH and RH Wing Fuel Tanks - Kit 286064B01R05 thru Kit 286064B28R01 NOTE : Kit 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 thru to rib bay 27-28, LH and RH wing) for all Configs except Config. 08. For Config. 08 rib bays 1-2 only. (d) Install additional bonding leads and electrical bonding points. (e) Do electrical bonding resistant tests of the new electrical bonding points. (f) Re-fuel the wings fuel tanks. (g) Check the wings fuel tanks for leaks. (h) Close-up. (6) ADDITIONAL WORK 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) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

(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 by Rev 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. C O**  **M P**  **L I**  **A N**  **C E**  (1) Classification Mandatory (2) Accomplishment Timescale (a) Accomplishment of this Service Bulletin has been rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandatory accomplishment timescale. **F. A P**  **P R** **O V**  **A L**  Approved under EASA Design Organisation Approval No. EASA 21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 10 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

**G. M A**  **N P**  **O W**  **E R**  The manpower estimates given in this Service Bulletin are based on direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operators circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints and sealants, etc. and general administration are also not included. Center Tank Kit 286064A01R05 Get access 30.0 Check of the bonding points 40.0 Modification/install the bonding points 13.0 Test 1.5 Close-up 30.0 **TOTAL MANHOURS 114.5 ELAPSED TIME (HOURS) 73.0**  Center Tank Kit 286064A02R02 Get access 30.0 Check of the bonding points 40.0 Modification/install the bonding points 13.0 Test 1.5 Close-up 30.0 **TOTAL MANHOURS 114.5 ELAPSED TIME (HOURS) 73.0**  Center Tank Kit 286064A03R00 Get access 30.0 Check of the bonding points 40.0 Install the bonding points 3.0 Test 1.5 Close-up 30.0 **TOTAL MANHOURS 104.5** DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

**ELAPSED TIME (HOURS) 63.0** LH and RH Wing Fuel Tanks. The hours for the following kits are for both wings. Rib Bay 1-2, Config. 08 Aircraft Only Kit 286064B20R06 Modification 20.0 **TOTAL MANHOURS 20.0 ELAPSED TIME (HOURS) 10.0**  NOTE : After the completion of the work in the wings fuel tanks, operators should allow two hours for fuel leak tests. Rib Bay 1-2, Kit 286064B01R05 All Aircraft Get access 1.0 Modification 21.0 Close up 1.0 **TOTAL MANHOURS 23.0 ELAPSED TIME (HOURS) 11.5**  Rib Bay 1-2, Kit 286064B22R05 Config. 03 Aircraft Modification 6.0 **TOTAL MANHOURS 6.0 ELAPSED TIME (HOURS) 3.0**  Rib Bay 1-2, Kit 286064B23R01 Config. 06 Aircraft Modification 2.0 **TOTAL MANHOURS 2.0 ELAPSED TIME (HOURS) 1.0**  Rib Bay 2-3, Kit 286064B01R05 All Aircraft Modification 6.0 **TOTAL MANHOURS 6.0 ELAPSED TIME (HOURS) 3.0**  DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

Rib Bay 2-3, Kit 286064B21R01 Config. 04 Aircraft Modification 6.0 **TOTAL MANHOURS 6.0 ELAPSED TIME (HOURS) 3.0**  Rib Bay 5-6, Kit 286064B03R03 All Aircraft Get access 1.0 Modification 4.0 Close up 1.0 **TOTAL MANHOURS 6.0 ELAPSED TIME (HOURS) 3.0**  Rib Bay 5-6, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft Modification 4.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  Rib Bay 8-9, Kit 286064B04R03 All Aircraft Get access 1.0 Modification 6.0 Close up 1.0 **TOTAL MANHOURS 8.0 ELAPSED TIME (HOURS) 4.0**  Rib Bay 8-9, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft Modification 4.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  Rib Bay 9-10, Kit 286064B05R01 All Aircraft Get access 1.0 Modification 6.0 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

Close up 1.0 **TOTAL MANHOURS 8.0 ELAPSED TIME (HOURS) 4.0**  Rib Bay 9-10, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft Modification 4.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  Rib Bay 10-11, Kit 286064B06R03 All Aircraft Get access 1.0 Modification 4.0 Close up 1.0 **TOTAL MANHOURS 6.0 ELAPSED TIME (HOURS) 3.0**  Rib Bay 10-11, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft Modification 4.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  Rib Bay 11-12, Kit 286064B07R01 All Aircraft Get access 1.0 Modification 2.0 Close up 1.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 4.0**  Rib Bay 12-13, Kit 286064B08R03 All Aircraft Get access 1.0 Modification 4.0 Close up 1.0 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

**TOTAL MANHOURS 6.0 ELAPSED TIME (HOURS) 3.0**  Rib Bay 12-13, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft Modification 4.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  Rib Bay 13-14, and Kit 286064B09R04 All Aircraft Get access 1.0 Modification 6.0 Close up 1.0 **TOTAL MANHOURS 8.0 ELAPSED TIME (HOURS) 4.0**  Rib Bay 14-15, Kit 286064B10R01 All Aircraft Get access 1.0 Modification 14.0 Close up 1.0 **TOTAL MANHOURS 16.0 ELAPSED TIME (HOURS) 8.0**  Rib Bay 14-15, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft Modification 4.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  Rib Bay 14-15, Kit 286064B25R01 Config. 07 Aircraft Modification 2.0 **TOTAL MANHOURS 2.0 ELAPSED TIME (HOURS) 1.0**  DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

Rib Bay 15-16, Kit 286064B11R05 All Aircraft Get access 1.0 Modification 8.0 Close up 1.0 **TOTAL MANHOURS 10.0 ELAPSED TIME (HOURS) 5.0**  Rib Bay 15-16, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft Modification 4.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  Rib Bay 16-17, Kit 286064B12R01 All Aircraft Get access 1.0 Modification 2.0 Close up 1.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  Rib Bay 17-18, Kit 286064B25R01 Config. 07 Aircraft Get access 1.0 Modification 1.0 Close up 1.0 **TOTAL MANHOURS 3.0 ELAPSED TIME (HOURS) 1.5**  Rib Bay 18-19, Kit 286064B13R03 All Aircraft Get access 1.0 Modification 4.0 Close up 1.0 **TOTAL MANHOURS 6.0** DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

**ELAPSED TIME (HOURS) 3.0** Rib Bay 18-19, Kit 286064B02R02 or Kit 286064B26R01 Config. 01 and Config. 02 Modification 4.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  Rib Bay 20-21, Kit 286064B14R02 All Aircraft Get access 1.0 Modification 4.0 Close up 1.0 **TOTAL MANHOURS 6.0 ELAPSED TIME (HOURS) 3.0**  Rib Bay 20-21, Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft Modification 4.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  Rib Bay 21-22, Kit 286064B15R04 All Aircraft Get access 1.0 Modification 4.0 Close up 1.0 **TOTAL MANHOURS 6.0 ELAPSED TIME (HOURS) 3.0**  Rib Bay 21-22 Kit 286064B02R02 or Kit 286064B26R01 Config. 01 and Config. 02 Modification 4.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  Rib Bay 24-25, Kit 286064B16R03 All Aircraft DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

Get access 1.0 Modification 4.0 Close up 1.0 **TOTAL MANHOURS 6.0 ELAPSED TIME (HOURS) 3.0**  Rib Bay 24-25, Kit 286064B02R02 or Kit 286064B26R01 Config. 01 and Config. 02 Modification 4.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  Rib Bay 25-26, Kit 286064B19R02 All Aircraft Get access 1.0 Modification 1.0 Close up 1.0 **TOTAL MANHOURS 3.0 ELAPSED TIME (HOURS) 1.5**  Rib Bay 26-27, Kit 286064B17R01 All Aircraft Get access 1.0 Modification 5.0 Close up 1.0 **TOTAL MANHOURS 7.0 ELAPSED TIME (HOURS) 3.5**  Rib Bay 26-27, Kit 286064B27R01 or Kit 286064B28R01 Config. 02 Aircraft Modification 5.0 **TOTAL MANHOURS 5.0 ELAPSED TIME (HOURS) 2.5**  Rib Bay 27-28, Kit 286064B18R04 All Aircraft Get access 1.0 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

Modification 8.0 Close up 1.0 **TOTAL MANHOURS 10.0 ELAPSED TIME (HOURS) 5.0**  Rib Bay 27-28, Kit 286064B02R02 or Kit 286064B26R01 Config. 01 and Config. 02 Modification 4.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  NOTE : The overall manhours for the wings fuel tanks can vary between 162 total manhours, elapsed time 83 manhours and 226 total manhours, 113 elapsed time manhours, depending on the aircraft configuration. NOTE : After the completion of the work in the wings fuel tanks, operators should allow two hours for fuel leak tests. ADDITIONAL WORK on LH wing tank (Introduced by Rev 01) Rib Bay 13-14, Kit 286064B39R00 All Aircraft Get access 0.5 Modification 1.0 Close up 0.5 **TOTAL MANHOURS 2.0 ELAPSED TIME (HOURS) 2.0**  ADDITIONAL WORK on center tank (Introduced by Rev 03) Get access 30.0 Check of the bonding points 1.0 Test 1.5 Close-up 30.0 **TOTAL MANHOURS 62.5 ELAPSED TIME (HOURS) 31.0**  ADDITIONAL WORK on wings tanks (Introduced by Rev 04) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

Rib Bay 14-15, Kit 286064B25R01 Config. 07 Aircraft Get access 1.0 Modification 2.0 Close up 1.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  ADDITIONAL WORK on wings tanks (Introduced by Rev 04) Rib Bay 17-18, Kit 286064B25R01 Config. 07 Aircraft Get access 1.0 Modification 2.0 Close up 1.0 **TOTAL MANHOURS 4.0 ELAPSED TIME (HOURS) 2.0**  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 ELAPSED TIME (HOURS) 31.0**  **H. W E**  **I G**  **H T**  **A N**  **D B** **A L** **A N**  **C E**  Not changed **I. E L**  **E C** **T R**  **I C** **A L**  **L O** **A D**  **D A**  **T**

**A** Not changed

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

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# A300-600 **A300-600** SERVICE BULLETIN

**J. R E**  **F E**  **R E**  **N C**  **E S**  Aircraft Maintenance Manual (AMM) : 06-41-57 20-28-11 24-00-00 24-31-11 24-41-00 27-80-00 28-00-00 28-10-00 28-11-00 28-11-22 28-11-29 28-25-00 28-25-21 28-42-00 33-13-00 33-14-00 57-20-43 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 51-43-00 51-75-10 51-76-10 51-76-20 Consumable Materials List (CML) Service Bulletin (SB) : A300-28-6028 A300-28-6069 A300-28-6089 A300-57-6026 A300-57-6070 **K. P U**  **B L**  **I C** **A T** **I O**  **N S**  **A F**  **F E**  **C T**  **E D**  Aircraft Maintenance Manual (AMM) : 28-11-21 28-12-15 28-21-13 28-21-21 28-25-15 28-25-21 28-42-23 28-42-24 28-42-35 28-42-36 28-42-44 28-42-45 28-43-21 28-46-21 28-46-22 57-20-43 Illustrated Parts Catalogue (IPC) : 28-11-05 28-11-11 28-11-12 28-21-13 28-21-21 28-25-03 28-25-05 28-25-12 28-26-03 28-42-44 28-43-05 57-20-43 **L. I N**  **T E**  **R C**  **H A**  **N G**  **E A**  **B I**  **L I**  **T Y**  **/ M**  **I X** **A B**  **I L**  **I T** **Y** None

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

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# A300-600 **A300-600** SERVICE BULLETIN

This Page Intentionally Left Blank

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

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# A300-600 **A300-600** SERVICE BULLETIN

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

**A I**  **L A**  **B I**  **L I**  **T Y**  (1) Material Operators with aircraft shown in the effectivity of this Service Bulletin should submit a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is: AIRBUS Material Logistics and Suppliers Weg beim Jaeger 150 P.O. Box 630262 D-22335 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 25 90 (2) Price and Availability Kit 286064A01R05 Cost : 181,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064A02R02 Cost : 119,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 286064A03R00 Cost : 137,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 286064B01R05 Cost : 214,00 US dollars Availability : 30 calendar days from receipt of order

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

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# A300-600 **A300-600** SERVICE BULLETIN

The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B02R02 Cost : 40,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B03R03 Cost : 80,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B04R03 Cost : 105,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B05R01 Cost : 100,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B06R03 Cost : 300,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B07R01 Cost : 17,00 US dollars Availability : 30 calendar days from receipt of order DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 24 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B08R03 Cost : 170,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B09R04 Cost : 48,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B10R01 Cost : 680,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B11R05 Cost : 144,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B12R01 Cost : 29,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B13R03 Cost : 235,00 US dollars Availability : 30 calendar days from receipt of order DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B14R02 Cost : 197,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B15R04 Cost : 183,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B16R03 Cost : 138,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B17R01 Cost : 183,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B18R04 Cost : 170,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B19R02 Cost : 40,00 US dollars Availability : 30 calendar days from receipt of order DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 26 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B20R06 Cost : 261,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B21R01 Cost : 170,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B22R05 Cost : 62,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B23R01 Cost : 17,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B25R01 Cost : 157,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B26R01 Cost : 40,00 US dollars Availability : 30 calendar days from receipt of order DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 27 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B27R01 Cost : 197,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. Kit 286064B28R01 Cost : 197,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. NOTE : The kits availability given above is the standard lead time from the date of your purchase order. If you require the Kits before this time, please include your retrofit planning schedule with your order so that we can try to comply with your requirements. ADDITIONAL WORK (Introduced by Rev 01) Kit 286064B39R00 Cost : 26,00 US dollars Availability : 30 calendar days from receipt of order The sales terms (Cost and Availability) are estimated in relation to economic conditions at the issue date of this Service Bulletin. NOTE : The kits availability given above is the standard lead time from the date of your purchase order. If you require the Kits before this time, please include your retrofit planning schedule with your order so that we can try to comply with your requirements. **B. I N**  **D U**  **S T**  **R Y**  **S U**  **P P**  **O R** **T I**  **N F**  **O R**  **M A**  **T I**  **O N**  AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

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

REVISION No. : 05 - Sep 27/10 Page : 28 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

**C. L I**  **S T**  **O F**  **C O**  **M P**  **O N**  **E N**  **T S**  Kit 286064A01R05 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 2 NAS1303-3 2 Bolt 3 NAS1149F0332P 2 Washer 4 NAS1726-4E 2 Nut 5 NAS1726-3E 14 Nut 7 E0088-10-125 1 Lead 8 NSA5519-2B 3 Clamp 13 AN735D40 8 Clamp 14 NAS1801-3-8 8 Screw 15 E0088-10-80 7 Lead 16 E0088-10-200 3 Lead 17 NAS1303-2 2 Bolt NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 286064A02R02 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 2 NAS1303-3 2 Bolt 3 NAS1149F0332P 1 Washer 4 NAS1726-4E 1 Nut 5 NAS1726-3E 19 Nut 7 E0088-10-125 1 Lead 8 NSA5519-2B 3 Clamp 9 NSA5050-4 1 Nut 13 AN735D40 8 Clamp 14 NAS1801-3-8 8 Screw 15 E0088-10-80 7 Lead 16 E0088-10-200 3 Lead 17 NAS1303-2 1 Bolt NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. Kit 286064A03R00 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 2 NAS1303-3 2 Bolt 3 NAS1149F0332P 2 Washer 5 NAS1726-3E 2 Nut 10 E0088-10-200 2 Lead DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 29 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 11 ASNA2050DCJ3215 4 Rivet 12 A9242127720000 2 Angle Kit 286064B01R05 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 4 NSA5472-4K7 4 Nut 14 E0088-41-160 1 Lead 15 AN742D6 1 Clamp 16 NSA5474-3K7 11 Nut 17 NSA5020-3-3 3 Bolt 20 NSA5474-4K7 7 Nut 25 H19200C4 1 Nut 27 NSA5041VBV3-4 1 Bolt 28 AN960C10L 1 Washer 34 NSA5041VBV3-10 2 Bolt 35 NSA5519-2B 4 Clamp 37 NAS1303-2 4 Bolt 38 E0088-10-100 2 Lead 39 E0088-41-100 2 Lead 45 NSA5022-4-21 4 Screw 46 NAS1304-3 4 Bolt 49 NSA5472-5K7 5 Nut 52 A2824028520000 3 Washer 53 AN960PD416 3 Washer 74 AN960KD10L 2 Washer 77 NSA5041VBV3-8 1 Bolt Kit 286064B02R02 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 4 NSA5472-4K7 4 Nut 9 A5715206420000 1 Plate 13 NAS1252-416L 1 Washer Kit 286064B03R03 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 2 NSA5020-3-6 1 Bolt 4 NSA5472-4K7 2 Nut 5 AN960C416L 1 Washer 6 NSA5041VBV4-2 1 Bolt 16 NSA5474-3K7 1 Nut 70 NSA5020-3-2 1 Bolt

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

REVISION No. : 05 - Sep 27/10 Page : 30 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Kit 286064B04R03 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 4 NSA5472-4K7 2 Nut 5 AN960C416L 1 Washer 16 NSA5474-3K7 1 Nut 17 NSA5020-3-3 1 Bolt 25 H19200C4 1 Nut 30 NSA5041VBV4-3 1 Bolt 88 AN960KD10 1 Washer Kit 286064B05R01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 1 E0088-40-100 1 Lead 3 NSA5041VBV4-11 1 Bolt 4 NSA5472-4K7 2 Nut 5 AN960C416L 1 Washer 7 NSA5041VBV3-5 1 Bolt 14 E0088-41-160 1 Lead 15 AN742D6 1 Clamp 16 NSA5474-3K7 3 Nut 17 NSA5020-3-3 1 Bolt 19 ABS0114-4-18 1 Bolt 20 NSA5474-4K7 1 Nut 31 NAS1303-10 1 Bolt Kit 286064B06R03 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 1 E0088-40-100 1 Lead 4 NSA5472-4K7 3 Nut 5 AN960C416L 1 Washer 16 NSA5474-3K7 1 Nut 18 NSA5472-3K7 1 Nut 28 AN960C10L 1 Washer 32 NSA5041VBV4-9 1 Bolt 33 NSA5041VBV3-3 1 Bolt 40 ABS0114-4-16 1 Bolt 70 NSA5020-3-2 1 Bolt Kit 286064B07R01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 16 NSA5474-3K7 2 Nut 20 NSA5474-4K7 1 Nut 39 E0088-41-100 1 Lead 50 AN742D8 1 Clamp 51 NAS1100-3-7 1 Screw DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 31 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 55 NAS1304-11 1 Bolt 56 NAS1303-7 1 Bolt 58 NAS1304-14 1 Bolt Kit 286064B08R03 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 4 NSA5472-4K7 3 Nut 5 AN960C416L 1 Washer 16 NSA5474-3K7 2 Nut 28 AN960C10L 1 Washer 32 NSA5041VBV4-9 1 Bolt 41 NSA5041VBV3-2 1 Bolt 42 NAS1303-1 1 Bolt 44 ABS0114-4-15 1 Bolt 89 E0088-40-190 1 Lead Kit 286064B09R04 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 16 NSA5474-3K7 4 Nut 17 NSA5020-3-3 1 Bolt 20 NSA5474-4K7 2 Nut 25 H19200C4 1 Nut 51 NAS1100-3-7 2 Screw 59 E0088-41-304 2 Lead 70 NSA5020-3-2 1 Bolt 90 NSA5020-3-5 1 Bolt Kit 286064B10R01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 1 E0088-40-100 1 Lead 4 NSA5472-4K7 2 Nut 5 AN960C416L 1 Washer 7 NSA5041VBV3-5 1 Bolt 14 E0088-41-160 1 Lead 15 AN742D6 1 Clamp 16 NSA5474-3K7 8 Nut 17 NSA5020-3-3 1 Bolt 18 NSA5472-3K7 2 Nut 20 NSA5474-4K7 3 Nut 26 NSA5041VBV3-7 1 Bolt 35 NSA5519-2B 4 Clamp 37 NAS1303-2 4 Bolt 38 E0088-10-100 2 Lead 39 E0088-41-100 2 Lead DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 32 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 45 NSA5022-4-21 4 Screw 54 NSA5041VBV4-7 1 Bolt 57 ABS0114-4-14 1 Bolt 69 NSA5041VBV3-6 2 Bolt Kit 286064B11R05 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 1 E0088-40-100 1 Lead 4 NSA5472-4K7 5 Nut 5 AN960C416L 1 Washer 14 E0088-41-160 1 Lead 15 AN742D6 1 Clamp 16 NSA5474-3K7 1 Nut 17 NSA5020-3-3 1 Bolt 18 NSA5472-3K7 2 Nut 20 NSA5474-4K7 3 Nut 28 AN960C10L 1 Washer 29 NSA5041VBV4-8 1 Bolt 33 NSA5041VBV3-3 1 Bolt 46 NAS1304-3 2 Bolt 49 NSA5472-5K7 2 Nut 52 A2824028520000 2 Washer 53 AN960PD416 1 Washer 70 NSA5020-3-2 1 Bolt 85 ABS0114-4-13 1 Bolt Kit 286064B12R01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 16 NSA5474-3K7 2 Nut 70 NSA5020-3-2 1 Bolt 71 NSA5020-3-4 1 Bolt Kit 286064B13R03 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 1 E0088-40-100 1 Lead 4 NSA5472-4K7 3 Nut 5 AN960C416L 1 Washer 16 NSA5474-3K7 1 Nut 18 NSA5472-3K7 1 Nut 28 AN960C10L 1 Washer 29 NSA5041VBV4-8 1 Bolt 33 NSA5041VBV3-3 1 Bolt 42 NAS1303-1 1 Bolt 61 ABS0114-4-12 1 Bolt DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 33 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Kit 286064B14R02 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 1 E0088-40-100 1 Lead 4 NSA5472-4K7 3 Nut 5 AN960C416L 1 Washer 12 NSA5041VBV4-5 1 Bolt 16 NSA5474-3K7 1 Nut 25 H19200C4 1 Nut 54 NSA5041VBV4-7 1 Bolt 63 ABS0114-4-10 1 Bolt 69 NSA5041VBV3-6 1 Bolt Kit 286064B15R04 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 1 E0088-40-100 1 Lead 4 NSA5472-4K7 1 Nut 5 AN960C416L 1 Washer 12 NSA5041VBV4-5 1 Bolt 16 NSA5474-3K7 2 Nut 28 AN960C10L 1 Washer 41 NSA5041VBV3-2 1 Bolt 42 NAS1303-1 1 Bolt 64 NSA5475-4K7 2 Nut 86 ABS0114-4-9 1 Bolt Kit 286064B16R03 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 1 E0088-40-100 1 Lead 5 AN960C416L 1 Washer 7 NSA5041VBV3-5 1 Bolt 16 NSA5474-3K7 2 Nut 27 NSA5041VBV3-4 1 Bolt 28 AN960C10L 1 Washer 62 NSA5041VBV4-6 1 Bolt 64 NSA5475-4K7 2 Nut 87 DHS1085-4 1 Washer 91 ABS0114-4-6 1 Bolt Kit 286064B17R01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 1 E0088-40-100 1 Lead 4 NSA5472-4K7 2 Nut 5 AN960C416L 1 Washer 12 NSA5041VBV4-5 1 Bolt 16 NSA5474-3K7 8 Nut DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 34 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 18 NSA5472-3K7 1 Nut 20 NSA5474-4K7 1 Nut 28 AN960C10L 1 Washer 67 ABS0114-4-5 1 Bolt 72 ABS0114-3-6 1 Bolt Kit 286064B18R04 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 1 E0088-40-100 1 Lead 5 AN960C416L 1 Washer 7 NSA5041VBV3-5 3 Bolt 16 NSA5474-3K7 3 Nut 20 NSA5474-4K7 1 Nut 30 NAS1304-4 2 Bolt 64 NSA5475-4K7 2 Nut 65 DHS783-63-18 1 Washer 78 NSA5041VBV4-4 1 Bolt 79 ABS0114-4-4 1 Bolt 87 DHS1085-4 1 Washer Kit 286064B19R02 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 16 NSA5474-3K7 1 Nut 17 NSA5020-3-3 1 Bolt 71 NSA5020-3-4 1 Bolt Kit 286064B20R06 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 14 E0088-41-160 1 Lead 15 AN742D6 1 Clamp 16 NSA5474-3K7 15 Nut 17 NSA5020-3-3 3 Bolt 20 NSA5474-4K7 5 Nut 25 H19200C4 1 Nut 27 NSA5041VBV3-4 1 Bolt 28 AN960C10L 1 Washer 34 NSA5041VBV3-10 2 Bolt 35 NSA5519-2B 4 Clamp 37 NAS1303-2 8 Bolt 38 E0088-10-100 2 Lead 39 E0088-41-100 2 Lead 45 NSA5022-4-21 4 Screw 46 NAS1304-3 2 Bolt 52 A2824028520000 1 Washer DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 35 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 53 AN960PD416 2 Washer 74 AN960KD10L 2 Washer 77 NSA5041VBV3-8 1 Bolt Kit 286064B21R01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 16 NSA5474-3K7 2 Nut 17 NSA5020-3-3 1 Bolt 77 NSA5041VBV3-8 1 Bolt Kit 286064B22R05 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 16 NSA5474-3K7 7 Nut 23 NAS1303-8 1 Bolt 37 NAS1303-2 4 Bolt 82 NSA5480PN3-5 2 Bolt Kit 286064B23R01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 16 NSA5474-3K7 1 Nut 17 NSA5020-3-3 1 Bolt 38 E0088-10-100 1 Lead 83 NSA5519-4B 1 Clamp Kit 286064B25R01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 16 NSA5474-3K7 2 Nut 20 NSA5474-4K7 2 Nut 62 NSA5041VBV4-6 1 Bolt 66 NAS1153-12 1 Screw 68 NSA5041VBV4-14 1 Bolt 69 NSA5041VBV3-6 1 Bolt Kit 286064B26R01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 4 NSA5472-4K7 4 Nut 10 A5715206420100 1 Plate 13 NAS1252-416L 1 Washer

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

REVISION No. : 05 - Sep 27/10 Page : 36 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Kit 286064B27R01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 4 NSA5472-4K7 5 Nut 9 A5715206420000 1 Plate 12 NSA5041VBV4-5 4 Bolt 13 NAS1252-416L 1 Washer Kit 286064B28R01 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 4 NSA5472-4K7 5 Nut 10 A5715206420100 1 Plate 12 NSA5041VBV4-5 4 Bolt 13 NAS1252-416L 1 Washer Kit 286064B39R00 (ADDITIONAL WORK Introduced by Rev 01) ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 16 NSA5474-3K7 2 Nut 20 NSA5474-4K7 2 Nut 51 NAS1100-3-7 2 Screw 59 E0088-41-304 2 Lead NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. **D. L I**  **S T**  **O F**  **M A**  **T E**  **R I**  **A L** **S -**  **O P**  **E R** **A T** **O R**  **S U**  **P P**  **L I**  **E D**  (1) Consumable Materials DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP MAT No. Sealant Mat. No. 09-001 As required Sealant Mat. No. 09-002 As required Low Density Fuel Tank Sealant Mat. No. 09-002D As required Corrosion Inhibiting Brush Consistency Mat. No. 09-013B As required Corrosion Inhibiting Fillet Consistency Mat. No. 09-016B As required Sealant Mat. No. 09-018 As required Corrosion Inhibiting Sealant Sprayable Mat. No. 09-025 As required Sealant Mat. No. 09-530 As required Cleaning agent Mat. No. 11-026 As required Alodine Mat. No. 13-002 As required Primer Mat. No. 16-001C As required DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 37 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP MAT No. Varnish Mat. No. 16-021 As required NOTE : To accomplish this Service Bulletin it is necessary to use the expendable parts listed in the AMM 28-25-21 P. Block 401. (2) Components Center Tank ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP EN6115V5-15 1 Screw EN6115V5-16 1 Screw NSA5041VP4-11 2 Screw NSA5041-3-9 1 Screw NSA5061-3 1 Washer NSA5061-4 5 Washer NSA5112-03 1 Washer NSA5112-04 3 Washer NSA5050-3 48 Nut NSA5050-4 21 Nut NSA5050-5 2 Nut NSA5050-6 4 Nut NSA5075-6 2 Nut NSA5182-4 2 Nut NSA5182-3 2 Nut NAS1726-3E 1 Nut NAS1726-4E 7 Nut ASNA2529-4 2 Nut ASNA2529-5 2 Nut ASNA2029-3 2 Nut NSA5355-4CA 1 Nut ASNA2050DXJ4828 2 Rivet ASNA2050DCJ3215 54 Rivet ASNA2050DCJ4020 2 Rivet Additional Work on center tank (Introduced by revision 03) ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP NSA5061-3 1 Washer NSA5112-04 1 Washer ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 17 NAS1303-2 1 Screw 20 NAS1149D0316H 1 Washer

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

REVISION No. : 05 - Sep 27/10 Page : 38 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

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

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

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

REVISION No. : 05 - Sep 27/10 Page : 39 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

This Page Intentionally Left Blank

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

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# A300-600 **A300-600** SERVICE BULLETIN

**3. A C** **C O**  **M P**  **L I**  **S H**  **M E**  **N T**  **I N**  **S T**  **R U**  **C T**  **I O**  **N S**  **A. G E**  **N E**  **R A**  **L** WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : MAKE SURE THAT ALL THE FLIGHT CONTROLS GROUND SAFETY LOCKS AND NOTICES ARE IN POSITION BEFORE YOU START THIS MODIFICATION. WARNING : BEFORE YOU DO ANY WORK ON THE FUEL SYSTEM OBEY THE SAFETY PRECAUTIONS (REFER TO AMM 28-00-00 PAGE BLOCK 301). WARNING : DO NOT DO ANY WORK IN THE FUEL TANKS UNTIL THE VAPOR CONCENTRATION IS BELOW 20% OF THE LOWER EXPLOSION LIMIT (LEL). WARNING : OBEY THE MANUFACTURER’S SAFETY INSTRUCTIONS WHEN YOU USE SEALANTS, VARNISH AND CLEANING AGENTS IN THE FUEL TANKS. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE, TO DO THIS : - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. (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, Page block 301). WARNING : MAKE SURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF THE TRAVEL 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.

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

REVISION No. : 05 - Sep 27/10 Page : 41 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

(e) Open, safety and tag these circuit breakers : For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPIT DESIGN) is embodied. PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/XFR VALVE 2QU P55 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

or PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL/R OUTR & L INR & CTR L 2QJ 208/B27 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/XFR VALVE 2QU P55 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61 For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPIT DESIGN) is not embodied. PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL OUTR & L INR & CTR L 2QJ 208/B27 128VU FUEL/FUELING HI LVL 6QJ 805/L87 128VU FUEL/FUELING OVERFLOW 5QJ 805/L86 128VU FUEL/FUELING/TRANSFER VALVE 2QU P55 128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83 128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84 128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85 (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 AMM 28-10-00, Page block 301 and AMM 28-25-00, Page block 301). DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 42 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

(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 removed during the ventilation process. (i) For Slat Track Canisters and Screwjack Canisters it is necessary to remove the inboard heat shields (as applicable) to allow the removal/installation of the applicable canister-flange nut (Refer to AMM 57-20-43, Page block 401). (j) For some Track Cans/Jack Cans it may be difficult to get access to the modification areas due to the small work area. If necessary these Track Cans/Jack Cans can be temporarily removed to allow access for bonding preparation. For the removal/installation of Track Cans/Jack Cans, refer to AMM 57-20-43, Page block 401.

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

REVISION No. : 05 - Sep 27/10 Page : 43 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

(k) For Slat Track Canisters and Screwjack Canisters it is necessary to remove the inboard heat shields (as applicable) to allow the removal/installation of the applicable canister-flange nut (Refer to AMM 57-20-43, Page block 401). (l) ADDITIONAL WORK on center tank introduced by revision 01 1 De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page block 301). 2 Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page block 301). WARNING : MAKE SURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF 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 COCKPIT DESIGN) is embodied. PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/XFR VALVE 2QU P55 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61 6 or PANEL DESIGNATION FIN LOCATION 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 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/XFR VALVE 2QU P55 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

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

REVISION No. : 05 - Sep 27/10 Page : 44 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

7 For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPIT DESIGN) is not embodied. PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL OUTR & L INR & CTR L 2QJ 208/B27 128VU FUEL/FUELING HI LVL 6QJ 805/L87 128VU FUEL/FUELING OVERFLOW 5QJ 805/L86 128VU FUEL/FUELING/TRANSFER VALVE 2QU P55 128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83 128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84 128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85 8 Defuel and ventilate the wing fuel tanks (Refer to AMM 28-25-00, Page block 301). 9 Remove wing manhole covers as necessary (Refer to AMM 28-11-22, Page block 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). 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 CLEAR OF THE TRAVEL RANGES OF THE SLATS/FLAPS. 3 Fully extend the slats (Refer to AMM 27-80-00, Page block 301). 4 Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-11, Page block 301). 5 Put access platforms in position as necessary. 6 Defuel and ventilate the center fuel tanks and the wing fuel tanks (Refer to AMM 28-10-00, Page block 301 and AMM 28-25-00, Page block 301). 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 the inboard heat shields (as applicable) to allow the removal/installation of the applicable canister-flange nut (Refer to AMM 57-20-43, Page block 401). 9 For some Track Cans/Jack Cans it may be difficult to get access to the modification areas due to the small work area. If necessary these Track Cans/Jack Cans can be temporarily removed to allow access for bonding preparation. For the removal/installation of Track Cans/Jack Cans (Refer to AMM 57-20-43, Page block 401). DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 45 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

(n) ADDITIONAL WORK on center tank (Introduced by Rev 03) 1 De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page block 301). 2 Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page block 301). 3 Put the access platforms in position. 4 Make sure that the external connector(s) is (are) not connected to the aircraft receptacle(s) EXT PWR. 5 Make sure that there is (are) warning notice(s) on the external power receptacle(s) to tell persons not to connect an external power source. 6 Make sure that the EMER EXIT LT pushbutton switch on the panel 26VU is on the DISARM position. 7 In the flight compartment, on the overhead panel 51VU, release the BAT pushbutton switch. 8 Display a warning notice on the overhead panel 51VU to tell persons not to operate the batteries. 9 Display a warning notice on refuel/defuel panel 110VU to tell persons not to operate the NORMAL BATTERY switch. 1 0 Display a warning notice in the cockpit to tell persons not to start the Auxiliary Power Unit (APU). 1 1 Display a warning notice in the cockpit to tell persons not to start ENG 1, 2. 1 2 Open, safety and tag these circuit breakers : Depending on aircraft configuration PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 321/P56 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

or PANEL DESIGNATION FIN LOCATION DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 46 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 128VU FUEL/FUELING HI LVL 6QJ 805/L87 128VU FUEL/FUELING OVERFLOW AND CAL 5QJ 805/L86 128VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 805/L88 128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83 128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84 128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85 1 3 Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-11, Page block 301). 1 4 Defuel and ventilate the center fuel tank and the wing fuel tanks (Refer to AMM 28-10-00, Page block 301 and AMM 28-25-00, Page block 301). 1 5 Remove additional wing manhole covers as necessary (Refer to AMM 28-11-22, Page block 401). 1 6 Open the access doors 147AZ and 148AZ (Refer to AMM 28-11-29, Page block 401). (o) ADDITIONAL WORK center tank (For Config. 03 using Kit A03 only) 1 De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page block 301). 2 Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page block 301). 3 Put the access platforms in position. 4 Open, safety and tag these circuit breakers : For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPIT DESIGN) is embodied. PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/XFR VALVE 2QU P55 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

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

REVISION No. : 05 - Sep 27/10 Page : 47 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

or PANEL DESIGNATION FIN LOCATION 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 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/XFR VALVE 2QU P55 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61 For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPIT DESIGN) is not embodied. PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL OUTR & L INR & CTR L 2QJ 208/B27 128VU FUEL/FUELING HI LVL 6QJ 805/L87 128VU FUEL/FUELING OVERFLOW 5QJ 805/L86 128VU FUEL/FUELING/TRANSFER VALVE 2QU P55 128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83 128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84 128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85 5 Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-11, Page block 301). 6 Defuel and ventilate the center fuel tank (Refer to AMM 28-10-00, Page block 301 and AMM 28-25-00, Page block 301). 7 Open the access doors 147AZ and 148AZ (Refer to AMM 28-11-29, Page block 401). (p) ADDITIONAL WORK on the wing tanks (For Config. 07 only) (Introduced by Rev 04) 1 De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page block 301). 2 Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page block 301). WARNING : MAKE SURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF 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. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 48 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

5 Open, safety and tag these circuit breakers : For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPIT DESIGN) is embodied. PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/XFR VALVE 2QU P55 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

or PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL/R OUTR & L INR & CTR L 2QJ 208/B27 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/XFR VALVE 2QU P55 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61 For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPIT DESIGN) is not embodied. PANEL DESIGNATION FIN LOCATION 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 128VU FUEL/FUELING HI LVL 6QJ 805/L87 128VU FUEL/FUELING OVERFLOW 5QJ 805/L86 128VU FUEL/FUELING/TRANSFER VALVE 2QU P55 128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83 128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84 128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85 6 Defuel and ventilate the wing fuel tanks (Refer to AMM 28-25-00, Page block 301).

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

REVISION No. : 05 - Sep 27/10 Page : 49 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

7 Remove wing manhole covers as necessary (Refer to AMM 28-11-22, Page block 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 wings fuel tanks and the center fuel, refer to AMM 20-28-11, Page block 001 for: - the preparation of the bonding positions. - the installation of bonding leads, clamps and the installation of bolts as bonding bolts. - the electrical-bonding resistance checks of the bonding positions. - the application of protective coating to bonding items. **B. M O**  **D I**  **F I**  **C A**  **T I**  **O N**  (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 : DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 50 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

- If blue coat present, no further action. - If no blue coat then :

Measure the electrical resistance between part and the structure, (Refer to AMM 20-28-11, Page block 001). - If the ohmic resistance <10mhm, apply the blue coat. - If the ohmic resistance >10mhm, do the bonding, (Refer to AMM 20-28-11, Page block 001). 1 Check the bonding points Items 1 thru 5 at FR44. Refer to Figure 1, Sheet 1, (General location) Refer to Figure 2, Sheets 1 thru 6, (Detailed location) Refer to Figure 3, Sheet 1, (Result table) 2 Check the bonding points Items 6 thru 24 at FR47. Refer to Figure 1, Sheet 1, (General location) Refer to Figure 4, Sheets 1 thru 17, (Detailed location) Refer to Figure 5, Sheet 1, (Result table) 3 Check the bonding points Items 25 thru 29 on the rib 1 (LH side). Refer to Figure 1, Sheet 1, (General location) Refer to Figure 6, Sheets 1 thru 3, (Detailed location) Refer to Figure 7, Sheet 1, (Result table) 4 Check the bonding points Items 30 thru 44 on the intrados panel. Refer to Figure 1, Sheet 1, (General location) Refer to Figure 8, Sheets 1 thru 10, (Detailed location) Refer to Figure 9, Sheet 1, (Result table) 5 Check the bonding points Items 45 thru 51 on the rib 1 (RH side). Refer to Figure 1, Sheet 1, (General location) Refer to Figure 10, Sheets 1 thru 6, (Detailed location) Refer to Figure 11, Sheet 1, (Result table) 6 Check the bonding points Items 52 thru 78 on the extrados panel. Refer to Figure 1, Sheet 1, (General location) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 51 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Refer to Figure 12, Sheets 1 thru 8, (Detailed location) Refer to Figure 13, Sheet 1, (Result table) (2) Kit 286064A01R05 (a) Modify or install the bonding points. 1 Modify the refueling pipes on LH side between FR44 and FR47, valid for aircraft on which Mod. No. 04801H5078 (FUEL - INSTALL TRIM TANK SYSTEM) is embodied. Refer to Figure 14 Sheets 1 thru 3

a Remove : 1 screw Item (285) Retain 1 washer Item (3) Retain Disengage the bonding lead item (281) without complete removal. - On the sleeve item (268), do a stripping to the dimensions given in the figure 14 sheet 3 - Install on the sleeve item (268) : 1 Bonding Lead E0088-10-80 Item 15 1 Nut NAS1726-3E Item 5 1 Clamp AN735D40 Item 13 1 Screw NAS1801-3-8 Item 14

b Install the bonding leads item (281) and 15 with : 1 Screw Item (285) 1 Washer Item (3) NOTE : Items (3) and (285) were retained at removal.

c For aircraft on which modification No. 06549 (FUEL - TRIM TANK SYSTEM - EMBODY ANTI-MODIFICATION TO ALLOW CHANGE FROM "WET" TO "DRY") is not embodied, do a stripping on the sleeve item (268) to the dimensions given in the figure 14 sheet 3 detail E. - Install on the sleeve item (268) : 1 Bonding Lead E0088-10-80 Item 15 1 Nut NAS1726-3E Item 5 1 Clamp AN735D40 Item 13 1 Screw NAS1801-3-8 Item 14 - Remove : 1 Screw Item (220) Retain 1 Nut Item (4) Discard 1 Screw Item (285) Retain 1 Washer Item (3) Retain DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 52 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

- 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) Retain 1 Washer Item (3) Retain Disengage the bonding lead item (284) without complete removal. b On the sleeve item (268), do a stripping to the dimensions given in the figure 15 sheet 3

c Install on the sleeve item (268) : 1 Bonding Lead E0088-10-80 Item 15 1 Nut NAS1726-3E Item 5 1 Clamp AN735D40 Item 13 1 Screw NAS1801-3-8 Item 14

d Install the bonding leads item (284) and 15 with : 1 Screw Item (285) 1 Washer Item (3) NOTE : Items (3) and (285) were retained at removal. 3 Modify the sleeves item (268), 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 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 53 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

2 Washer Item (3) Retain 1 Screw Item (269) Retain 1 Nut Item (4) Discard - Disengage the bonding lead item (16). b On the sleeves item (268), do strippings to the dimensions given in the figure 15 sheet 6.

c On the tee pipe, do strippings to the dimensions given in the figure 15 sheet 6. d Install on the sleeves item (268) : Refer to Figure 15 Sheet 6 2 Bonding Lead E0088-10-160 Item 16 2 Clamp AN735D40 Item 13 2 Nut NAS1726-3E Item 5 2 Screw NAS1801-3-8 Item 14

e Put the bonding leads Item (16) and Item 16 in position on the tee pipe. Refer to Figure 15 Sheet 5 f Install : 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 the figure 15 sheet 8. b Install on the sleeves item (268) : Refer to Figure 15 Sheet 8 3 Bonding Lead E0088-10-80 Item 15 3 Clamp AN735D40 Item 13 3 Nut NAS1726-3E Item 5 3 Screw NAS1801-3-8 Item 14

c Attach the bonding lead Item 15 on the flange of tee pipe : Refer to Figure 15 Sheet 7 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 54 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

1 Bolt NAS1303-2 Item 17 1 Washer NAS1149D0316H Item 20

d Remove from the tee pipe : Refer to Figure 15 Sheet 8 2 Screw Item (569) Retain 2 Nut Item (5) Discard

e Put the bonding leads Item 15 in position on the tee pipe. Refer to Figure 15 Sheets 7 and 8 f Install on the tee pipe : Refer to Figure 15 Sheet 8 2 Screw Item (569) 2 Nut NAS1726-3E Item 5 NOTE : Item (569) was retained at removal. 5 Modify the feed pipes, valid for aircraft on which Mod. No. 04801H5078 (FUEL - INSTALL TRIM TANK SYSTEM) is embodied. Refer to Figure 16 Sheets 1 thru 3

a Remove from LH side : 1 Screw Item (285) Retain 1 Washer Item (413) Retain

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

c Install : 1 Bonding Lead E0088-10-80 Item 15 1 Clamp NSA5519-2B Item 8 1 Bolt NAS1303-3 Item 2 1 Nut NAS1726-3E Item 5 1 Screw Item (285) 1 Washer Item (413) NOTE : Items (285) and (413) were retained at removal. d Remove from RH side : 1 Screw Item (285) Retain 1 Washer Item (413) Retain 1 Nut Item (5) Discard Disengage the bonding lead without complete removal.

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

REVISION No. : 05 - Sep 27/10 Page : 55 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

e On the tube item (334), do a stripping to the dimensions given in the figure 16 sheet 3. f Install : 1 Bonding Lead E0088-10-160 Item 16 1 Clamp NSA5519-2B Item 8 1 Bolt NAS1303-3 Item 2 1 Nut NAS1726-3E Item 5 Put the bonding leads Item in position with : 1 Screw Item (285) 1 Washer Item (413) 1 Nut NAS1726-3E Item 5 NOTE : Items (285) and (413) were retained at removal. 6 Install new bonding lead on the cross feed pipe between FR46 and FR47 Refer to Figure 17 Sheets 1 and 2

a Remove : 1 Screw Item (2) Retain 1 Washer Item (3) Retain - Disengage the bonding lead without complete removal. b On the tube, do a stripping to the dimensions given in the figure 17 sheet 2.

c Install : 1 Nut NAS1726-3E Item 5 2 Bolt NAS1303-2 Item 17 2 Washer NAS1149F0332P Item 3 1 Bonding Lead E0088-10-125 Item 7 1 Clamp NSA5519-2B Item 8 - Install the bonding leads with : 1 Screw Item (2) 1 Washer Item (3) NOTE : Items (2) and (3) were retained at removal. (3) Kit 286064A02R02 (a) Modify or install the bonding points. 1 Modify the refueling pipes on LH side between FR44 and FR47. Refer to Figure 18 Sheets 1 thru 3

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

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# A300-600 **A300-600** SERVICE BULLETIN

1 Screw Item (285) Retain 1 Washer Item (3) Retain Disengage the bonding lead item (281) without complete removal. - On the sleeve item (268), do a stripping to the dimensions given in the figure 18 sheet 3 - Install on the sleeve item (268) : 1 Bonding Lead E0088-10-80 Item 15 1 Nut NAS1726-3E Item 5 1 Clamp AN735D40 Item 13 1 Screw NAS1801-3-8 Item 14

b Install the bonding leads item (281) and 15 with : 1 Screw Item (285) 1 Washer Item (3) NOTE : Items (3) and (285) were retained at removal.

c For aircraft on which modification No. 06549 (FUEL - TRIM TANK SYSTEM - EMBODY ANTI-MODIFICATION TO ALLOW CHANGE FROM "WET" TO "DRY") is not embodied, do a stripping on the sleeve item (268) to the dimensions given in the figure 18 sheet 3 detail E. - Install on the sleeve item (268) : 1 Bonding Lead E0088-10-80 Item 15 1 Nut NAS1726-3E Item 5 1 Clamp AN735D40 Item 13 1 Screw NAS1801-3-8 Item 14 - Remove : 1 Screw Item (220) Retain 1 Nut Item (4) Discard 1 Screw Item (285) Retain 1 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. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

Refer to Figure 19 Sheets 1 thru 3

a Remove : Refer to Figure 19 Sheets 2 and 3 1 Screw Item (1) Retain 1 Nut Item (5) Discard Disengage the bonding lead item (284) without complete removal. b On the sleeve item (268), do a stripping to the dimensions given in the figure 19 sheet 3

c Install on the sleeve item (268) : 1 Bonding Lead E0088-10-80 Item 15 1 Nut NAS1726-3E Item 5 1 Clamp AN735D40 Item 13 1 Screw NAS1801-3-8 Item 14

d Install the bonding leads item (284) and 15 with : 1 Screw Item (1) 1 Nut NAS1726-3E Item 5 NOTE : Item (1) was retained at removal. 3 Modify the sleeves item (268). Refer to Figure 19 Sheets 1, 4 thru 6

a Remove : Refer to Figure 19 Sheet 4 2 Screw Item (1) Retain 2 Nut Item (5) Discard 1 Screw Item (255) Retain 1 Nut Item (9) Discard - Disengage the bonding leads item (249). b On the sleeves item (268), do strippings to the dimensions given in the figure 19 sheet 6.

c On the tee pipe, do strippings to the dimensions given in the figure 19 sheets 4 and 6. d Install on the sleeves item (268) : Refer to Figure 19 Sheet 6 2 Bonding Lead E0088-10-160 Item 16 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

2 Clamp AN735D40 Item 13 2 Nut NAS1726-3E Item 5 2 Screw NAS1801-3-8 Item 14

e Put the bonding leads Item (249) and Item 16 in position on the tee pipe. Refer to Figure 19 Sheet 5 f Install : 2 Screw Item (1) 2 Nut NAS1726-3E Item 5 1 Screw Item (255) 1 Nut NSA5050-4 Item 9 NOTE : Items (1) and (255) were retained at removal. 4 Modify the sleeves item (268) from TTS pipes : Refer to Figure 19 Sheets 7 and 8

a On the sleeves item (268), do strippings to the dimensions given in the figure 19 sheet 8. b Install on the sleeves item (268) : Refer to Figure 19 Sheet 8 3 Bonding Lead E0088-10-80 Item 15 3 Clamp AN735D40 Item 13 3 Nut NAS1726-3E Item 5 3 Screw NAS1801-3-8 Item 14

c Remove from the tee pipe : Refer to Figure 19 Sheet 8 2 Screw Item (569) Retain 2 Nut Item (5) Discard

d Put the bonding leads Item 15 in position on the tee pipe. Refer to Figure 19 Sheets 7 and 8

e Install on the tee pipe : Refer to Figure 19 Sheet 8 2 Screw Item (569) 2 Nut NAS1726-3E Item 5 NOTE : Items (569) were retained at removal. 5 Modify the feed pipes. Refer to Figure 20 Sheets 1 thru 3 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

a Remove from LH side : 1 Screw Item (1) Retain 1 Nut Item (5) Discard

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

c Install : 1 Bonding Lead E0088-10-80 Item 15 1 Clamp NSA5519-2B Item 8 1 Bolt NAS1303-3 Item 2 2 Nut NAS1726-3E Item 5 1 Screw Item (1) NOTE : Item (1) was retained at removal. d Remove from RH side : 1 Screw Item (1) Retain 1 Nut Item (5) Discard Disengage the bonding lead without complete removal.

e On the tube item (334), do a stripping to the dimensions given in the figure 20 sheet 3. f Install : 1 Bonding Lead E0088-10-160 Item 16 1 Clamp NSA5519-2B Item 8 1 Bolt NAS1303-3 Item 2 1 Nut NAS1726-3E Item 5 Put the bonding leads in position with : 1 Screw Item (1) 1 Nut NAS1726-3E Item 5 NOTE : Item (1) was retained at removal. 6 Install new bonding lead on the cross feed pipe between FR46 and FR47 Refer to Figure 21 Sheets 1 and 2

a Remove : 1 Screw Item (1) Retain 1 Nut Item (5) Discard - Disengage the bonding lead without complete removal. b On the tube, do a stripping to the dimensions given in the figure 21 sheet 2. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

c Install : 1 Nut NAS1726-3E Item 5 1 Bolt NAS1303-2 Item 17 1 Washer NAS1149F0332P Item 3 1 Bonding Lead E0088-10-125 Item 7 1 Clamp NSA5519-2B Item 8 - Install the bonding leads with : 1 Screw Item (1) 1 Nut NAS1726-3E Item 5 NOTE : Item (1) was retained at removal. (4) Kit 286064A03R00 (a) Install the bonding points. 1 Remove :

2 Screw Item (206) Retain 2 Washer Item (260) Retain 2 On the blanking plates item (310), do a stripping to the dimension given in the figure 22, sheets 2 and 3. 3 Temporarily install the bonding lead item 10 on the angle item 12. 4 Temporarily install the angle item 12 on the structure as shown in the figure 22, sheets 2 and 3. 5 Drill the structure to match the holes of the angle item 12 at the dimensions given in the figure 22, sheet 3. 6 Install : 2 Angle A9242127720000 Item 12

with 4 Rivet ASNA2050DCJ3215 Item 11 7 Install : 2 Screw Item (206) 2 Washer Item (260) 2 Bonding Lead E0088-10-200 Item 10 2 Nut NAS1726-3E Item 5 2 Bolt NAS1303-3 Item 2 2 Washer NAS1149F0332P Item 3

NOTE : Items (206) and (260) were retained at removal. (5) Wings Fuel Tanks DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

(a) The Tables that follow list all the equipment in the wings fuel tanks that are to be modified for electrical bonding. The work is listed by rib bay. The detailed worksteps for each rib bay is given in para. (6) thru (25) for pre Mod. 12226 aircraft and para. (26) for Post Mod. 12226 aircraft. Paragraph (27) refers to the ADDITIONAL WORK (Introduced by Rev 01) that is necessary if this Service Bulletin has been embodied on aircraft at original issue, which were not Config. 05 aircraft. The worksteps given are for the LH wing. The worksteps for the RH wing are the same unless otherwise stated. TABLE 1 - PRE. MOD. 12226 AIRCRAFT LH AND RH WING APPLICABLE RIB BAY EQUIPMENT TO BE ELECTRICALLY BONDED REFERENCED FIGURES APPLICABLE KIT
Rib Bay 1-2 Water Drain Valves. Water Scavenge Pipes (Config. 03 aircraft). MLI. Fuel Feed Pipe. Low Fuel Pressure Switches. Fuel Booster Pumps. Fuel Booster Pumps (Config. 06 aircraft). Diffuser. Fuel Level sensor. Figure 23, Sheet 1 Figure 24, Sheet 1 Figure 25, Sheet 1 Figure 26, Sheet 1 Figure 27, Sheet 1 Figure 28, Sheet 1 Figure 29, Sheet 2 Figure 30, Sheet 2 Kit B01R05 all aircraft. For Config. 03 aircraft Kit B22R05. For Config. 06 aircraft Kit B23R01.

Rib Bay 2-3 Diffuser. Calibration Sensor (Config. 04 aircraft) Figure 29, Sheet 1 Figure 30, Sheet 1 Kit B01R05 all aircraft. For Config. 04 aircraft Kit B21R01. Rib Bay 5-6 Slat Track Canister 3. Figure 31, Sheet 1, Sheet 2 Kit B03R03 all aircraft and Kit B02R02 or B26R01 for Config. 02 aircraft Rib Bay 8-9 Slat Track Canister 4. MLI. Figure 32, Sheet 1 Figure 31, Sheet 2 Figure 25, Sheet 1 Kit B04R03 all aircraft and Kit B02R02 or B26R01 for Config. 02 aircraft.

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

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# A300-600 **A300-600** SERVICE BULLETIN

LH AND RH WING APPLICABLE RIB BAY EQUIPMENT TO BE ELECTRICALLY BONDED REFERENCED FIGURES APPLICABLE KIT
Rib Bay 9-10 Screwjack Canister 3. Water Drain Valve. Figure 33, Sheet 1, Sheet 2 Figure 23, Sheet 1 Kit B05R01 all aircraft and Kit B02R02 or B26R01 for Config. 02 aircraft. Rib Bay 10-11 Slat Track Canister 5 Figure 34, Sheet 1 Figure 31, Sheet 2 Kit B06R03 all aircraft and Kit B02R02 or B26R01 for Config. 02 aircraft. Rib Bay 11-12 (RH Wing only) Cadensicon. Figure 35, Sheet 1 Kit B07R01 all aircraft. Rib Bay 12-13 Slat Track Canister 6. Figure 36, Sheet 1 Figure 31 Sheet 2 Kit B08R03 all aircraft and Kit B02R02 or B26R01 for Config. 02 aircraft. Rib Bay 13-14 MLI. Refuel/Defuel Valves. Fuel Level Sensor. Overwing Refuel Panel. Figure 25, Sheet 1 Figure 37, Sheet 1 and Sheet 2 Figure 30, Sheet 1 Figure 39, Sheet 1 Kit B09R04 all aircraft.

Rib Bay 14-15 Screwjack Canister 4. Water Drain Valve. Low Fuel Pressure Switches. Fuel Booster Pumps. Provision for Fuel Jettison System - Blanking plate (Config. 07 aircraft). Figure 40, Sheet 1 Figure 33, Sheet 2 Figure 23, Sheet 1, Sheet 2 Figure 27, Sheet 2 and Sheet 2 Figure 41, Sheet 1 Figure 38, Sheet 1 Kit B10R01 all aircraft and Kit B02R02 or B26R01 for Config. 02 aircraft. Kit B25R01 for Config. 07 aircraft.

Rib Bay 15-16 Slat Track Canister 7. Diffuser. Water Drain Valve. Figure 42, Sheet 1 Figure 31, Sheet 2 Figure 29, Sheet 3 Figure 23, Sheet 1 Kit B11R05 all aircraft and Kit B02R02 or B26R01 for Config. 02 aircraft.

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

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

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# A300-600 **A300-600** SERVICE BULLETIN

LH AND RH WING APPLICABLE RIB BAY EQUIPMENT TO BE ELECTRICALLY BONDED REFERENCED FIGURES APPLICABLE KIT
Rib Bay 17-18 Provision for a Fuel Jettison System - Blanking Plates (Config. 07 aircraft). Figure 38, Sheet1 Kit B25R01 for Config. 07 aircraft.
Rib Bay 18-19 Slat Track Canister 8. Figure 43, Sheet 1 Figure 31, Sheet 2 Kit B13R03 all aircraft and Kit B02R02 or B26R01 for Config 01 and Config. 02 aircraft. Rib Bay 20-21 Screwjack Canister 5. MLI Figure 44, Sheet 1 Figure 33, Sheet 2 Figure 25, Sheet 1 Kit B14R02 all aircraft and Kit B02R02 or B26R01 for Config. 02 aircraft. Rib Bay 21-22 Slat Track Canister 9. Figure 45, Sheet 1 Figure 31, Sheet 2 Kit B15R04 all aircraft and Kit B02R02 or B26R01 for Config 01 and Config. 02 aircraft. Rib Bay 24-25 Slat Track Canister 10 Figure 46, Sheet 1 Figure 31, Sheet 2 Kit B16R03 all aircraft and Kit B02R02 or B26R01 for Config. 01 and Config. 02 aircraft. Rib Bay 25-26 Fuel level Sensor Figure 30, Sheet 1 Kit B19R02 all aircraft. Rib Bay 26-27 Screwjack Canister 6. MLI. Overwing Refuel Panel. Figure 47, Sheet 1 Figure 25, Sheet 1 Figure 39, Sheet 1 Kit B17R01 all aircraft and Kit B27R01 or B28R01 for Config. 02 aircraft. Rib Bay 27-28 Slat Track Canister 11. Water Drain. Fuel Overflow Sensor. Overpressure Protector. Figure 48, Sheet 1 Figure 31, Sheet 2 Figure 23, Sheet 1 Figure 30, Sheet 4 Figure 49, Sheet 1 Kit B18R04 all aircraft and Kit B02R02 or B26R01 for Config. 01 and Config. 02 aircraft.

CAUTION : DO NOT USE SELF SEALING NUTS AT ANY OF THE BONDING POINTS.
ADDITIONAL WORK (Introduced by Rev 01) Rib Bay 13-14 Additional Work Refuel/Defuel Valves LH Wing Figure 37, Sheet 1 and Sheet 2 Kit B39R00

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

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# A300-600 **A300-600** SERVICE BULLETIN

TABLE 2 - CONFIG 08 POST Mod. 12226 AIRCRAFT ONLY LH and RH WING - APPLICABLE RIB BAY EQUIPMENT TO BE ELECTRICALLY BONDED REFERENCE FIGURES APPLICABLE KIT
Rib Bay 1-2 Water Drain Valves. Water Scavenge Pipe. MLI. Fuel Feed Pipe Support Bracket. Low Fuel Pressure Switches. Fuel Booster Pumps Canisters. Fuel Diffuser. Low Level Fuel Sensor. Figure 23, Sheet 1 Figure 24, Sheet 2 Figure 25, Sheet 1 Figure 26, Sheet 1 Figure 27, Sheet 1 Figure 28, Sheet 1 Figure 29, Sheet 4 Figure 30, Sheet 3 Kit B20R06

CAUTION : DO NOT USE SELF SEALING NUTS AT ANY OF THE BONDING POINTS. (6) Rib Bay 1-2 Kit 286064B01R05 all aircraft Kit 286064B22R05 Config. 03 aircraft Kit 286064B23R01 Config. 06 aircraft (a) Forward Rib Bay Water Drain Valve Kit 286064B01R05 Refer to Figure 23, Sheet 1, Detail D 1 At the water drain valve, remove: - one nut, Item (20), discard. - one bolt, Item (19), retain. 2 At the base of the water drain valve prepare the bonding area. For the bolt through the wing skin also prepare the countersink. Install: - 1 retained bolt, Item (19). 1 Nut NSA5474-4K7 Item 20 (b) Aft Rib Bay Water Drain Valve Kit 286064B01R05 Refer to Figure 23, Sheet 1, Detail A DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

1 At the water drain valve, remove: - one nut, Item (20), discard. - one bolt, Item (19), retain. 2 At the water drain valve pipe prepare the bonding area and install: 1 Clamp AN742D6 Item 15 1 Lead E0088-41-160 Item 14 1 Bolt NSA5020-3-3 Item 17 1 Nut NSA5474-3K7 Item 16 3 At the base of the water drain valve prepare the bonding area. For the bolt through the wing skin also prepare the countersink. Install: - 1 retained bolt, Item (19). - the other end of bonding lead, Item 14. 1 Nut NSA5474-4K7 Item 20 (c) Water Scavenge Pipe - Config. 03 aircraft Kit 286064B22R05 Refer to Figure 24, Sheet 1 1 At the pipe clamps (Refer to Detail A and Detail C), remove: - five nuts, Item (16), discard. - three bolts, Item (37), discard. - two bolts, Item (82), discard. - three clamps, Item (22), retain. 2 At the water drain-pipe support bracket (Refer to Detail B), remove: - two nuts, Item (16), discard. - one bolt, Item (37), discard. - one bolt, Item (23), discard. - one clamp, Item (22) retain. If the support bracket is attached by rivets, remove one of the rivets and increase the diameter of the hole to 4.826-4-877mm (0.1900-0.1920in.) to allow for the installation of a bolt. 3 On the support bracket and pipe clamp position (refer to Detail B) prepare the bonding area and install: DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

- 1 retained clamp, Item (22). 1 Bolt NAS1303-2 Item 37 1 Bolt NAS1303-8 Item 23 2 Nut NSA5474-3K7 Item 16 4 On the support brackets and pipe clamp positions (refer to Detail A and C) prepare the bonding areas and install: - 3 retained clamps, Item (22). 2 Bolt NSA5480PN3-5 Item 82 3 Bolt NAS1303-2 Item 37 5 Nut NSA5474-3K7 Item 16 (d) MLI Kit 286064B01R05 Refer to Figure 25, Sheet 1, Detail B 1 At the base of the MLI, remove: - one nut, Item (25), discard. - the related bolt, Item (24), retain. 2 Prepare the bonding area and for the bolt that goes through the wing skin, prepare the countersink. Install: - the retained bolt, Item (24) 1 Nut H19200C4 Item 25 (e) Fuel Feed Pipe Support Kit 286064B01R05 Refer to Figure 26, Sheet 1 1 At the fuel pipe support bracket, upper section, remove: - one nut, Item (16), discard. - one bolt, Item (27), discard. 2 At the fuel pipe support bracket, lower section, remove: - one nut, Item (16), discard. - one bolt, Item (77), discard. - one washer, Item (28), if installed, discard. 3 At the fuel pipe support bracket, upper section, prepare the bonding area and install: DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

1 Bolt NSA5041VBV3-4 Item 27 1 Nut NSA5474-3K7 Item 16 4 At the fuel pipe support bracket, lower section, prepare the bonding area and install: 1 Bolt NSA5041VBV3-8 Item 77 1 Nut NSA5474-3K7 Item 16

and if applicable: 1 Washer AN960C10L Item 28 (f) Low Fuel Pressure Switches Kit 286064B01R05 Refer to Figure 27, Sheet 1 1 At each pressure switch attachment to the rear spar, remove: - one nut, Item (16), discard. - one bolt, Item (34), discard. 2 At the two pressure switch pipes prepare the bonding areas and install: 2 Clamp NSA5519-2B Item 35 2 Lead E0088-10-100 Item 38 2 Bolt NAS1303-2 Item 37 2 Nut NSA5474-3K7 Item 16 3 At the two pressure switches attachments to the rear spar prepare the bonding areas and attach the bonding leads, Item 38, with: 2 Bolt NSA5041VBV3-10 Item 34 2 Nut NSA5474-3K7 Item 16 4 Torque tighten the nuts, Item 16, to between 0.34-0.40 mdaN (30-35 lbf.in.). (g) Fuel Booster Pumps Canisters - All Aircraft Kit 286064B01R05 Refer to Figure 28, Sheet 1 1 At each canister flange (at the positions shown in the figure), remove: - two bolts, Item (45), discard. CAUTION : BOLTS THAT GO THROUGH THE FAIRING ARE NOT TO BE USED AS BONDING BOLTS. 2 At the two canister flanges prepare the bonding areas and for the bolts through the wing skin prepare the countersinks only and install: 4 Bolt NSA5022-4-21 Item 45 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

3 At each of the canisters, at the fuel outlet flange (adjacent to the existing bonding lead, refer to Detail C) remove: - one nut (20), discard. - one bolt, Item (43), retain. 4 On the two pressure switch pipes prepare the bonding areas and install: 2 Clamp NSA5519-2B Item 35 2 Lead E0088-41-100 Item 39 2 Bolt NAS1303-2 Item 37 2 Nut NSA5474-3K7 Item 16 5 Torque tighten the bonding lead nuts, Item 16, to between 0.34-0.40 mdaN (30-35 lbf.in.). 6 At the two canisters, adjacent to the existing bonding leads, prepare the bonding areas and attach the bonding leads, Item 39, with: - two retained bolts, Item (43). 2 Nut NSA5474-4K7 Item 20 7 Torque tighten the nuts, Item 20, to between 0.68-0.70 mdaN (60-70 lbf.in.). (h) Fuel Booster Pump Config. 06 aircraft Kit 286064B23R01 Refer to Figure 28, Sheet 1 1 At the rear of the outboard canister, on the canister housing (refer to Detail B), remove: - one bolt, Item (47), retain. - one washer, Item (48), retain. 2 On the canister pipe prepare the bonding area and install: 1 Clamp NSA5519-4B Item 83 1 Lead E0088-10-100 Item 38 1 Bolt NSA5020-3-3 Item 17 1 Nut NSA5474-3K7 Item 16 3 Torque tighten the bonding lead nut, Item 16, to between 0.34-0.40 mdaN (30-35 lbf.in.). 4 Attach the bonding lead, Item 38, to the canister housing with: - one retained bolt, Item (47). - one retained washer, Item (48). DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

(i) Diffuser Kit 286064B01R05 Refer to Figure 29, Sheet 2, Detail B 1 At the diffuser, remove: - one nut, Item (20), discard. - one washer, Item (52), discard. - two bolts, Item (46), discard. - two washers, Item (53), discard. 2 At the support brackets attachment to the structure, remove: - two nuts, Item (49), discard.

or - two nuts, Item (4), discard. NOTE : The bolts that attach the support brackets to the structure are an interference fit through the wing skin and are therefore bonded, do not remove. 3 At the diffuser prepare the bonding areas and install: 2 Bolt NAS1304-3 Item 46 2 Washer AN960PD416 Item 53 1 Washer A2824028520000 Item 52 1 Nut NSA5474-4K7 Item 20 4 At the diffuser support bracket attachments to the structure, prepare the bonding areas around the bolt holes in the brackets only and install: 2 Nut NSA5472-5K7 Item 49

or 2 Nut NSA5472-4K7 Item 4 (j) Fuel Level Sensor Kit 286064B01R05 Refer to Figure 30, Sheet 2, Detail E NOTE : It is not necessary to disconnect the sensor for this modification. 1 At the sensor bracket, remove: - one nut, Item (16), discard - one washer, Item (74), discard. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

- one bolt, Item (17), discard. 2 At the support bracket of the FQI Probe No.2, remove: - one nut, Item (16), discard. - one washer, Item (74), discard. - one bolt (17), discard. 3 At the support bracket, where it is attached to the structure, remove: - one nut, Item (49), discard. NOTE : The bolt that attaches the support bracket to the structure is an interference fit through the wing skin and is therefore bonded, do not remove. 4 At the support bracket, where it is attached to the structure, prepare the bonding area that surrounds the bolt hole and install: 1 Nut NSA5472-5K7 Item 49 5 At the sensor bracket prepare the bonding area and install: 1 Bolt NSA5020-3-3 Item 17 1 Washer AN960KD10L Item 74 1 Nut NSA5474-3K7 Item 16 6 At the support bracket of the FQI Probe No.2 prepare the bonding areas and install: 1 Bolt NSA5020-3-3 Item 17 1 Washer AN960KD10L Item 74 1 Nut NSA5474-3K7 Item 16 (7) Rib Bay 2-3 Kit 286064B01R05 Kit 286064B21R01 (a) Diffuser Kit 286064B01R05 Refer to Figure 29, Sheet 1, Detail A 1 At the diffuser, remove: - two nuts, Item (20), discard. - two washers, Item (52), discard. - one washer, Item (53), (if installed), discard. - two bolts, Item (46), discard. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

2 At the diffuser support brackets attachment to the structure, remove: - two nuts, Item (49), discard.

or - two nuts, Item (4), discard. NOTE : The bolts that attach the support bracket to the structure are an interference fit through the wing skin and are therefore bonded, do not remove. 3 At the diffuser prepare the bonding areas and install: 2 Bolt NAS1304-3 Item 46 2 Washer A2824028520000 Item 52 1 Washer AN960PD416 Item 53 2 Nut NSA5474-4K7 Item 20 4 At each diffuser support bracket, where it is attached to the structure, prepare the bonding area around the bolt hole in the bracket only and install: 2 Nut NSA5472-5K7 Item 49

or 2 Nut NSA5472-4K7 Item 4 (b) Calibration Sensor Config. 04 Aircraft. Kit 286064B21R01 Refer to Figure 30, Sheet 1, Detail C 1 At the sensor bracket, remove: - one nut, Item (16), discard. - one bolt, Item (17), discard. 2 At the support bracket, remove: - one nut, Item (16), discard. - one bolt, Item (77), discard. 3 At the sensor bracket prepare the bonding area and install: 1 Bolt NSA5020-3-3 Item 17 1 Nut NSA5474-3K7 Item 16 4 At the support bracket prepare the bonding area and install: 1 Bolt NSA5041VBV3-8 Item 77 1 Nut NSA5474-3K7 Item 16 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

(8) Rib Bay 5-6 Kit 286064B03R03 All Aircraft Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft (a) Slat Track Canister 3 Kit 286064B03R03 All Aircraft Refer to Figure 31, Sheet 1 1 At one of the canister attachment bracket positions (refer to Detail C), remove: - two nuts, Item (4), discard. - one washer, Item (5), discard. - one bolt, Item (6), discard. - one nut, Item (16), discard. - one bolt, Item (2), discard. retain any packing that you may find. NOTE : The bolts that attach the support bracket to the structure are an interference fit through the wing skin and are therefore bonded, do not remove. 2 At the canister attachment bracket prepare the bonding areas. At the support bracket, where it is attached to the structure, prepare the bonding area around the bolt hole only. Together with any retained packing, install: 1 Bolt NSA5041VBV4-2 Item 6 1 Washer AN960C416L Item 5 2 Nut NSA5472-4K7 Item 4 1 Bolt NSA5020-3-6 Item 2 1 Nut NSA5474-3K7 Item 16 1 Bolt NSA5020-3-2 Item 70

NOTE : If there is no spacer installed with Item 2 then use the alternate bolt, Item 70. (b) Canister Drain Config. 02 Aircraft Kit 286064B02R02 or Kit 286064B26R01 Refer to Figure 31, Sheet 2 1 At the canister drain, remove: - four nuts, Item (4), discard. - four washers, Item (13), discard. - the two piece plate, Item (10), discard. - four bolts, Item (11), retain. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

2 At the canister drain install the one piece plate, LH or RH, as applicable: 1 Plate LH A5715206420000 Item 9

or: 1 Plate RH A5715206420100 Item 10

with: - 3 retained bolts, Item (11). 3 Nut NSA5472-4K7 Item 4 NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the bolt holes diameter in the new plate, Item 9 or 10, to between 7.142-7.193mm (0.2812-0.2832in.) for the second oversize bolts, Item (11). 3 Prepare the bonding area. For the bolt through the wing skin prepare the countersink only. Install: - 1 retained bolt, Item (11). 1* Washer NAS1252-416L Item 13 NOTE : * A second washer can be installed to allow correct installation of bolt (11), if necessary. 1 Nut NSA5472-4K7 Item 4 4 Apply Sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant around the new plate to seal. (9) Rib Bay 8-9 Kit 286064B04R03 All Aircraft Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft (a) Slat Track Canister 4 Kit 286064B04R03 Refer to Figure 32, Sheet 1 1 At one of the canister attachment bracket positions (refer to Detail B), remove: - two nuts, Item (4), discard. - one washer, Item (5), discard. - one bolt, Item (30), discard. - one nut, Item (16), discard. - one bolt, Item (17), discard. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

- one washer, Item (88), discard. retain any packing that you may find. 2 At the canister attachment bracket prepare the bonding areas. NOTE : The bolt attaching the support bracket to the structure is an interference fit in the skin and is therefore bonded, prepare only around the bolt hole in the bracket at this position. Install (together with any retained packing) : 1 Bolt NSA5041VBV4-3 Item 30 1 Washer AN960C416L Item 5 2 Nut NSA5472-4K7 Item 4 1 Bolt NSA5020-3-3 Item 17 1 Nut NSA5474-3K7 Item 16 1 Washer AN960KD10 Item 88 (b) Canister Drain Config. 02 Aircraft Kit 286064B02R02 or Kit 286064B26R01 Refer to Figure 31, Sheet 2 1 At the canister drain remove: - four nuts, Item (4), discard. - four washers, Item (13), discard. - the two piece plate, Item (10), discard. - four bolts, Item (11), retain. 2 At the canister drain install: 1 Plate LH A5715206420000 Item 9

or: 1 Plate RH A5715206420100 Item 10

with: - 3 retained bolts, Item (11). 3 Nut NSA5472-4K7 Item 4 NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the bolt holes diameter in the new plate, Item 9 or 10, to between 7.142-7.193mm (0.2812-0.2832in.) for the second oversize bolts, Item (11). 3 Prepare the bonding area. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (11). 1* Washer NAS1252-416L Item 13 NOTE : * A second washer can be installed to allow correct installation of bolt (11), if necessary. 1 Nut NSA5472-4K7 Item 4 4 Apply Sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant around the new plate to seal. (c) MLI Kit 286064B04R03 Refer to Figure 25, Sheet 1, Detail B 1 At the base of the MLI, remove: - one nut, Item (25), discard. - one bolt, Item (24), retain. 2 Prepare the bonding area. NOTE : For the bolt through the wing skin prepare the countersink. Install: - 1 retained bolt, Item (24). 1 Nut H19200C4 Item 25 (10) Rib Bay 9-10 Kit 286064B05R01 All Aircraft Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft (a) Screwjack Canister 3 Kit 286064B05R01 Refer to Figure 33, Sheet 1 1 At the rib adjacent to the canister flange (refer to Detail B), remove: - one nut, Item (4), discard. - one bolt, Item (3), discard. 2 At the canister flange, remove: - one nut, Item (4), discard. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

- one bolt, Item (19), discard. 3 At the canister flange, prepare the bonding area and install: 1 Lead E0088-40-100 Item 1 1 Bolt ABS0114-4-18 Item 19 1 Washer AN960C416L Item 5 1 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the bolt, Item 19, is installed from the front spar side and the nut is installed inside the fuel tank. This will give easier access at some flanges to torque tighten the nut. 4 At the rib adjacent to the canister flange prepare the bonding area and attach the bonding lead, Item 1, with: 1 Bolt NSA5041VBV4-11 Item 3 1 Nut NSA5472-4K7 Item 4 5 Torque tighten the bonding lead nut, Item 4, to between 0.68-0.79 mdaN (60-70 lbf.in.). 6 At the canister attachment bracket, remove: - two nuts, Item (16), discard. - one bolt, Item (31), discard. - one bolt, Item (7), discard. retain any packing that you may find. 7 At the canister attachment bracket prepare the bonding areas and install (together with any retained packing) : 1 Bolt NAS1303-10 Item 31 1 Bolt NSA5041VBV3-5 Item 7 2 Nut NSA5474-3K7 Item 16 (b) Canister Drain Config. 02 Aircraft Kit 286064B02R02 or Kit 286064B26R01 Refer to Figure 33, Sheet 2, Detail C 1 At the canister drain remove: - four nuts, Item (4), discard. - four washers, Item (13), discard. - the two piece plate, Item 10), discard. - four bolts, Item (11), retain. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

2 At the canister drain install the one piece plate (LH or RH, as applicable) : 1 Plate LH A5715206420000 Item 9

or 1 Plate RH A5715206420100 Item 10

with: - three retained bolts, Item (11). 3 Nut NSA5472-4K7 Item 4 NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the bolt holes diameter in the new plate, Item 9 or 10, to between 7.142-7.193mm (0.2812-0.2832in.) for the second oversize bolts, Item (11). 3 Prepare the bonding area NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (11). 1 Washer NAS1252-416L Item 13 1 Nut NSA5472-4K7 Item 4 4 Apply Sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant around the new plate to seal. (c) Water Drain Valve Kit 286064B05R01 Refer to Figure 23, Sheet 1, Detail C 1 At the base of the water drain valve, remove: - one nut, Item (20), discard. - one bolt, Item (19), retain. 2 At the water drain pipe prepare the bonding area and install: 1 Clamp AN742D6 Item 15 1 Lead E0088-41-160 Item 14 1 Bolt NSA5020-3-3 Item 17 1 Nut NSA5474-3K7 Item 16 3 Torque tighten the bonding lead nut, Item 16 to between 0.34-0.40 mdaN (30-35 lbf.in.). DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

4 At the base of the water drain valve prepare the bonding area NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (19). - the other end of bonding lead, Item 14. 1 Nut NSA5474-4K7 Item 20 (11) Rib Bay 10-11 Kit 286064B06R03 All Aircraft Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft (a) Slat Track Canister 5 Kit 286064B06R03 Refer to Figure 34, Sheet 1 1 At the rib adjacent to the canister flange, remove: - one nut, Item (4), discard. - one bolt, Item (32), discard. 2 At the canister flange, remove: - one nut, Item (4), discard. - one bolt, Item (40), discard. 3 At the canister flange prepare the bonding area and install: 1 Lead E0088-40-100 Item 1 1 Bolt ABS0114-4-16 Item 40 1 Washer AN960C416L Item 5 1 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the bolt, Item 40, is installed from the front spar side and the nut is installed inside the fuel tank. This will give easier access at some flanges to torque tighten the nut. 4 At the rib adjacent to the canister flange prepare the bonding area and attach the bonding lead, Item 1, with: 1 Bolt NSA5041VBV4-9 Item 32 1 Nut NSA5472-4K7 Item 4 5 Torque tighten the bonding lead nut, Item (4), to between 0.68-0.79 mdaN (60-70 lbf.in.). DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

6 At the canister attachment bracket (refer to Detail B), remove: - one nut, Item (4), discard. - one nut, Item (18), discard. - one washer, Item (28), discard. - one bolt, Item (33), discard. - one nut, Item (16), discard. - one bolt, Item (70), discard. retain any packing that you may find. 7 At the canister attachment bracket prepare the bonding areas. NOTE : The bolt attaching the support bracket to the structure is an interference fit in the skin and is therefore bonded, prepare only around the bolt hole in the bracket at this position. Install: 1 Nut NSA5472-4K7 Item 4 1 Bolt NSA5041VBV3-3 Item 33 1 Washer AN960C10L Item 28 1 Nut NSA5472-3K7 Item 18 1 Bolt NSA5020-3-2 Item 70 1 Nut NSA5474-3K7 Item 16 (b) Canister Drain Config. 02 Aircraft Kit 286064B02R02 or Kit 286064B26R01 Refer to Figure 31, Sheet 2 1 At the canister drain, remove: - four nuts, Item (4), discard. - four washers, Item (13), discard. - the two piece plate, Item (10), discard. - four bolts, Item (11), retain. 2 At the canister drain install the one piece plate (LH or RH, as applicable) : 1 Plate LH A5715206420000 Item 9

or: 1 Plate RH A5715206420100 Item 10 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

with: - three retained bolts, Item (11). 3 Nut NSA5472-4K7 Item 4 NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the bolt holes diameter in the new plate, Item 9 or 10, to between 7.142-7.193mm (0.2812-0.2832in.) for the second oversize bolts, Item (11). 3 Prepare the bonding area NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (11). 1* Washer NAS1252-416L Item 13 NOTE : * A second washer can be installed to allow correct installation of bolt (11), if necessary. 1 Nut NSA5472-4K7 Item 4 4 Apply Sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant around the new plate to seal. (12) Rib Bay 11-12 (RH Wing Only) Kit 286064B07R01 All Aircraft (a) Cadensicon Refer to Figure 35, Sheet 1 1 At the mounting plate attachment to the front spar (refer to Detail A and B) remove: - one nut, Item (20), discard. - one bolt (Post. Mod. 04741), Item (55), discard.

or: - one bolt (Pre. Mod. 04741), Item (58), discard. 2 At the cadensicon mounting plate, remove: - one nut, Item (16), discard. - one bolt, Item (56), discard. 3 At the cadensicon pipe prepare the bonding area and install: DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

1 Clamp AN742D8 Item 50 1 Lead E0088-41-100 Item 39 1 Screw NAS1100-3-7 Item 51 1 Nut NSA5474-3K7 Item 16 4 Torque tighten the bonding lead nut, Item 16, to between 0.34-0.40 mdaN (30-35 lbf.in.). 5 At the front spar prepare the bonding area and attach the bonding lead, Item 39, to the front spar with (Post Mod. 04741) : 1 Bolt NAS1304-11 Item 55

or Pre Mod. 04741 : 1 Bolt NAS1304-14 Item 58

with: 1 Nut NSA5474-4K7 Item 20 6 At the cadensicon mounting plate prepare the bonding area and install: 1 Bolt NAS1303-7 Item 56 1 Nut NSA5474-3K7 Item 16 (13) Rib Bay 12-13 Kit 286064B08R03 All Aircraft Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft (a) Slat Track Canister 6 Kit 286064B08R03 Refer to Figure 36, Sheet 1 1 At the rib adjacent to the canister flange, remove: - one nut, Item (4), discard. - one bolt, Item (32), discard. 2 At the canister flange, remove: - one nut, Item (4), discard. - one bolt, Item (44), discard. 3 At the canister flange prepare the bonding area and install: 1 Lead E0088-40-190 Item 89 1 Bolt ABS0114-4-15 Item 44 1 Washer AN960C416L Item 5 1 Nut NSA5472-4K7 Item 4 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the bolt, Item 44, is installed from the front spar side and the nut is installed inside the fuel tank. This will give easier access at some flanges to torque tighten the nut. 4 At the rib adjacent to the canister flange prepare the bonding area and attach the bonding lead, Item 89, with: 1 Bolt NSA5041VBV4-9 Item 32 1 Nut NSA5472-4K7 Item 4 5 Torque tighten the bonding lead nut, Item 4, to between 0.68-0.79 mdaN (60-70 lbf.in.). 6 At the canister attachment bracket, 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. 9 At the canister attachment bracket, remove: - one nut, Item (4), discard. - one nut, Item (16), discard. - one washer, Item (28), discard. - one bolt, Item (41), discard. retain any packing that you may find. 1 0 At the canister attachment bracket prepare the bonding areas. NOTE : The bolt attaching the support bracket to the structure is an interference fit in the skin and is therefore bonded, prepare only around the bolt hole in the bracket at this position. Install: 1 Nut NSA5472-4K7 Item 4 1 Bolt NSA5041VBV3-2 Item 41 1 Washer AN960C10L Item 28 2 Nut NSA5474-3K7 Item 16 1 Bolt NAS1303-1 Item 42 (b) Canister Drain Config. 02 Aircraft Kit 286064B02R02 or Kit 286064B26R01 Refer to Figure 31, Sheet 2 1 At the canister drain, remove: - four nuts, Item (4), discard. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

- four washers, Item (13), discard. - the two piece plate, Item (10), discard. - four bolts, Item (11), retain. 2 At the canister drain install the one piece plate (LH or RH, as applicable) : 1 Plate LH A5715206420000 Item 9

or: 1 Plate RH A5715206420100 Item 10

with: - three retained bolts, Item (11). 3 Nut NSA5472-4K7 Item 4 NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the bolt holes diameter in the new plate, Item 9 or 10, to between 7.142-7.193mm (0.2812-0.2832in.) for the second oversize bolts, Item (11). 3 Prepare the bonding area. NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (11). 1* Washer NAS1252-416L Item 13 NOTE : * A second washer can be installed to allow correct installation of bolt (11), if necessary. 1 Nut NSA5472-4K7 Item 4 4 Apply Sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant around the new plate to seal. (14) Rib Bay 13-14 Kit 286064B09R04 All Aircraft (a) MLI Kit 286064B09R04 Refer to Figure 25, Sheet 1, Detail B 1 At the base of the MLI, remove: - one nut, Item (25), discard. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

- one bolt, Item (24), retain. 2 At the base of the MLI prepare the bonding area. NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (24). 1 Nut H19200C4 Item 25 (b) Refuel/Defuel Valve - All Aircraft Kit 286064B09R04 Refer to Figure 37, Sheet 1, Sheet 2 1 If necessary remove and retain the heat shield. 2 On each valve at the front spar, remove: - one nut, Item (20), discard. NOTE : Remove and discard any bonding lead tags that may be installed under the nuts, Item (20). 3 On the valves prepare the bonding areas and install: 2 Lead E0088-41-304 Item 59 2 Nut NSA5474-4K7 Item 20

NOTE : In some instances the bonding lead may be too short to connect to the fastener shown because of interference from the heat shield. In this case connect the bonding leads to the fasteners that are diagonally opposite. 4 Torque tighten the nuts, Item 20, to between 0.68-0.79 mdaN (60-70 lbf.in.). 5 At the two bonding lead tag positions on the front spar, attach the bonding leads, Item 59, with: 2 Screw NAS1100-3-7 Item 51 2 Nut NSA5474-3K7 Item 16

NOTE : It is Mandatory to put the heat shield in its installation position (if removed) before you attach the bonding leads, Item 59, to the bonding tags, (Refer to Sheet 2) 6 Torque tighten the nuts, Item 16, to between 0.34-0.40 mdaN (30-35 lbf.in.). 7 Complete the installation of the heat shield. (c) High Level Fuel Sensor - All Aircraft Kit 286064B09R04 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

Refer to Figure 30, Sheet 1, Detail B 1 At the sensor bracket, remove: - one nut, Item (16), discard. - one bolt, Item (70), discard. 2 At the support bracket, remove: - one nut, Item (16), discard. - one bolt, Item (17), discard.

or - one bolt, Item (90), discard. 3 At the sensor bracket prepare the bonding area and install: 1 Bolt NSA5020-3-2 Item 70 1 Nut NSA5474-3K7 Item 16 4 At the support bracket prepare the bonding area and install: 1 Nut NSA5474-3K7 Item 16 1 Bolt NSA5020-3-3 Item 17

or 1 Bolt NSA5020-3-5 Item 90

NOTE : If bolt, Item 17, is too short the bolt, item 90, may be used as an alternative. (d) Overwing Refuel Panel No Kit Refer to Figure 39, Sheet 1 and AMM 28-25-21, Page block 401 1 Put protective material or masking tape on the wing skin, around the refuel/defuel panels. 2 At the refuel panels loosen the bolts and lift the panel. 3 Put the panel on the protective material. 4 At the contact surfaces of the panel and the wing skin opening (Refer to the Figure) use abrasive paper grade 1 or Emery cloth, grade 320, to remove any protective coating. Clean the prepared surfaces with Cleaning agent (Mat. No. 11-026). 5 Apply Alodine (Mat. No. 13-002) to the contact surfaces of the panel and the wing skin. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

6 Apply sealant (Mat. No. 09-018) to the contact surface of the wing skin. 7 Align the panel offset bolt and put the panel into the wing skin opening. Make sure that the panel attachment chain is clear of the bolt holes. 8 Tighten the bolts. 9 Remove any unwanted sealant. 1 0 Remove the protective material that you put around the opening. 1 1 If necessary, apply paint to the heads of the bolts and the panel and/or wing skin (Refer to SRM 51-75-10). (15) Rib Bay 14-15 Kit 286064B10R01 All Aircraft Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft Kit 286064B25R01 Config. 07 Aircraft (a) Screwjack Canister 4 Kit 286064B10R01 Refer to Figure 40, Sheet 1 1 At the rib adjacent to the canister flange, remove: - one nut, Item (4), discard. - one bolt, Item (54), discard. 2 At the canister flange, remove: - one nut, Item (4), discard. - one bolt, Item (57), discard. 3 At the canister flange prepare the bonding area and install: 1 Lead E0088-40-100 Item 1 1 Bolt ABS0114-4-14 Item 57 1 Washer AN960C416L Item 5 1 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the bolt, Item 57, is installed from the front spar side and the nut is installed inside the fuel tank. This will give easier access at some flanges to torque tighten the nut. 4 At the rib adjacent to the canister flange prepare the bonding area and attach the bonding lead, Item 1, with: 1 Bolt NSA5041VBV4-7 Item 54 1 Nut NSA5472-4K7 Item 4 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

5 Torque tighten the bonding lead nut, Item 4, to between 0.68-0.79 mdaN (60-70 lbf.in.). 6 At the canister attachment bracket, remove: - one nut, Item (7), discard. - one bolt, Item (18), discard. retain any packing that you may find. 7 At the canister attachment to the structure, remove: - one nut, Item (18), discard. - one bolt, Item (26), discard. retain any packing that you may find. 8 At the canister attachment to the structure prepare the bonding area and install (together with any retained packing) : 1 Bolt NSA5041VBV3-7 Item 26 1 Nut NSA5472-3K7 Item 18 9 At the canister bracket prepare the bonding area and install (together with any retained packing) 1 Bolt NSA5041VBV3-5 Item 7 1 Nut NSA5472-3K7 Item 18 (b) Canister Drain Config. 02 Aircraft Kit 286064B02R02 or Kit 286064B26R01 Refer to Figure 33, Sheet 2 1 At the canister drain, remove: - four nuts, Item (4), discard. - four washers, Item (13), discard. - the two piece plate, Item (10), discard. - four bolts, Item (11), retain. 2 At the canister drain install the one piece plate (LH or RH, as applicable) : 1 Plate LH A5715206420000 Item 9

or: 1 Plate RH A5715206420100 Item 10 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

with: - three retained bolts, Item (11). 3 Nut NSA5472-4K7 Item 4 NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the bolt holes diameter in the new plate, Item 9 or 10, to between 7.142-7.193mm (0.2812-0.2832in.) for the second oversize bolts, Item (11). 3 Prepare the bonding area. NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (11). 1* Washer NAS1252-416L Item 13 NOTE : * A second washer can be installed to allow correct installation of bolt (11), if necessary. 1 Nut NSA5472-4K7 Item 4 4 Apply Sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant around the new plate to seal. (c) Water Drain Valve - All Aircraft Kit 286064B10R01 Refer to Figure 23, Sheet 1, Sheet 2 1 At the water drain pipe (refer to Sheet 2, Detail A) disconnect the bonding lead, Item (84) from the bonding lug, remove: - one nut, Item (80), discard. - one bolt, Item (81), discard. CAUTION : DO NOT REMOVE AND DISCARD ANY OTHER BONDING LEADS FROM RIB 14. 2 At the bonding leads attachment to rib 14 (adjacent to the compensator), remove: - one nut, Item (16), discard. - one bolt, Item (22), retain. - one bonding lead, Item (84), discard. NOTE : If necessary, temporarily remove any other bonding leads to get access to the bonding lead, Item (84) at rib 14. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

3 At the bonding leads attachment to rib 14, install (together with any other bonding leads that you temporarily removed for access) : - one retained bolt, Item (22). 1 Nut NSA5474-3K7 Item 16 4 At the bonding leads attachment to rib 14, apply protective coating over the fastener and the bonding leads terminals (refer to AMM 20-28-11, Page block 1). 5 At the water drain pipe, apply Sealant (Mat. No. 09-001) over the bonding lug. 6 At the base of the water drain valve (refer to Sheet 1 Detail A), remove: - one nut, Item (20), discard. - one bolt, Item (19), retain. 7 At water drain valve-pipe prepare the bonding area and install: 1 Clamp AN742D6 Item 15 1 Lead E0088-41-160 Item 14 1 Bolt NSA5020-3-3 Item 17 1 Nut NSA5474-3K7 Item 16 8 At the base of the water drain valve prepare the bonding area. NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (19). - the other end of the lead, Item 14. 1 Nut NSA5474-4K7 Item 20 9 Torque tighten the bonding lead nut, Item 16, to between 0.34-0.40 mdaN (30-35 lbf.in.). (d) Low Fuel Pressure Switches Kit 286064B10R01 Refer to Figure 27, Sheet 2, Detail D 1 At each pressure switch attachment to the rear spar, remove: - one nut, Item (16), discard. - one bolt, Item (69), discard. 2 At the pressure switches pipes prepare the bonding area and install: 2 Clamp NSA5519-2B Item 35 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

2 Lead E0088-10-100 Item 38 2 Nut NSA5474-3K7 Item 16 2 Bolt NAS1303-2 Item 37 3 At the pressure switches attachment to the rear spar prepare the bonding areas and attach the bonding leads, Item 38, with: 2 Bolt NSA5041VBV3-6 Item 69 2 Nut NSA5474-3K7 Item 16 4 Torque tighten the bonding lead nuts, Item 16, to between 0.34-0.40 mdaN (30-35 lbf.in.). (e) Fuel Booster Pumps Kit 286064B10R01 Refer to Figure 41, Sheet 1 1 At each canister flange, remove from the positions shown in the figure: - two bolts, Item (45), discard. CAUTION : BOLTS THAT GO THROUGH THE FAIRING ARE NOT TO BE USED AS BONDING POINTS. 2 At the canister flanges prepare the bonding areas and for the bolts through the wing skin prepare the countersink only. Install: 4 Bolt NSA5022-4-21 Item 45 3 At each of the fuel pump canisters, adjacent to the existing bonding lead, (refer to Detail C) remove: - one nut, Item (20), discard. - one bolt, Item (43), retain. 4 On the two pressure switches pipes prepare the bonding areas and install: 2 Clamp NSA5519-2B Item 35 2 Lead E0088-41-100 Item 39 2 Bolt NAS1303-2 Item 37 2 Nut NSA5474-3K7 Item 16 5 Torque tighten the bonding lead nuts, Item 16, to between 0.34-0.40 mdaN (30-35 lbf.in.). 6 At the two fuel pump canisters, adjacent to the existing bonding lead, (refer to Detail C) prepare the bonding areas and attach the bonding leads, Item 39, with: - 2 retained bolts, Item (43). DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

2 Nut NSA5474-4K7 Item 20 7 Torque tighten the nuts, Item 20, to between 0.68-0.79 mdaN (60-70 lbf.in.). (f) Fuel Jettison System - Blanking Plates Kit 286064B25R01 Config. 07 Aircraft Refer to Figure 38, Sheet 1, Detail A and B NOTE : Access to rib bays 13-14 and 15-16 is also necessary. 1 At the blanking plate at rib 14 (refer to Detail A), remove: - one nut, Item (20), discard. - one bolt, Item (62), discard. 2 At the blanking plate prepare the bonding area and install: 1 Bolt NSA5041VBV4-6 Item 62 1 Nut NSA5474-4K7 Item 20 3 At the blanking plate at rib 15 (refer to Detail B), remove: - one nut, Item (16), discard. - one bolt, Item (69), discard. 4 At the blanking plate prepare the bonding area and install: 1 Bolt NSA5041VBV3-6 Item 69 1 Nut NSA5474-3K7 Item 16 (16) Rib Bay 15-16 Kit 286064B11R05 All Aircraft Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft (a) Slat Track Canister 7 Kit 286064B11R05 Refer to Figure 42, Sheet 1 1 At the rib adjacent to the canister flange, remove: - one nut, Item (4), discard. - one bolt, Item (29), discard. 2 At the canister flange, remove: - one nut, Item (4), discard. - one bolt, Item (85), discard 3 At the canister flange prepare the bonding area and install: DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

1 Lead E0088-40-100 Item 1 1 Bolt ABS0114-4-13 Item 85 1 Washer AN960C416L Item 5 1 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the bolt, Item 85, is installed from the front spar side and the nut is installed inside the fuel tank. This will give easier access at some flanges to torque tighten the nut. 4 At the rib adjacent to the canister prepare the bonding area and attach the bonding lead, Item 1, with: 1 Bolt NSA5041VBV4-8 Item 29 1 Nut NSA5472-4K7 Item 4 5 Torque tighten the bonding lead nut, Item 4, to between 0.68-0.79 mdaN (60-70 lbf.in.). 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. 9 At the canister attachment bracket position (refer to Detail C), remove: - one nut, Item (4), discard. - one nut, Item (18), discard. - one washer, Item (28), discard. - one bolt, Item (33), discard. retain any packing that you may find. 1 0 At the canister attachment bracket prepare the bonding areas. NOTE : The bolt attaching the support bracket to the structure is an interference fit in the skin and therefore bonded, prepare only around the bolt hole in the bracket at this position. Install: 1 Nut NSA5472-4K7 Item 4 1 Bolt NSA5041VBV3-3 Item 33 1 Washer AN960C10L Item 28 2 Nut NSA5472-3K7 Item 18 1 Bolt NSA5020-3-2 Item 70 (b) Canister Drain Config. 02 Aircraft Kit 286064B02R02 or Kit 286064B26R01 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

Refer to Figure 31, Sheet 2 1 At the canister drain, remove: - four nuts, Item (4), discard. - four washers, Item (13), discard. - the two piece plate, Item (10), discard. - four bolts, Item (11), retain. 2 At the canister drain install the one piece plate (LH or RH, as applicable) : 1 Plate LH A5715206420000 Item 9

or: 1 Plate RH A5715206420100 Item 10

with: - three retained bolts, Item (11). 3 Nut NSA5472-4K7 Item 4 NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the bolt holes diameter in the new plate, Item 9 or 10, to between 7.142-7.193mm (0.2812-0.2832in.) for the second oversize bolts, Item (11). 3 Prepare the bonding area. NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (11). 1* Washer NAS1252-416L Item 13 NOTE : * A second washer can be installed to allow correct installation of bolt (11), if necessary. 1 Nut NSA5472-4K7 Item 4 4 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant around the new plate to seal. (c) Diffuser - All Aircraft Kit 286064B11R05 Refer to Figure 29, Sheet 3 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

1 At the diffuser attachment brackets remove: - two nuts, Item (20), discard. - two washers, Item (52) (if installed), discard. - two bolts, Item (46), discard. - one washer if fitted, Item (53), discard. 2 At the diffuser attachment to the structure, remove: - two nuts, Item (49), discard.

or - two nuts, Item (4), discard. 3 At the diffuser prepare the bonding areas and install: 2 Bolt NAS1304-3 Item 46 2 Washer A2824028520000 Item 52 1 Washer AN960PD416 Item 53 2 Nut NSA5474-4K7 Item 20 4 At the diffuser attachment to the structure prepare the bonding areas and install: NOTE : The bolts attaching the support brackets to the structure are an interference fit in the skin and are therefore bonded, prepare only around the bolt hole in the bracket at this position. 2 Nut NSA5472-5K7 Item 49

or 2 Nut NSA5472-4K7 Item 4 (d) Water Drain Valve - All Aircraft Kit 286064B11R05 Refer to Figure 23, Sheet 1 1 At the base of the water drain valve, (refer to Detail A) remove: - one nut, Item (20), discard. - one bolt, Item (19), retain. 2 At the water drain pipe prepare the bonding area and install: 1 Clamp AN742D6 Item 15 1 Lead E0088-41-160 Item 14 1 Bolt NSA5020-3-3 Item 17 1 Nut NSA5474-3K7 Item 16 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

3 Torque tighten the bonding lead nut, Item 16, to between 0.34-0.40 mdaN (30-35 lbf.in.). 4 At the base of the water drain valve prepare the bonding area. NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (19). - the other end of bonding lead, Item 14. 1 Nut NSA5474-4K7 Item 20 5 Torque tighten the nut, Item 20, to between 0.68-0.79 mdaN (60-70 lbf.in.) (17) Rib Bay 16-17 Kit 286064B12R01 All Aircraft (a) Fuel Level Sensor Refer to Figure 30, Sheet 2, Detail D 1 At the sensor bracket, remove: - one nut, Item (16), discard. - one bolt, Item (70), discard. 2 At the support bracket, remove: - one nut, Item (16), discard. - one bolt, Item (71), discard. 3 at the sensor bracket prepare the bonding area and install: 1 Bolt NSA5020-3-2 Item 70 1 Nut NSA5474-3K7 Item 16 4 At the support bracket prepare the bonding area and install: 1 Bolt NSA5020-3-4 Item 71 1 Nut NSA5474-3K7 Item 16 (18) Rib Bay 17-18 Kit 286064B25R01 Refer to Figure 38, Sheet 1 (a) Fuel Jettison System Blanking Plates 1 At the blanking plates, remove: DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

- one bolt, Item (66), discard. - one bolt, Item (68), discard. - one nut, Item (16), discard. - one nut, Item (20), discard. 2 At the blanking plates prepare the bonding areas and install: 1 Bolt NAS1153-12 Item 66 1 Nut NSA5474-3K7 Item 16 1 Bolt NSA5041VBV4-14 Item 68 1 Nut NSA5474-4K7 Item 20 (19) Rib Bay 18-19 Kit 286064B13R03 All Aircraft Kit 286064B02R02 or Kit 286064B26R01 for Config. 01 and Config. 02 aircraft. (a) Slat Track Canister 8 Kit 286064B13R03 Refer to Figure 43, Sheet 1 1 At the rib adjacent to the canister flange, remove: - one nut, Item (4), discard. - one bolt, Item (29), discard. 2 At the canister flange, remove: - one nut, Item (4), discard. - one bolt, Item (61), discard. 3 At the canister flange prepare the bonding area and install: 1 Lead E0088-40-100 Item 1 1 Bolt ABS0114-4-12 Item 61 1 Washer AN960C416L Item 5 1 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the bolt, Item 61, is installed from the front spar side and the nut is installed inside the fuel tank. This will give easier access at some flanges to torque tighten the nut. 4 At the rib adjacent to the canister flange prepare the bonding area and attach the bonding lead, Item 1, with: 1 Bolt NSA5041VBV4-8 Item 29 1 Nut NSA5472-4K7 Item 4 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

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, 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. 9 At the canister attachment brackets (refer to Detail C) remove: - one nut, Item (4), discard. - one bolt, Item (33), discard. - one washer, Item (28), discard. - one nut, Item (18), discard. - one nut, Item (16), discard. retain any packing that you may find. 1 0 At the canister attachment bracket prepare the bonding areas NOTE : The bolt attaching the support bracket to the structure is an interference fit in the skin and is therefore bonded, prepare only around the bolt hole in the bracket at this position. Install (together with any retained packing) : 1 Nut NSA5472-4K7 Item 4 1 Bolt NAS1303-1 Item 42 1 Nut NSA5474-3K7 Item 16 1 Bolt NSA5041VBV3-3 Item 33 1 Washer AN960C10L Item 28 1 Nut NSA5472-3K7 Item 18 (b) Canister Drain Config. 01 and Config. 02 aircraft. Kit 286064B02R02 or Kit 286064B26R01 Refer to Figure 31, Sheet 2 1 At the canister drain, remove: - four nuts, Item (4), discard. - four washers, Item (13), discard. - the two piece plate, Item (10), discard. - four bolts, Item (11), retain.

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

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# A300-600 **A300-600** SERVICE BULLETIN

2 At the canister drain install the one piece plate (Item 9 LH or Item 10 RH, as applicable) : 1 Plate LH A5715206420000 Item 9

or: 1 Plate RH A5715206420100 Item 10

with: - three retained bolts, Item (11). 3 Nut NSA5472-4K7 Item 4 NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the bolt holes diameter in the new plate, Item 9 or 10, to between 7.142-7.193mm (0.2812-0.2832in.) for the second oversize bolts, Item (11). 3 Prepare the bonding area. NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (11). 1* Washer NAS1252-416L Item 13 NOTE : * A second washer can be installed to allow correct installation of bolt (11), if necessary. 1 Nut NSA5472-4K7 Item 4 4 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant around the new plate to seal. (20) Rib Bay 20-21 Kit 286064B14R02 All Aircraft Kit 286064B02R02 or Kit 286064B26R01 Config. 02 Aircraft (a) Screwjack Canister 5 Kit 286064B14R02 Refer to Figure 44, Sheet 1 1 At the rib adjacent to the canister flange, remove: - one nut, Item (4), discard. - one bolt, Item (54), discard. 2 At the canister flange, remove: DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

- one nut, Item (4), discard. - one bolt, Item (63), discard. 3 At the canister flange prepare the bonding area and install: 1 Lead E0088-40-100 Item 1 1 Bolt ABS0114-4-10 Item 63 1 Washer AN960C416L Item 5 1 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the bolt, Item 63, is installed from the front spar side and the nut is installed inside the fuel tank. This will give easier access at some flanges to torque tighten the nut. 4 At the rib adjacent to the canister flange prepare the bonding area and attach the bonding lead, Item 1, with: 1 Bolt NSA5041VBV4-7 Item 54 1 Nut NSA5472-4K7 Item 4 5 At the canister attachment bracket, remove: - one nut, Item (4), discard. - one bolt, Item (12), discard. 6 At the bracket attachment to the structure, remove: - one nut, Item (16), discard. - one bolt, Item (69), discard. 7 At the canister attachment bracket prepare the bonding area and install: 1 Bolt NSA5041VBV4-5 Item 12 1 Nut NSA5472-4K7 Item 4 8 At the bracket attachment to the structure prepare the bonding area and install: 1 Bolt NSA5041VBV3-6 Item 69 1 Nut NSA5474-3K7 Item 16 (b) Canister Drain Config. 02 Aircraft Kit 286064B02R02 or Kit 286064B26R01 Refer to Figure 33, Sheet 2 1 At the canister drain, remove: - four nuts, Item (4), discard. - four washers, Item (13), discard. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

- the two piece plate, Item (10), discard. - four bolts, Item (11), retain. 2 At the canister drain install the one piece plate (Item 9 LH or Item 10 RH, as applicable) : 1 Plate LH A5715206420000 Item 9

or: 1 Plate RH A5715206420100 Item 10

with: - three retained bolts, Item (11). 3 Nut NSA5472-4K7 Item 4

NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the bolt holes diameter in the new plate, Item 9 or 10, to between 7.142-7.193mm (0.2812-0.2832in.) for the second oversize bolts, Item (11). 3 Prepare the bonding area. NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (11). 1* Washer NAS1252-416L Item 13 NOTE : * A second washer can be installed to allow correct installation of bolt (11), if necessary. 1 Nut NSA5472-4K7 Item 4 4 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant around the new plate to seal. (c) MLI - All Aircraft Kit 286064B14R02 Refer to Figure 25, Sheet 1, Detail B 1 At the base of the MLI, remove: - one nut, Item (25), discard. - one bolt, Item (24), retain. 2 At the base of the MLI prepare the bonding area. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (24). 1 Nut H19200C4 Item 25 (21) Rib Bay 21-22 Kit 286064B15R04 All Aircraft Kit 286064B02R02 or Kit 286064B26R01 for Config. 01 and Config. 02 aircraft. (a) Slat Track Canister 9 Kit 286064B15R04 Refer to Figure 45, Sheet 1 1 At the rib adjacent to the canister flange, remove: - one nut, Item (64), discard. - one bolt, Item (12), discard. 2 At the canister flange, remove: - one nut, Item (64), discard. - one bolt, Item (86), discard. 3 At the canister flange prepare the bonding area and install: 1 Lead E0088-40-100 Item 1 1 Bolt ABS0114-4-9 Item 86 1 Washer AN960C416L Item 5 1 Nut NSA5475-4K7 Item 64

NOTE : The washer, Item 5, is only necessary under the nut, Item 64, if the bolt, Item 86, is installed from the front spar side and the nut is installed inside the fuel tank. This will give easier access at some flanges to torque tighten the nut. 4 At the rib adjacent to the canister flange prepare the bonding area and attach the bonding lead, Item 1, with: 1 Bolt NSA5041VBV4-5 Item 12 1 Nut NSA5475-4K7 Item 64 5 Torque tighten the bonding lead nut, Item 2, to between 0.68-0.79 mdaN (60-70 lbf.in.). 6 At the inboard canister attachment bracket position (refer to Detail C), remove: - one nut, Item (4), discard. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

- two nuts, Item (16), discard. - one bolt, Item (41), discard. - one bolt, Item (42), discard. - one washer, Item (28), discard. retain any packing that you may find. 7 At the canister attachment bracket prepare the bonding areas. NOTE : The bolt attaching the support bracket to the structure is an interference fit in the skin and is therefore bonded, prepare only around the bolt hole in the bracket at this position. Install (together with any retained packing) : 1 Nut NSA5472-4K7 Item 4 1 Bolt NAS1303-1 Item 42 2 Nut NSA5474-3K7 Item 16 1 Bolt NSA5041VBV3-2 Item 41 1 Washer AN960C10L Item 28 (b) Canister Drain Config. 01 and Config. 02 Aircraft. Kit 286064B02R02 or Kit 286064B26R01 Refer to Figure 31, Sheet 2 1 At the canister drain, remove: - four nuts, Item (4), discard. - four washers, Item (13), discard. - the two piece plate, Item (10), discard. - four bolts, Item (11), retain. 2 At the canister drain install the plate (Item 9 LH or Item 10 RH, as applicable) : 1 Plate LH A5715206420000 Item 9

or: 1 Plate RH A5715206420100 Item 10

with: - three retained bolts, Item (11). 3 Nut NSA5472-4K7 Item 4

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

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# A300-600 **A300-600** SERVICE BULLETIN

NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the bolt holes diameter in the new plate, Item 9 or 10, to between 7.142-7.193mm (0.2812-0.2832in.) for the second oversize bolts, Item (11). 3 Prepare the bonding area. NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (11). 1* Washer NAS1252-416L Item 13 NOTE : * A second washer can be installed to allow correct installation of bolt (11), if necessary. 1 Nut NSA5472-4K7 Item 4 4 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant around the new plate to seal. (22) Rib Bay 24-25 Kit 286064B16R03 All Aircraft Kit 286064B02R02 or Kit 286064B26R01 for Config. 01 and Config. 02 Aircraft. (a) Slat Track Canister 10 Kit 286064B16R03 Refer to Figure 46, Sheet 1 1 At the rib adjacent to the canister flange, remove: - one nut, Item (64), discard. - one bolt, Item (62), discard. 2 At the canister flange, remove: - one nut, Item (64), discard. - one bolt, Item (91), discard. 3 At the canister flange prepare the bonding area and install: 1 Lead E0088-40-100 Item 1 1 Bolt ABS0114-4-6 Item 91 1 Washer AN960C416L Item 5 1 Nut NSA5475-4K7 Item 64

NOTE : The washer, Item 5, is only necessary under the nut, Item 64, if the bolt, Item 91, is installed from the front spar side and the nut is DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

installed inside the fuel tank. This will give easier access at some flanges to torque tighten the nut. 4 At the rib adjacent to the canister flange prepare the bonding area and attach the bonding lead, Item 1, with: 1 Bolt NSA5041VBV4-6 Item 62 1 Nut NSA5475-4K7 Item 64 5 Torque tighten the bonding lead nut, Item 2, to between 0.68-0.79 mdaN (60-70 lbf.in.). 6 At the canister attachment bracket (refer to Detail A), remove: - two nuts, Item (16), discard. - one washer, Item (28), discard. - one bolt, Item (27), discard. - one washer, Item (87), discard. - one bolt, Item (7), discard. retain any packing that you may find. 7 At the canister attachment bracket prepare the bonding areas and install (together with any retained packing) : 1 Bolt NSA5041VBV3-5 Item 7 1 Washer DHS1085-4 Item 87 1 Bolt NSA5041VBV3-4 Item 27 1 Washer AN960C10L Item 28 2 Nut NSA5474-3K7 Item 16 (b) Canister Drain, Config. 01 and Config. 02 Aircraft. Kit 286064B02R02 or Kit 286064B26R01 Refer to Figure 31, Sheet 2 1 At the canister drain, remove: - four nuts, Item (4), discard. - four washers, Item (13), discard. - the two piece plate, Item (10), discard. - four bolts, Item (11), retain. 2 At the canister drain install the plate (Item 9 LH or Item 10 RH, as applicable) : 1 Plate LH A5715206420000 Item 9 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

or: 1 Plate RH A5715206420100 Item 10

with: - three retained bolts, Item (11). 3 Nut NSA5472-4K7 Item 4 NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the bolt hole diameter in the new plate item 9 or 10, to between 7.142-7.193mm (0.2812-0.2832in) for the second oversize bolts, Item (11). 3 Prepare the bonding area. NOTE : For the bolt through the skin prepare the countersink only. Install: - one retained bolt, Item (11). 1* Washer NAS1252-416L Item 13 NOTE : * A second washer can be installed to allow correct installation of bolt (11), if necessary. 1 Nut NSA5472-4K7 Item 4 4 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant around the new plate to seal. (23) Rib Bay 25-26 Kit 286064B19R02 - All Aircraft (a) Fuel Level Sensor Refer to Figure 30, Sheet 1, Detail A 1 At the sensor bracket, remove: - one bolt, Item (71), discard. 2 At the support bracket, remove: - one nut, Item (16), discard. - one bolt, Item (17), discard. 3 At the sensor bracket prepare the bonding area and install: 1 Bolt NSA5020-3-4 Item 71 4 At the support bracket prepare the bonding area and install: DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

1 Bolt NSA5020-3-3 Item 17 1 Nut NSA5474-3K7 Item 16 (24) Rib Bay 26-27 Kit 286064B17R01 All Aircraft Kit 286064B27R01 or Kit 286064B28R01 Config. 02 Aircraft (a) Screwjack Canister 6 Kit 286064B17R01 Refer to Figure 47, Sheet 1. 1 At the rib adjacent to the canister flange, remove: - one nut, Item (4), discard. - one bolt, Item (12), discard. 2 At the canister flange, remove: - one nut, Item (4), discard. - one bolt, Item (67), discard. 3 At the canister flange prepare the bonding area and install: 1 Lead E0088-40-100 Item 1 1 Bolt ABS0114-4-5 Item 67 1 Washer AN960C416L Item 5 1 Nut NSA5472-4K7 Item 4

NOTE : The washer, Item 5, is only necessary under the nut, Item 4, if the bolt, Item 67, is installed from the front spar side and the nut is installed inside the fuel tank. This will give easier access at some flanges to torque tighten the nut. 4 At the rib adjacent to the canister flange prepare the bonding area and attach the bonding lead, Item 1, with: 1 Bolt NSA5041VBV4-5 Item 12 1 Nut NSA5472-4K7 Item 4 5 Torque tighten the bonding lead nut, Item 4, to between 0.68-0.79 mdaN (60-70 lbf.in.). 6 At the canister attachment bracket (refer to Detail A), remove - one nut, Item (18), discard. - one washer, Item (28), discard. - one bolt, Item (72), discard. retain any packing that you may find. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

7 At the canister attachment bracket prepare the bonding area and install: 1 Bolt ABS0114-3-6 Item 72 1 Washer AN960C10L Item 28 1 Nut NSA5472-3K7 Item 18 (b) Canister Drain Config. 02 Aircraft Kit 286064B27R01 (LH) or Kit 286064B28R01 (RH) Refer to Figure 47, Sheet 2 1 At the canister drain remove: - four nuts, Item (4), discard. - the two piece plate, Item (10), discard. - four bolts, Item (12), discard. - packing, Item (6), retain. 2 At the drain spacer, Item (7) attachment to the wing skin, remove: - one nut, Item (4), discard. - one bolt, Item (5), retain. 3 At the drain spacer, Item (7) attachment to the wing skin prepare the bonding area. NOTE : For the bolt through the wing skin prepare the countersink only. Install: - 1 retained bolt, Item (5). 1 Nut NSA5472-4K7 Item 4 4 At the canister drain install the plate (Item 9 LH or Item 10 RH, as applicable) : 1 Plate LH A5715206420000 Item 9

or: 1 Plate RH A5715206420100 Item 10

with: - retained packing, Item (6) 3 Bolt NSA5041VBV4-5 Item 12 3 Nut NSA5472-4K7 Item 4 5 Prepare the bonding area and install: DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

1 Bolt NSA5041VBV4-5 Item 12 1* Washer NAS1252-416L Item 13 NOTE : * A second washer can be installed to allow correct installation of bolt 12, if necessary. 1 Nut NSA5472-4K7 Item 4 6 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant around the new plate to seal, Also repair any sealant on the bottom flange of the spacer, Item (7). (c) MLI Kit 286064B17R01 Refer to Figure 25, Sheet 1, Detail A 1 At the attachment of the MLI No.6 to the manhole cover, remove: - seven nuts, Item (16), discard. - seven bolts, Item (22), retain. - the protective support tube, retain. 2 At the base of the MLI, remove: - one nut, Item (20), discard. - one bolt, Item (24), retain. 3 At the base of the MLI prepare the bonding area and install: - one retained bolt, Item (24). 1 Nut NSA5474-4K7 Item 20 4 Put the protective tube in position over the MLI and install: - six retained bolts, Item (22). 6 Nut NSA5474-3K7 Item 16 5 Prepare the bonding area. NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (22). 1 Nut NSA5474-3K7 Item 16 (d) Overwing Refuel Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

No Kit Refer to Figure 39 and AMM 28-25-21, Page block 401 1 Put protective material or masking tape on the wing skin, around the refuel/defuel panels. 2 At the refuel panels loosen the bolts and lift the panel. 3 Put the panel on the protective material. 4 At the contact surfaces of the panel and the wing skin opening (Refer to the Figure) use abrasive paper grade 1 or Emery cloth, grade 320, to remove any protective coating. Clean the prepared surfaces with Cleaning agent (Mat. No. 11-026). 5 Apply Alodine (Mat. No. 13-002) to the contact surfaces of the panel and the wing skin. 6 Apply sealant (Mat. No. 09-018) to the contact surface of the wing skin. 7 Align the panel offset bolt and put the panel into the wing skin opening. Make sure that the panel attachment chain is clear of the bolt holes. 8 Tighten the bolts. 9 Remove any unwanted sealant. 1 0 Remove the protective material that you put around the opening. 1 1 If necessary, apply paint to the heads of the bolts and the panel and/or wing skin (Refer to SRM 51-75-10). (25) Rib Bay 27-28 Kit 286064B18R04 All Aircraft Kit 286064B02R02 or Kit 286064B26R01 for Config. 01 and Config. 02 Aircraft. (a) Slat Track Canister 11 Kit 286064B18R04 Refer to Figure 48, Sheet 1 1 At the rib adjacent to the canister flange, remove: - one nut, Item (64), discard. - one bolt, Item (78), discard. 2 At the canister flange, remove: - one nut, Item (64), discard. - one bolt, Item (79), discard. 3 At the canister flange prepare the bonding area and install: DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

1 Lead E0088-40-100 Item 1 1 Bolt ABS0114-4-4 Item 79 1 Washer AN960C416L Item 5 1 Nut NSA5475-4K7 Item 64

NOTE : The washer, Item 5, is only necessary under the nut, Item 64, if the bolt, Item 79, is installed from the front spar side and the nut is installed inside the fuel tank. This will give easier access at some flanges to torque tighten the nut. 4 At the rib adjacent to the canister flange prepare the bonding area and attach the bonding lead, Item 1, with: 1 Bolt NSA5041VBV4-4 Item 78 1 Nut NSA5475-4K7 Item 64 5 Torque tighten the bonding lead nut, Item 2, to between 0.68-0.79 mdaN (60-70 lbf.in.). 6 At the canister attachment bracket, remove: - one nut, Item (16), discard. - one washer, Item (87), discard. - one bolt, Item (7), discard. 7 At the bracket attachment to the structure, remove: - one nut, Item (16), discard. - one washer, Item (65), discard. - one bolt, Item (7), discard. retain any packing that you may find. 8 At the bracket attachment to the structure prepare the bonding area and install (together with any retained packing) : 1 Bolt NSA5041VBV3-5 Item 7 1 Washer DHS783-63-18 Item 65 1 Nut NSA5474-3K7 Item 16 9 At the canister attachment bracket prepare the bonding area and install: 1 Bolt NSA5041VBV3-5 Item 7 1 Washer DHS1085-4 Item 87 1 Nut NSA5474-3K7 Item 16 (b) Canister Drain, Config. 01 and Config. 02 Aircraft. Kit 286064B02R02 or Kit 286064B26R01 Refer to Figure 31, Sheet 2 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

1 At the canister drain, remove: - four nuts, Item (4), discard. - four washers, Item (13), discard. - the two piece plate, Item (10), discard. - four bolts, Item (11), retain. 2 At the canister drain install the plate (Item 9 LH or Item 10 RH, as applicable) : 1 Plate LH A5715206420000 Item 9

or: 1 Plate RH A5715206420100 Item 10

with: - three retained bolts, Item (11). 3 Nut NSA5472-4K7 Item 4 NOTE : If Service Bulletin A300-57-6026 has been embodied, increase the bolt holes diameter in the new plate, Item 9 or 10, to between 7.142-7.193mm (0.2812-0.2832in.) for the second oversize bolts, Item (11). 3 Prepare the bonding area. NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (11). 1* Washer NAS1252-416L Item 13 NOTE : * A second washer can be installed to allow correct installation of bolt (11), if necessary. 1 Nut NSA5472-4K7 Item 4 4 Apply sealant (Mat. No. 09-001) over the three nuts and a fillet of sealant around the new plate to seal. (c) Water Drain Kit 286064B18R04 Refer to Figure 23, Sheet 1, Detail B 1 At the water drain, remove: DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

- one nut, Item (20), discard. - one bolt, Item (19), retain. 2 At the water drain prepare the bonding area and install: - one retained bolt, Item (19). 1 Nut NSA5474-4K7 Item 20 (d) Fuel Overflow Sensor Kit 286064B18R04 Refer to Figure 30, Sheet 4 NOTE : Access to Rib Bay 26-27 is also necessary. 1 At the sensor bracket, remove: - one nut, Item (16), discard. - one bolt, Item (7), discard. 2 At the sensor bracket prepare the bonding area and install: 1 Bolt NSA5041VBV3-5 Item 7 1 Nut NSA5474-3K7 Item 16 (e) Overpressure Protector Kit 286064B18R04 Refer to Figure 49, Sheet 1 1 At the flange of the overpressure protector, remove: - two bolts, Item (30), discard. 2 Prepare the bonding areas and install: 2 Bolt NAS1304-4 Item 30 (26) Wings Fuel Tank Equipment - Rib Bay 1-2 Config. 08 Aircraft Kit 286064B20R06 (a) Forward Rib Bay Water Drain Valve Refer to Figure 23, Sheet 1, Detail D 1 At the water drain valve, remove: - one nut, Item (20), discard. - one bolt, Item (19), retain. 2 At the base of the water drain valve prepare the bonding area. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

NOTE : For the bolt through the wing skin prepare the countersink only. Install: - 1 retained bolt, Item (19). 1 Nut NSA5474-4K7 Item 20 (b) Aft Rib Bay Water Drain Valve. Refer to Figure 23, Sheet 1, Detail A 1 At the water drain valve, remove: - one nut, Item (20), discard. - one bolt, Item (19), retain. 2 At the water drain valve pipe prepare the bonding area and install: 1 Clamp AN742D6 Item 15 1 Lead E0088-41-160 Item 14 1 Bolt NSA5020-3-3 Item 17 1 Nut NSA5474-3K7 Item 16 3 At the base of the water drain valve prepare the bonding area. NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (19) - the other end of the lead, Item 14. 1 Nut NSA5474-4K7 Item 20 (c) Water Scavenge Pipe. Refer to Figure 24, Sheet 2 1 At the support bracket and pipe clamp positions (Refer to Detail A, Detail B and Detail C) remove: - Four nuts, Item (16), discard. - Four bolts, Item (37), discard. - Four clamps, Item (22), retain. 2 On the support brackets and pipe clamp positions, (refer to Detail A, Detail B and C) , prepare the bonding areas and install: - four retained clamps, Item (22) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

4 Bolt NAS1303-2 Item 37 4 Nut NSA5474-3K7 Item 16 (d) MLI Refer to Figure 25, Sheet 1, Detail B 1 At the base of the MLI, remove: - one nut, Item (25), discard. - one bolt, Item (24), retain. 2 At the base of the MLI prepare the bonding area. NOTE : For the bolt through the wing skin prepare the countersink only. Install: - one retained bolt, Item (24). 1 Nut H19200C4 Item 25 (e) Fuel Feed Pipe Support Refer to Figure 26, Sheet 1 1 At the fuel pipe support bracket, upper section, remove: - one nut, Item (16), discard. - one bolt, Item (27), discard. 2 At the fuel pipe support bracket, lower section, remove: - one nut, Item (16), discard. - one bolt, Item (77), discard. - one washer, Item (28), if installed, discard. 3 At the fuel pipe support bracket, upper section, prepare the bonding area and install: 1 Bolt NSA5041VBV3-4 Item 27 1 Nut NSA5474-3K7 Item 16 4 At the fuel pipe support bracket, lower section, prepare the bonding area and install: 1 Bolt NSA5041VBV3-8 Item 77 1 Nut NSA5474-3K7 Item 16

and, if applicable : DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

1 Washer AN960C10L Item 28 (f) Low Fuel Pressure Switches Refer to Figure 27, Sheet 1 1 At each pressure switch attachment to the rear spar, remove: - one nut, Item (16), discard. - one bolt, Item (34), discard. 2 At the two pressure switch pipes prepare the bonding areas and install: 2 Clamp NSA5519-2B Item 35 2 Lead E0088-10-100 Item 38 2 Bolt NAS1303-2 Item 37 2 Nut NSA5474-3K7 Item 16 3 At the two pressure switch attachments to the rear spar prepare the bonding areas and attach the bonding leads, Item 38, with: 2 Bolt NSA5041VBV3-10 Item 34 2 Nut NSA5474-3K7 Item 16 4 Torque tighten the bonding lead nuts, Item 16, to between 0.34-0.40 mdaN (30-35 lbf.in.). (g) Fuel Booster Pump Canisters Refer to Figure 28, Sheet 1 1 At each canister flange, remove from the positions shown in the figure: - two bolts, Item (45), discard. CAUTION : BOLTS THAT GO THROUGH THE FAIRING ARE NOT TO BE USED AS BONDING POINTS. 2 At the two canister flanges prepare the bonding areas. NOTE : For the bolts through the wing skin prepare the countersinks only. Install: 4 Bolt NSA5022-4-21 Item 45 3 At each of the fuel pump canisters, adjacent to the existing bonding lead, (refer to Detail C) remove: - one nut, Item (20), discard. - one bolt, Item (43), retain. 4 On the two pressure switches pipes prepare the bonding areas and install: DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

2 Clamp NSA5519-2B Item 35 2 Lead E0088-41-100 Item 39 2 Bolt NAS1303-2 Item 37 2 Nut NSA5474-3K7 Item 16 5 Torque tighten the bonding leads nuts, Item 16, to between 0.34-0.40 mdaN (30-35 lbf.in.). 6 At each of the fuel pump canisters, adjacent to the existing bonding lead, (refer to Detail C) prepare the bonding areas and attach the bonding leads, Item 39, with: - one retained bolts, Item (43). 2 Nut NSA5474-4K7 Item 20 7 Torque tighten the nut, Item 20 to between 0.68-0.70 mdaN (60-70 lbf.in.). (h) Diffuser Refer to Figure 29, Sheet 4, Detail B 1 At the diffuser, remove: - one nut, Item (20), discard. - one washer, Item (52), discard. - two bolts, Item (46), discard. - two washers, Item (53), discard. 2 At the diffuser prepare the bonding areas and install: 2 Bolt NAS1304-3 Item 46 2 Washer AN960PD416 Item 53 1 Washer A2824028520000 Item 52 1 Nut NSA5474-4K7 Item 20 (i) Low Level Fuel Sensor Refer to Figure 30, Sheet 3, Detail E NOTE : It is not necessary to disconnect the sensor for this modification. 1 At the sensor bracket, remove: - one nut, Item (16), discard - one washer, Item (74), discard. - one bolt, Item (17), discard. 2 At the support bracket of the FQI Probe No.2, remove: - one nut, Item (16), discard. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

- one washer, Item (74), discard. - one bolt, Item (17), discard. 3 At the sensor bracket prepare the bonding area and install: 1 Bolt NSA5020-3-3 Item 17 1 Washer AN960KD10L Item 74 1 Nut NSA5474-3K7 Item 16 4 At the support bracket of the FQI Probe No.2 prepare the bonding areas and install: 1 Bolt NSA5020-3-3 Item 17 1 Washer AN960KD10L Item 74 1 Nut NSA5474-3K7 Item 16 (27) ADDITIONAL WORK on the LH wing tank (Introduced by Rev 01) This additional work is necessary if this Service Bulletin, at the original issue, has been embodied on aircraft which were not Config. 05 aircraft. (a) Refuel/Defuel Valve LH Wing - Rib Bay 13-14 Kit 286064B39R00 Refer to Figure 37, Sheet 1, Sheet 2 1 Get access to Rib Bay 13-14 refer to para 3.A (1) Preparation. 2 If necessary remove and retain the heat shield. 3 On each valve at the front spar, remove: - one nut, Item (20), discard. NOTE : Remove and discard any bonding lead tags that may be installed under the nuts, Item (20). 4 On the valves prepare the bonding areas and install: 2 Lead E0088-41-304 Item 59 2 Nut NSA5474-4K7 Item 20 5 Torque tighten the nuts, Item 20, to between 0.68-0.79 mdaN (60-70 lbf.in.). 6 At the two bonding lead tag positions on the front spar, attach the bonding leads, Item 59, with: 2 Screw NAS1100-3-7 Item 51 2 Nut NSA5474-3K7 Item 16

NOTE : It is Mandatory to put the heat shield in its installation position (if removed) before you attach the bonding leads, Item 59, to the bonding tags, (Refer to Sheet 2). DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

7 Torque tighten the nuts, Item 16, to between 0.34-0.40 mdaN (30-35 lbf.in.). 8 Complete the installation of the heat shield. (28) ADDITIONAL WORK 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, (Refer to AMM 20-28-11, Page block 001). - If the ohmic resistance <10mhm, apply the blue coat. - If the ohmic resistance >10mhm, do the bonding (Refer to AMM 20-28-11, Page block 001). 1 Check the bonding points Item 25 on the rib 1 (LH side). Refer to Figure 50, Sheet 1, (General location) Refer to Figure 51, Sheets 1 and 2, (Detailed location) Refer to Figure 52, Sheet 1, (Result table) (29) ADDITIONAL WORK on the center tank (For Config 03 aircraft using Kit A03 only) (Introduced by Rev 04) (a) Install the bonding points. 1 Remove :

2 Screw Item (206) Retain 2 Washer Item (260) Retain 2 On the blanking plates item (310), do a stripping to the dimension given in the figure 22, sheets 2 and 3. 3 Temporarily install the bonding lead item 10 on the angle item 12. 4 Temporarily install the angle item 12 on the structure as shown in the figure 22, sheets 2 and 3. 5 Drill the structure to match the holes of the angle item 12 at the dimensions given in the figure 22, sheet 3. 6 Install : DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

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 10 2 Nut NAS1726-3E Item 5 2 Bolt NAS1303-3 Item 2 2 Washer NAS1149F0332P Item 3 NOTE : Items (206) and (260) were retained at removal. (30) ADDITIONAL WORK on the wings tanks (For Config. 07 aircraft only) (Introduced by Rev 04) (a) Fuel Jettison System - Blanking Plates Kit 286064B25R01 Config. 07 Aircraft Refer to Figure 38, Sheet 1, Detail A and B NOTE : Access to rib bays 13-14 and 15-16 is also necessary. 1 At the blanking plate at rib 14 (refer to Detail A), remove: - one nut, Item (20), discard. - one bolt, Item (62), discard. 2 At the blanking plate prepare the bonding area and install: 1 Bolt NSA5041VBV4-6 Item 62 1 Nut NSA5474-4K7 Item 20 3 At the blanking plate at rib 15 (refer to Detail B), remove: - one nut, Item (16), discard. - one bolt, Item (69), discard. 4 At the blanking plate prepare the bonding area and install: 1 Bolt NSA5041VBV3-6 Item 69 1 Nut NSA5474-3K7 Item 16 (b) Config. 07 Rib Bay 17-18 Kit 286064B25R01 Refer to Figure 38, Sheet 1 1 Get access to Rib Bay 17-18 refer to para 3.A (1) Preparation. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

2 Fuel Jettison System Blanking Plates

a At the blanking plates, remove: - one bolt, Item (66), discard. - one bolt, Item (68), discard. - one nut, Item (16), discard. - one nut, Item (20), discard. b At the blanking plates prepare the bonding areas and install: 1 Bolt NAS1153-12 Item 66 1 Nut NSA5474-3K7 Item 16 1 Bolt NSA5041VBV4-14 Item 68 1 Nut NSA5474-4K7 Item 20 **C. T E**  **S T**  (1) Wings Fuel Tanks (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 AMM 20-28-11, Page block 001 (b) Preliminary Tests: 1 Initial conditions

a On each connectors that you disconnected, do a visual check as defined by ESPM 20-51-10 to make sure that. - The label of the plug is the same as the label on the receptacle. - The plug is correctly locked. 2 Do the Functional Test of the Instrument and Panel Integral Lighting (Refer to AMM 33-13-00, Page block 501). 3 Do the Operational Test of the Annunciator Light Test (Refer to AMM 33-14-00, Page block 501). 4 Do the Operational Test of the Quantity Indicating System (Refer to AMM 28-42-00, Page block 501). 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, do a leak test of the wings fuel tanks (Refer to AMM 28-11-00, Page block 501). DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

NOTE : Fuel leaks are not permitted. (2) Center Tank (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 AMM 20-28-11, Page block 001 (b) Preliminary Tests: 1 Initial conditions

a On each connectors that you disconnected, do a visual check as defined by ESPM 20-51-10 to make sure that. - The label of the plug is the same as the label on the receptacle. - The plug is correctly locked. 2 Do the Functional Test of the Instrument and Panel Integral Lighting (Refer to AMM 33-13-00, Page block 501). 3 Do the Operational Test of the Annunciator Light Test (Refer to AMM 33-14-00, Page block 501). 4 Do the Operational Test of the Quantity Indicating System (Refer to AMM 28-42-00, Page block 501). 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, do a 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) (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 AMM 20-28-11, Page block 001 (b) After the worksteps in para. D. CLOSE UP, (2) (a) thru (f) have been completed, do a leak test of the wings fuel tanks (Refer to AMM 28-11-00, Page block 501). (c) Preliminary Tests: 1 Initial conditions

a On each connectors that you disconnected, do a visual check as defined by ESPM 20-51-10 to make sure that. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

- The label of the plug is the same as the label on the receptacle. - The plug is correctly locked. 2 Do the Functional Test of the Instrument and Panel Integral Lighting (Refer to AMM 33-13-00, Page block 501). 3 Do the Operational Test of the Annunciator Light Test (Refer to AMM 33-14-00, Page block 501). 4 Do the Operational (BITE) test after the reconnection of plugs 1076VC and 2022VC (Refer to AMM 28-42-00, Page block 501). (4) ADDITIONAL WORK on the center tank (Introduced by Rev 03) (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 AMM 20-28-11, Page block 001 (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 defined by ESPM 20-51-10 to make sure that. . The label of the plug is the same as the label on the receptacle. . The plug is correctly locked. b Do the Functional Test of the Instrument and Panel Integral Lighting (Refer to AMM 33-13-00, Page block 501).

c Do the Operational Test of the Annunciator Light Test (Refer to AMM 33-14-00, Page block 501). (5) ADDITIONAL WORK on the center tank (For Config. 03 aircraft using Kit A03 only) (Introduced by Rev 04) (a) Do a check of the electrical bonding (Refer to AMM 20-28-11, Page block 001). DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

NOTE : For maximum permissible resistance values : Refer to the table AMM 20-28-11, Page block 001 (b) After the worksteps in para. D. CLOSE UP, (6) (a) have been completed, do a leak test of the center fuel tanks (Refer to AMM 28-11-00, Page block 501). 1 Preliminary Tests:

a Initial conditions - On each connectors that you disconnected, do a visual check as defined by ESPM 20-51-10 to make sure that. . The label of the plug is the same as the label on the receptacle. . The plug is correctly locked. b Do the Functional Test of the Instrument and Panel Integral Lighting (Refer to AMM 33-13-00, Page block 501).

c Do the Operational Test of the Annunciator Light Test (Refer to AMM 33-14-00, Page block 501). (6) ADDITIONAL WORK on the wing tanks (For Config. 07 aircraft only) (Introduced by Rev 04) (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 AMM 20-28-11, Page block 001 (b) After the worksteps in para. D. CLOSE UP, (6) (a) have been completed, do a leak test of the wings fuel tanks (Refer to AMM 28-11-00, Page block 501). 1 Preliminary Tests:

a Initial conditions - On each connectors that you disconnected, do a visual check as defined by ESPM 20-51-10 to make sure that. . The label of the plug is the same as the label on the receptacle. . The plug is correctly locked. b Do the Functional Test of the Instrument and Panel Integral Lighting (Refer to AMM 33-13-00, Page block 501).

c Do the Operational Test of the Annunciator Light Test (Refer to AMM 33-14-00, Page block 501). **D. C L**  **O S**  **E U**  **P** (1) Center Fuel Tank DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

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# A300-600 **A300-600** SERVICE BULLETIN

(a) Make sure that the work areas are clean and clear of tools and other items of equipment. (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 CLOSED BEFORE YOU REMOVE THE SAFETY CLIPS, TAGS AND CLOSE THE CIRCUIT BREAKERS.For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPIT DESIGN) is embodied. PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/XFR VALVE 2QU P55 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

or PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL/R OUTR & L INR & CTR L 2QJ 208/B27 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/XFR VALVE 2QU P55 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61 For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPIT DESIGN) is not embodied. PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL/L OUTR & R INR & CTR R 1QJ 208/B26 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 125 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL OUTR & L INR & CTR L 2QJ 208/B27 128VU FUEL/FUELING HI LVL 6QJ 805/L87 128VU FUEL/FUELING OVERFLOW 5QJ 805/L86 128VU FUEL/FUELING/TRANSFER VALVE 2QU P55 128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83 128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84 128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85 (g) Remove the access platforms. (h) Restore the systems and the aircraft to normal operating condition. (2) Wings Fuel Tanks (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the heat shields (Refer to AMM 57-23-11, Page block 401). (c) Install the wings fuel tanks manhole covers and access doors/panels (Refer to AMM 28-11-22, Page block 401 and AMM 28-11-29, Page block 401). (d) Remove all the warning notices. (e) Close the Main Landing Gear (MLG) doors (Refer to AMM 32-12-11, Page block 301). (f) Refuel the center fuel tank and wing fuel tanks (Refer to AMM 28-25-00, Page block 301). (g) Remove the safety clips and tags and close these circuit breakers : WARNING : IF OTHER TANKS HAVE BEEN OPENED ENSURE ALL TANKS ARE CLOSED BEFORE YOU REMOVE THE SAFETY CLIPS, TAGS AND CLOSE THE CIRCUIT BREAKERS. PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 321/P56 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

or

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

REVISION No. : 05 - Sep 27/10 Page : 126 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 128VU FUEL/FUELING HI LVL 6QJ 805/L87 128VU FUEL/FUELING OVERFLOW AND CAL 5QJ 805/L86 128VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 805/L88 128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83 128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84 128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85 (h) Remove the access platforms. (i) Put the aircraft and the systems in a normal operating condition. (3) ADDITIONAL WORK on the LH wing tank (Introduced by Rev 01) (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the heat shields (Refer to AMM 57-23-11, Page block 401). (c) Install the wings fuel tanks manhole covers and access doors/panels (Refer to AMM 28-11-22, Page block 401 and AMM 28-11-29, Page block 401). (d) Refuel the wings fuel tanks (Refer to AMM 28-25-00, Page block 1). (e) Remove the safety clips and tags and close these circuit breakers : WARNING : IF OTHER TANKS HAVE BEEN OPENED ENSURE ALL TANKS ARE CLOSED BEFORE YOU REMOVE THE SAFETY CLIPS, TAGS AND CLOSE THE CIRCUIT BREAKERS. PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 321/P56 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

or PANEL DESIGNATION FIN LOCATION

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

REVISION No. : 05 - Sep 27/10 Page : 127 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 128VU FUEL/FUELING HI LVL 6QJ 805/L87 128VU FUEL/FUELING OVERFLOW AND CAL 5QJ 805/L86 128VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 805/L88 128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83 128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84 128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85 (f) Remove the access platforms. (g) Put the aircraft and the systems in a normal operating condition. (4) ADDITIONAL WORK on the center tank (Introduced by Rev 03) (a) Close-up 1 Make sure that the work areas are clean and clear of tools and other items of equipment. 2 Remove all the warning notices. 3 Close the Main Landing Gear (MLG) doors (Refer to AMM 32-12-11, Page block 301). 4 Remove the safety clips and tags and close these circuit breakers: WARNING : IF OTHER TANKS HAVE BEEN OPENED ENSURE ALL TANKS ARE CLOSED BEFORE YOU REMOVE THE SAFETY CLIPS, TAGS AND CLOSE THE CIRCUIT BREAKERS.Depending on aircraft configuration PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 321/P56 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

or PANEL DESIGNATION FIN LOCATION

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

REVISION No. : 05 - Sep 27/10 Page : 128 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 128VU FUEL/FUELING HI LVL 6QJ 805/L87 128VU FUEL/FUELING OVERFLOW AND CAL 5QJ 805/L86 128VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 805/L88 128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83 128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84 128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85 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 by Rev 04) (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the heat shields (Refer to AMM 57-23-11, Page block 401). (c) Install the wings fuel tanks manhole covers and access doors/panels (Refer to AMM 28-11-22, Page block 401 and AMM 28-11-29, Page block 401). (d) Remove the safety clips and tags and close these circuit breakers: CAUTION : IF OTHER TANKS HAVE BEEN OPENED ENSURE ALL TANKS ARE CLOSED BEFORE YOU REMOVE THE SAFETY CLIPS, TAGS AND CLOSE THE CIRCUIT BREAKERS.Depending on aircraft configuration PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 321/P56 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

or PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26

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

REVISION No. : 05 - Sep 27/10 Page : 129 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 128VU FUEL/FUELING HI LVL 6QJ 805/L87 128VU FUEL/FUELING OVERFLOW AND CAL 5QJ 805/L86 128VU FUEL/FUELING/CTL & REFUEL VALVE 1QU 805/L88 128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83 128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84 128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85 (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 items of equipment. 2 Install wing manhole covers as necessary (Refer to AMM 28-11-22, Page block 401). 3 Remove all the warning notices. 4 Remove the safety clips and tags and close these circuit breakers: For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPIT DESIGN) is embodied. PANEL DESIGNATION FIN LOCATION 22VU FUEL/TK LO LVL AND CAL/L OUTR & R INR & CTR R 1QJ 208/B26 22VU FUEL/TK LO LVL AND CAL/R OUTR & L INR & CTR L 2QJ 208/B27 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/XFR VALVE 2QU P55 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61

or PANEL DESIGNATION FIN LOCATION

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

REVISION No. : 05 - Sep 27/10 Page : 130 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION 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 132VU FUEL/FUELING HI LVL 6QJ 321/P57 132VU FUEL/FUELING OVERFLOW AND CAL 5QJ 321/P58 132VU FUEL/FUELING/XFR VALVE 2QU P55 132VU FUEL/FQI/SUPPLY AND IND 1QT 321/P59 132VU FUEL/FQI/CHAN SUPPLY 1 3QT 321/P60 132VU FUEL/FQI/CHAN SUPPLY 2 4QT 321/P61 For Aircraft on which Modification No. 04803S5726 (MODIFY COCKPIT DESIGN) is not embodied. PANEL DESIGNATION FIN LOCATION 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 128VU FUEL/FUELING HI LVL 6QJ 805/L87 128VU FUEL/FUELING OVERFLOW 5QJ 805/L86 128VU FUEL/FUELING/TRANSFER VALVE 2QU P55 128VU FUEL/FQI/SUPPLY AND IND 1QT 805/L83 128VU FUEL/FQI/CHAN SUPPLY 1 3QT 805/L84 128VU FUEL/FQI/CHAN SUPPLY 2 4QT 805/L85 5 Remove the access platforms. 6 Retract the slats (Refer to AMM 27-80-00, Page block 301). 7 Restore the systems and the aircraft to normal operating condition. **E. D O**  **C U**  **M E**  **N T**  **A**

**T I**  **O N**  Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

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

REVISION No. : 05 - Sep 27/10 Page : 131 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

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

REVISION No. : 05 - Sep 27/10 Page : 132 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 2, Sheet 1 Location of the Bonding Points at FR44 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 133 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 2, Sheet 2 Location of the Bonding Points at FR44 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 134 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 2, Sheet 3 Location of the Bonding Points at FR44 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 135 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 2, Sheet 4 Location of the Bonding Points at FR44 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 136 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 2, Sheet 5 Location of the Bonding Points at FR44 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 137 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 2, Sheet 6 Location of the Bonding Points at FR44 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 138 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 3, Sheet 1 Bonding Points to Check at FR44

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

REVISION No. : 05 - Sep 27/10 Page : 139 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 1 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 140 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 2 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 141 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 3 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 142 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 4 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 143 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 5 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 144 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 6 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 145 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 7 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 146 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 8 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 147 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 9 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 148 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 10 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 149 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 11 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 150 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 12 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 151 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 13 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 152 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 14 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 153 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 15 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 154 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 16 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 155 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 4, Sheet 17 Location of the Bonding Points at FR47 DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 156 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 5, Sheet 1 Bonding Points to Check at FR47

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

REVISION No. : 05 - Sep 27/10 Page : 157 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 6, Sheet 1 Location of the Bonding Points on the Rib 1 (LH side) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 158 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 6, Sheet 2 Location of the Bonding Points on the Rib 1 (LH side) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 159 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 6, Sheet 3 Location of the Bonding Points on the Rib 1 (LH side) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 160 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 7, Sheet 1 Bonding Points to check on the Rib 1 (LH side) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 161 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 8, Sheet 1 Location of the Bonding Points on the Intrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 162 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 8, Sheet 2 Location of the Bonding Points on the Intrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 163 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 8, Sheet 3 Location of the Bonding Points on the Intrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 164 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 8, Sheet 4 Location of the Bonding Points on the Intrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 165 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 8, Sheet 5 Location of the Bonding Points on the Intrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 166 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 8, Sheet 6 Location of the Bonding Points on the Intrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 167 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 8, Sheet 7 Location of the Bonding Points on the Intrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 168 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 8, Sheet 8 Location of the Bonding Points on the Intrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 169 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 8, Sheet 9 Location of the Bonding Points on the Intrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 170 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 8, Sheet 10 Location of the Bonding Points on the Intrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 171 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 9, Sheet 1 Bonding Points to check on the Intrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 172 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 10, Sheet 1 Location of the Bonding Points on the Rib 1 (RH side) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 173 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 10, Sheet 2 Location of the Bonding Points on the Rib 1 (RH side) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 174 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 10, Sheet 3 Location of the Bonding Points on the Rib 1 (RH side) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 175 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 10, Sheet 4 Location of the Bonding Points on the Rib 1 (RH side) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 176 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 10, Sheet 5 Location of the Bonding Points on the Rib 1 (RH side) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 177 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 10, Sheet 6 Location of the Bonding Points on the Rib 1 (RH side) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 178 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 11, Sheet 1 Bonding Points to check on the Rib 1 (RH side) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 179 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 12, Sheet 1 Location of the Bonding Points on the Extrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 180 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 12, Sheet 2 Location of the Bonding Points on the Extrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 181 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 12, Sheet 3 Location of the Bonding Points on the Extrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 182 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 12, Sheet 4 Location of the Bonding Points on the Extrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 183 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 12, Sheet 5 Location of the Bonding Points on the Extrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 184 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 12, Sheet 6 Location of the Bonding Points on the Extrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 185 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 12, Sheet 7 Location of the Bonding Points on the Extrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 186 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 12, Sheet 8 Location of the Bonding Points on the Extrados Panel DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 187 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

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

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

REVISION No. : 05 - Sep 27/10 Page : 188 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 14, Sheet 1 Modification of the Refueling Pipes on LH side between FR44 and FR47 (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 189 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 14, Sheet 2 Modification of the Refueling Pipes on LH side between FR44 and FR47 (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 190 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 14, Sheet 3 Modification of the Refueling Pipes on LH side between FR44 and FR47 (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 191 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 15, Sheet 1 Modification of the TTS pipes (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 192 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 15, Sheet 2 Modification of the TTS pipes (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 193 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 15, Sheet 3 Modification of the TTS pipes (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 194 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 15, Sheet 4 Modification of the TTS pipes (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 195 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 15, Sheet 5 Modification of the TTS pipes (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 196 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 15, Sheet 6 Modification of the TTS pipes (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 197 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 15, Sheet 7 Modification of the TTS pipes (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 198 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 15, Sheet 8 Modification of the TTS pipes (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 199 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 16, Sheet 1 Modification of the Feed Pipes (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 200 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 16, Sheet 2 Modification of the Feed Pipes (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 201 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 16, Sheet 3 Modification of the Feed Pipes (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 202 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 17, Sheet 1 Modification of the Cross Feed Pipe (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 203 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 17, Sheet 2 Modification of the Cross Feed Pipe (Kit 286064A01R05) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 204 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 18, Sheet 1 Modification of the Refueling Pipes on LH side between FR44 and FR47 (Kit 286064A02R02) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 205 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 18, Sheet 2 Modification of the Refueling Pipes on LH side between FR44 and FR47 (Kit 286064A02R02) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 206 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 18, Sheet 3 Modification of the Refueling Pipes on LH side between FR44 and FR47 (Kit 286064A02R02) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 207 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 19, Sheet 1 Modification of the TTS pipes (Kit 286064A02R02) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 208 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 19, Sheet 2 Modification of the TTS pipes (Kit 286064A02R02) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 209 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 19, Sheet 3 Modification of the TTS pipes (Kit 286064A02R02) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 210 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 19, Sheet 4 Modification of the TTS pipes (Kit 286064A02R02) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 211 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 19, Sheet 5 Modification of the TTS pipes (Kit 286064A02R02) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 212 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 19, Sheet 6 Modification of the TTS pipes (Kit 286064A02R02) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 213 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 19, Sheet 7 Modification of the TTS pipes (Kit 286064A02R02) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 214 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 19, Sheet 8 Modification of the TTS pipes (Kit 286064A02R02) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 215 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 20, Sheet 1 Modification of the Feed Pipes (Kit 286064A02R02)

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

REVISION No. : 05 - Sep 27/10 Page : 216 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 20, Sheet 2 Modification of the Feed Pipes (Kit 286064A02R02)

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

REVISION No. : 05 - Sep 27/10 Page : 217 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 20, Sheet 3 Modification of the Feed Pipes (Kit 286064A02R02)

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

REVISION No. : 05 - Sep 27/10 Page : 218 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 21, Sheet 1 Modification of the Cross Feed Pipe (Kit 286064A02R02)

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

REVISION No. : 05 - Sep 27/10 Page : 219 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 21, Sheet 2 Modification of the Cross Feed Pipe (Kit 286064A02R02)

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

REVISION No. : 05 - Sep 27/10 Page : 220 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

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

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

REVISION No. : 05 - Sep 27/10 Page : 221 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 22, Sheet 2 Electrical Bonding of the Canister Pumps (Kit 286064A03R00)

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

REVISION No. : 05 - Sep 27/10 Page : 222 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 22, Sheet 3 Electrical Bonding of the Canister Pumps (Kit 286064A03R00)

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

REVISION No. : 05 - Sep 27/10 Page : 223 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

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

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

REVISION No. : 05 - Sep 27/10 Page : 224 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 23, Sheet 2 Water Drains and Water Drain Valves Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 225 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 24, Sheet 1 Water Scavenge Pipes Electrical Bonding

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

REVISION No. : 05 - Sep 27/10 Page : 226 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 24, Sheet 2 Water Scavenge Pipes Electrical Bonding

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

REVISION No. : 05 - Sep 27/10 Page : 227 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 25, Sheet 1 Magnetic Level Indicators Electrical Bonding

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

REVISION No. : 05 - Sep 27/10 Page : 228 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

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

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

REVISION No. : 05 - Sep 27/10 Page : 229 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

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

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

REVISION No. : 05 - Sep 27/10 Page : 230 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

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

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

REVISION No. : 05 - Sep 27/10 Page : 231 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

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

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

REVISION No. : 05 - Sep 27/10 Page : 232 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 29, Sheet 1 Fuel Diffusers - Inner and Outer Tanks Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 233 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 29, Sheet 2 Fuel Diffusers - Inner and Outer Tanks Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 234 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 29, Sheet 3 Fuel Diffusers - Inner and Outer Tanks Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 235 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 29, Sheet 4 Fuel Diffusers - Inner and Outer Tanks Electrical Bonding

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

REVISION No. : 05 - Sep 27/10 Page : 236 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 30, Sheet 1 Wings - Fuel Level Sensors Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 237 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 30, Sheet 2 Wings - Fuel Level Sensors Electrical Bonding

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

REVISION No. : 05 - Sep 27/10 Page : 238 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 30, Sheet 3 Wings - Fuel Level Sensors Electrical Bonding

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

REVISION No. : 05 - Sep 27/10 Page : 239 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 30, Sheet 4 Wings - Fuel Level Sensors Electrical Bonding

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

REVISION No. : 05 - Sep 27/10 Page : 240 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 31, Sheet 1 Slat Track Canister 3 and Typical Canister Drain Attachment Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 241 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 31, Sheet 2 Slat Track Canister 3 and Typical Canister Drain Attachment Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 242 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 32, Sheet 1 Slat Track Canister 4 Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 243 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 33, Sheet 1 Screwjack Canister 3 and Typical Canister Drain Attachment Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 244 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 33, Sheet 2 Screwjack Canister 3 and Typical Canister Drain Attachment Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 245 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 34, Sheet 1 Slat Track Canister 5 Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 246 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

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

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

REVISION No. : 05 - Sep 27/10 Page : 247 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 36, Sheet 1 Slat Track Canister 6 Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 248 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 37, Sheet 1 Refuel/Defuel Valves Electrical Bonding

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

REVISION No. : 05 - Sep 27/10 Page : 249 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 37, Sheet 2 Refuel/Defuel Valves Electrical Bonding

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

REVISION No. : 05 - Sep 27/10 Page : 250 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

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

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

REVISION No. : 05 - Sep 27/10 Page : 251 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

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

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

REVISION No. : 05 - Sep 27/10 Page : 252 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 40, Sheet 1 Screwjack Canister 4 Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 253 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

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

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

REVISION No. : 05 - Sep 27/10 Page : 254 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 42, Sheet 1 Slat Track Canister 7 Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 255 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 43, Sheet 1 Slat Track Canister 8 Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 256 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 44, Sheet 1 Screwjack Canister 5 Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 257 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 45, Sheet 1 Slat Track Canister 9 Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 258 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 46, Sheet 1 Slat Track Canister 10 Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 259 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 47, Sheet 1 Screwjack Canister 6 Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 260 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 47, Sheet 2 Screwjack Canister 6 Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 261 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 48, Sheet 1 Slat Track Canister 11 Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 262 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 49, Sheet 1 Overpressure Protector Electrical Bonding DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 263 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 50, Sheet 1 Decomposition of the Center Tank (Additional work, Introduced by Rev 03) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 264 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 51, Sheet 1 Location of the Bonding Points on the Rib 1 (LH side) (Additional work, Introduced by Rev 03) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 265 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 51, Sheet 2 Location of the Bonding Points on the Rib 1 (LH side) (Additional work, Introduced by Rev 03) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 266 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

Figure 52, Sheet 1 Bonding Points to check on the Rib 1 (LH side) (Additional work, Introduced by Rev 03) DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 267 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN

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

REVISION No. : 05 - Sep 27/10 Page : 268 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN REPORTING SHEET

**TITLE : FUEL - GENERAL - MODIFY THE EQUIPMENT IN THE FUEL TANKS FOR ADDITIONAL ELECTRICAL BONDING**  **MODIFICATION No. :** 12495H5555 P l e ase co m p l ete t h e a p p ro p r i ate i te m (A o r B) : A - SB W I L L B E embodied .................................................................. YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiement:

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............................................................................................................................... .............................................. B - SB H AS B E E N embodied on aircraft: ............................................................................................................

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

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

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

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

. K of t h i s S B ) : If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either : Advance data................................................................................... YES/NO Or : Intermediate/Temporary revision ..................................................... YES/NO I m p o rta n t I n fo r m at i o n : This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - updating of maintenance documentation to show pre and post SB data. - updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. P l e as e ret u r n t h i s co m p l ete d s h e et to : **AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  Attn: SEDCC1 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com Or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

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

REVISION No. : 05 - Sep 27/10 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reserved

# A300-600 **A300-600** SERVICE BULLETIN REPORTING QUALITY

**TITLE : FUEL - GENERAL - MODIFY THE EQUIPMENT IN THE FUEL TANKS FOR ADDITIONAL ELECTRICAL BONDING**  **MODIFICATION No. :** 12495H5555 Use this form to tell us what is your perception of the quality of this Service Bulletin.The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to futher improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) -Quality rating of this SB 4 3 2 1 -Quality rating of the Accomplishment Instructions 4 3 2 1 -Quality rating of the Illustrations 4 3 2 1 -Is this SB easy to understand ? Y / N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue.

Planning Material Instructions X Effectivity X Kit Content X Preparation X Reason X List of Materials X Mod/Inspection X Manpower Operator Supplied X Test X References X Re-identification X Close-up X Publication X Tooling X Illustrations C o m m e n ts :

Operator : Date: Name/Title : Please return this form to: **AIRBUS CUSTOMER SERVICES DIRECTORATE**  **1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE**  Attn: SEMB Service Bulletins Management FAX: (+33) 5 61 93 42 51 Or via your Resident Customer Support Office. DATE : Jul 28/05 SERVICE BULLETIN No. : A300-28-6064

REVISION No. : 05 - Sep 27/10 Page : 1 of 1 Printed in France © AIRBUS 2008 All rights reserved