# Airbus Service Bulletin A300-57-6049 Copy: Revision 07 ("U.S. DOT/FAA - Service Bulletin A300-57-6049 Revision 07"), 89 pages: PDF https://openairdocs.org/files/sha256/b6/c5/b6c590234fb5a44f1374db6f21e5af89462107d208bd68f7254be4cb031a2dfd; text https://openairdocs.org/service-documents/airbus/a300-57-6049/file/b6c590234fb5.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2013-1064; AD 2014-20-18 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md) - Type: Service bulletin (Service Bulletin) - Number: A300-57-6049 - Latest revision known: A300-57-6049, Revision 8, dated July 4, 2017 (OpenAirDocs) - Page: https://openairdocs.org/service-documents/airbus/a300-57-6049 ## ADs that cite it (5) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2018-19-18](https://openairdocs.org/ad/2018-19-18.md), effective Nov 7, 2018: Revision 8 - [AD 2014-20-18](https://openairdocs.org/ad/2014-20-18.md), effective Dec 11, 2014: Revisions 06 and 07 - [AD 2005-23-08](https://openairdocs.org/ad/2005-23-08.md), effective Dec 19, 2005: Revision 06 - [AD 2002-11-04](https://openairdocs.org/ad/2002-11-04.md), effective Jul 8, 2002: Revision 4 - [AD 97-16-06](https://openairdocs.org/ad/97-16-06.md), effective Sep 5, 1997: No revision named Also cited in [5 proposed ADs](https://openairdocs.org/service-documents/airbus/a300-57-6049/proposed.md), [7 difficulty reports](https://openairdocs.org/service-documents/airbus/a300-57-6049/reports.md). ## Text (89 pages) Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2013-1064; AD 2014-20-18 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 @ A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET 5 DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : 1 of 3 Printed in FRANCE © AIRBUS, 2006 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 MANDATORY MANDATORY MANDATORY ATA SYSTEM : 57 TITLE : WINGS-SECTION 21-INSPECTION OF HOLES "H"AND "I" OF THE CORNER ANGLE FITTING. MODIFICATION No. : None This page transmits Revision No. 07 of Service Bulletin No. A300-57-6049. ADDITIONAL WORK No additional work is required by this revision for aircraft modified by any previous issue. REASON Accomplishment of Service Bulletin No. A300-57-6069 cancels the requirement of inspection of holes H and I of the corner angle fitting defined in this Service Bulletin and cancels the requirement of inspection of the rear spar and bottom panel at junction with fuselage defined in Service Bulletin No. A300-57-6086. CHANGES SUMMARY : — REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES . Sentence Concerning the Airworthiness Directive (Consigne de Navigabilite) deleted. Sentence added. In the EVALUATION TABLE, Airworthiness Directive number deleted. — EFFECTIVITY . Operators updated. PLANNING INFORMATION : — EFFECTIVITY . 1.A. Effectivity updated. — REASON ### Page 2 @ A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved . 1.C. Sentence concerning the Airworthiness Directive (Consigne de Navigabilite) deleted. Sentence added. — COMPLIANCE . 1.E. Sentence concerning the Airworthiness Directive updated. — APPROVAL . 1.F. Sentence updated. — REFERENCES . 1.J. Reference to Service Bulletins No. A300-57-6069 and A300-57-6086 added. Reference to Airworthiness Directive No. 2000-533-328(B) deleted. MATERIAL INFORMATION : — MATERIAL - PRICE AND AVAILABILITY . 2.A. Address updated. ACCOMPLISHMENT INSTRUCTIONS : — GENERAL . 3.A. Warning updated. FILING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS This is only applicable for Revision No. 05 and subsequent. If information is required for Revisions issued previous to this, please check your copies of Revision Transmittal Sheets or contact AIRBUS. Revision No. 05 issued to create a Kit A08 valid for A/C post Service Bulletin No. A300-57-6050. Fasteners length updated to match fasteners of Service Bulletin No. A300-57-6050. Fastener hole H added in Kit A07. Revision No. 06 issued to update the thresholds and intervals, to inform the operators that the Airworthiness Directive/Consigne de Navigabilite No. 1999-147-279 becomes No. 2000-533-328(B), the Para. EFFECTIVITY is updated and new inspection of holes U, V, W, X, Y for configurations No. 01, 02 and 03 added. This Service Bulletin has been entirely re-written, in order to have an easier understanding of the inspection to be carried out. 2 ### Page 3 @ A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved REVISION SEQUENCE ORIGINAL : Sep 09/94 REVISION No. : 01 — Sep 08/95 REVISION No. : 02 — Jul 25/96 REVISION No. : 03 — Dec 15/98 REVISION No. : 04 — Jul 27/00 REVISION No. : 05 — Sep 14/01 REVISION No. : 06 — Jul 15/04 REVISION No. : 07 — Dec 22/06 3 ### Page 4 @ A300-600 SERVICE BULLETIN SUMMARY 5 DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : 1 of 4 Printed in FRANCE © AIRBUS, 2006 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft MANDATORY MANDATORY MANDATORY ATA SYSTEM : 57 TITLE : WINGS-SECTION 21-INSPECTION OF HOLES "H"AND "I" OF THE CORNER ANGLE FITTING. MODIFICATION No. : None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES Cracks have been found on A300 B2/B4 fleet at about 20,000 flights on FR47 forward fitting at the level of last fastener of external angle fitting. Cracks if undetected can increase in magnitude in rear spar and panel, thus reducing the residual strength capacity of the structure and requiring and extensive structural repair. The in-service experience from the application of inspection on the A300 and A300-600 fleets shows that: — Cracks have been found before reaching the threshold. — Cracks have been found in other holes (basically holes H and I were inspected) during accomplishment of modification Service Bulletins No. A300-53-0298 and A300-57-6050. Revision No.03 of this Service Bulletin takes this new data into account. From Revision No.03 of this SB, further in service experience have shown that cracks have been found in other holes than holes H, I, K, L, M and N. This is why Revision No.06 request to inspect new holes U, V, W, X and Y in order to take these new findings into account. The aim of this Service Bulletin is to call for eddy current inspection of holes H, I, K, L, M, N and U, V, W, X, Y in LH and RH internal angles of wing center box. This inspection will make it possible to detect crack propagation at an early stage, thus avoiding an extensive repair. Accomplishment of Service Bulletin No. A300-57-6069 cancels the requirement of inspection of holes H and I of the corner angle fitting defined in this Service ### Page 5 @ A300-600 SERVICE BULLETIN SUMMARY DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Bulletin and cancels the requirement of inspection of the rear spar and bottom panel at junction with fuselage defined in Service Bulletin No. A300-57-6086. EFFECTIVITY This Service Bulletin is applicable to these operators : 51Y 90X AAL ABD AWW CAL CES CSN DLH FDX HLF I2L IRA JLJ KAC KAL LAA MON MSR NVJ OAL OHY QTR SUD SVA TAR THA CONCURRENT REQUIREMENTS None REFERENCES/REPERCUSSIONS TFU : 57.10.00.003 OEB : None AOT : None SIL : 53-057 LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No OTHERS : None NATURE OF THE WORK AIRCRAFT : YES EQUIPMENT : NO HARD : NO SOFT : NO OBRM : NO MANPOWER Inspection LH and RH sides, Config. 01 or 02 or 03 or 04 EVALUATION TABLE COMPLIANCE Mandatory CANCELS INSPECTION SB Yes 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 KIT PRICE (USD) See SB TOTAL MANHOURS 47.0 ELAPSED TIME (HOURS) 23.0 2 ### Page 6 @ A300-600 SERVICE BULLETIN SUMMARY DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Rework for one hole Cut out one fitting MATERIAL INFORMATION AIRCRAFT DATA Kit 576049A01R05 : 4 bolts Kit 576049A02R06 : 4 bolts Kit 576049A03R09 : 6 bolts Kit 576049A04R06 : 12 bolts Kit 576049A05R06 : 12 bolts Kit 576049A06R04 : 16 bolts Kit 576049A07R03 : 56 bolts Kit 576049A08R01 : 12 bolts Kit 576049A09R00 : 20 bolts Kit 576049A10R00 : 10 bolts APPENDICES Yes: see Appendix 01 TOTAL MANHOURS 2.0 ELAPSED TIME (HOURS) 2.0 TOTAL MANHOURS 8.0 ELAPSED TIME (HOURS) 8.0 3 ### Page 7 @ A300-600 SERVICE BULLETIN SUMMARY DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 4 ### Page 8 @ A300-600 SERVICE BULLETIN 5 DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : 1 of 77 Printed in FRANCE © AIRBUS, 2006 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 MANDATORY MANDATORY MANDATORY ATA SYSTEM : 57 TITLE : WINGS-SECTION 21-INSPECTION OF HOLES "H"AND "I" OF THE CORNER ANGLE FITTING. MODIFICATION No. : None This document contains Airbus PROPRIETARY INFORMATION and shall at all times remain the property of Airbus; no intellectual property right or licence is granted by Airbus in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without Airbus's prior written consent. 1. PLANNING INFORMATION A. EFFECTIVITY (1) Models B4-601 B4-603 B4-605R B4-620 B4-622 B4-622R C4-605R/F C4-620 F4-605R (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 0371 0377 0380 0384 0388 0391 0395 0398 0401 0405 0408 0411 0414 0417 0423 0459-0466 0469-0471 0474 0477 0479 0505-0518 0521 0525 0529 0530 0532 0533 0536 0540 0543 0546 0553-0561 0563 0566 0569 0572 0575 0577 0579 0581 0582 0584 0601-0619 0621 0623 0625-0633 0635 0637 0639 0641 0643 0645 0657 0659 0662 0664 0666 0668 0670 0673 0675 0677 0679 0681 0683 0685 0688 0690 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 ### Page 9 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : The aircraft with Mod. No. 12171S21827 (PLATES SKIN - REINFORCE FR47) or Mod. No. 12249S21912 (CENTER FUSELAGE/WING - REINFORCE FR47) embodied in production are not concerned by this Service Bulletin. (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 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 51Y 0533 90X 0666 AAL 0423 0459 0460 0461 0462 0463 0465 0466 0469 0470 0471 0474 0506 0507 0508 0509 0510 0511 0512 0513 0514 0515 0516 0517 0606 0610 0612 0615 0619 0626 0639 0643 0645 0675 ABD 0529 0557 0755 0758 0775 AWW 0633 CAL 0536 0555 0625 0743 0767 0788 CES 0521 0525 0532 0707 0709 0713 0715 0725 0732 0741 0746 0754 0763 CSN 0733 0734 0739 0750 0756 0762 DLH 0380 0391 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701 FDX 0358 0361 0365 0388 0417 0477 0479 0530 0543 0559 0572 0579 0581 0657 0659 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 HLF 0773 I2L 0677 IRA 0632 0696 0723 0727 JLJ 0602 0617 0621 0637 0641 0670 0679 0683 0703 0711 0724 0729 0730 0737 0740 0753 0770 0783 0797 KAC 0344 0673 0694 0699 0719 0721 KAL 0582 0609 0627 0631 0662 0685 0692 0717 0722 0731 LAA 0601 0616 MON 0540 0556 0604 0605 MSR 0561 0575 0607 2 ### Page 10 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (c) Effectivity by MSN and Kit/Configuration 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 0371 0377 0380 0384 0388 0391 0395 0398 0401 0405 0408 0411 0414 0417 NOTE (01) For each Kit, read Config. 01 or 02. The kits and configurations applicable to these MSNs are given at the end of this list: 0423 0459-0466 0469-0471 0474 0477 0479 0505-0518 0521 0525 0529-0530 0532-0533 0536 0540 0543 0546 0553-0561 0563 0566 NVJ 0354 OAL 0603 OHY 0584 0744 0747 0749 0764 QTR 0554 0560 0611 0613 0614 0630 0664 0668 0688 0690 SUD 0252 SVA 0284 0294 0301 0307 0312 0317 0321 0336 0341 0348 0351 TAR 0505 0558 0563 THA 0368 0371 0377 0384 0395 0398 0464 0518 0566 0569 0577 0628 0629 0635 0681 0705 0782 0784 0785 0786 0787 KIT No. QTY PER A/C CONFIGURATION 576049A01R05 1 01 02 576049A03R09 1 01 02 576049A04R06 1 01 02 576049A06R04 1 01 02 576049A08R01 1 01 02 576049A09R00 1 01 02 576049A10R00 1 01 02 OPERATOR MSN 3 ### Page 11 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 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 0690 0692 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721-0725 NOTE (01) For each Kit, read Config. 01 or 02. The kits and configurations applicable to these MSNs are given at the end of this list: 0797 0799-0804 The kits and configurations applicable to these MSNs are given at the end of this list: 0726-0750 0752-0764 0766-0775 0777-0794 KIT No. QTY PER A/C CONFIGURATION 576049A02R06 1 01 02 576049A03R09 1 01 02 576049A05R06 1 01 02 576049A06R04 1 01 02 576049A08R01 1 01 02 576049A09R00 1 01 02 576049A10R00 1 01 02 KIT No. QTY PER A/C CONFIGURATION 576049A02R06 1 03 576049A03R09 1 03 576049A05R06 1 03 576049A06R04 1 03 576049A09R00 1 03 KIT No. QTY PER A/C CONFIGURATION 576049A07R03 1 04 4 ### Page 12 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : When the airplane model designation is or has been changed from one of the following simplified airplane model designation B4-600, the value quoted may have to be revised. In such a case, AIRBUS must be contacted to implement changes. NOTE : Kit 576049A01R05 : Hole H with crack. - valid aircraft MSN 0252 thru 0417 (without Service Bulletin No. A300-57-6050 embodied). NOTE : Kit 576049A02R06 : Hole H with crack. - Valid aircraft MSN 0420 thru 0725 (without Service Bulletin No. A300-57-6050 embodied). - Valid aircraft MSN 0797 and subsequent (Mod. No. 10155S20321 embodied in production line). NOTE : Kit 576049A03R09 : Hole I with crack. - Valid aircraft MSN 0252 thru 0725 (without Service Bulletin No. A300-57-6050 embodied). - Valid aircraft MSN 0797 and subsequent (Mod. No. 10155S20321 embodied in production line). NOTE : Kit 576049A04R06 : Holes H and I without crack. - Valid aircraft MSN 0252 thru 0417 (without Service Bulletin No. A300-57-6050 embodied). NOTE : Kit 576049A05R06 : Holes H and I without crack. - Valid aircraft MSN 0420 thru 0725 (without Service Bulletin No. A300-57-6050 embodied). - Valid aircraft MSN 0797 and subsequent (Mod. No. 10155S20321 embodied in production line). CONFIGURATION No. Pre Mod.10454 (SB No.57-6050) Post Mod.10454 (SB No.57-6050) Post Mod. 10155 (Serial Solution) Mod. 10155 partly embodied 01 * 02 * 03 * 04 * 5 ### Page 13 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Kit 576049A06R04 : Holes K, L, M, N with or without crack. - Valid aircraft MSN 0252 thru 0725 (without Service Bulletin No. A300-57-6050 embodied). - valid aircraft MSN 0797 and subsequent (Mod. No. 10155S20321 embodied in production line). NOTE : Kit 576049A07R03 : Holes H, I, K, L, M, N, Y, U, V, W, X with or without crack. - Valid aircraft MSN 0726 thru 0794 (Mod. No. 10155S20321 partly embodied in production line). NOTE : Kit 576049A08R01 : Holes H, I, K, L, M, N without crack. - Valid aircraft MSN 0252 thru 0725 (with Service Bulletin No. A300-57-6050 embodied). NOTE : Kit 576049A09R00 : Holes U, V, W, X, Y with or without crack. - Valid aircraft MSN 0252 thru 0725 (without Service Bulletin No. A300-57-6050 embodied). - valid aircraft MSN 0797 and subsequent (Mod. No. 10155S20321 embodied in production line). NOTE : Kit 576049A10R00 : Holes U, V, W, X, Y without crack. - Valid aircraft MSN 0252 thru 0725 (with Service Bulletin No. A300-57-6050 embodied). NOTE : Config. 01 and 02 concerns B4/600 type, B4-601, B4-603, B4-605R, B4-620, B4-622, B4-622R, C4-605R, C4-620 models. NOTE : Config. 03 and 04 concerns B4/600 type, B4-622R, B4-605R, C4-605R/F, F4-605R models. (3) Spares None B. CONCURRENT REQUIREMENTS None 6 ### Page 14 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved C. REASON (1) History Cracks have been found on A300 B2/B4 fleet at about 20,000 flights on FR47 forward fitting at the level of last fastener of external angle fitting. Cracks if undetected can increase in magnitude in rear spar and panel, thus reducing the residual strength capacity of the structure and requiring and extensive structural repair. The in-service experience from the application of inspection on the A300 and A300-600 fleets shows that: — Cracks have been found before reaching the threshold. — Cracks have been found in other holes (basically holes H and I were inspected) during accomplishment of modification Service Bulletins No. A300-53-0298 and A300-57-6050. Revision No.03 of this Service Bulletin takes this new data into account. From Revision No.03 of this SB, further in service experience have shown that cracks have been found in other holes than holes H, I, K, L, M and N. This is why Revision No.06 request to inspect new holes U, V, W, X and Y in order to take these new findings into account. (2) Objective/Action The aim of this Service Bulletin is to call for eddy current inspection of holes H, I, K, L, M, N and U, V, W, X, Y in LH and RH internal angles of wing center box. (3) Advantages This inspection will make it possible to detect crack propagation at an early stage, thus avoiding an extensive repair. Accomplishment of Service Bulletin No. A300-57-6069 cancels the requirement of inspection of holes H and I of the corner angle fitting defined in this Service Bulletin and cancels the requirement of inspection of the rear spar and bottom panel at junction with fuselage defined in Service Bulletin No. A300-57-6086. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : 7 ### Page 15 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved On LH and RH rear internal angles of wing center box — Gaining acces to the working areas. — Removing PR sealant. — Removing fasteners H, I, K, L, M, N, Y, U, V, W, X (all configuration). — Performing rotating probe inspection. — Reinstalling fasteners. — Applying PR sealant. — Test. — Close-up. E. COMPLIANCE (1) Classification Mandatory (2) Accomplishment Timescale 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. This Service Bulletin is mandatory at the following thresholds and intervals, whichever occurs first. HOLES H, I, K, L, M, N, U, V, W, X, Y AFT: Average Flight Time CONFIG.No. THRESHOLD THRESHOLD INTERVAL INTERVAL ** Flight Cycles Flight Hours Flight Cycles Flight Hours 01 10400 22450 4500 9700 02 14200* 30650 4500 9700 03 14200 30650 4500 9700 01AFT<=1,5FH/FC 11250 16850 4850 7300 02AFT<=1,5FH/FC 15350* 23000 4850 7300 03AFT<=1,5FH/FC 15350 23000 4850 7300 8 ### Page 16 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved * Counted starting from the Service Bulletin No. A300-57-6050 embodiment time. ** For customers who have already retrofitted the Service Bulletin (Inspection of holes H and I), the new threshold value, equal to the basic "grace period", must be used for holes K, L, M, N, U, V, W, X, Y. HOLES H, I, K, L, M, N, U, V, W, X, Y AFT: Average Flight Time Grace Period: — Where A/C are between 1400 FC/3500 FH less than threshold or have exceeded the threshold by less than 1900 FC/4600 FH flights, the first inspection is to be performed within 1400 FC/3500 FH after receipt of this Service Bulletin. — For A/C which have exceeded the threshold by more than 1900 FC/4600 FH flights, the first inspection is to be performed within 700 FC/1700 FH after receipt of this Service Bulletin. NOTE : The number of touch and go flights can be neglected when they are less than five percent of the total number of flights between two consecutive inspections. When the percentage of touch and go flights is more than five percent of total number of flights between two consecutive inspections, each touch and go flight beyond five percent has to be counted as a flight cycle. A touch and go is a landing in which an airplane touches the runway and does not come to a full stop prior to commencing an additional flight. F. APPROVAL Approved under EASA Design Organisation Approval No. EASA 21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. CONFIG.No. THRESHOLD THRESHOLD INTERVAL INTERVAL Flight Cycles Flight Hours Flight Cycles Flight Hours 04 12300 26550 4500 9700 04AFT<=1,5FH/FC 13300 19950 4850 7300 9 ### Page 17 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator's circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc, and general administration work are also not included. Inspection LH and RH sides, Config.01 or 02 or 03 or 04 Rework the hole Rework the fitting H. WEIGHT AND BALANCE Not changed I. ELECTRICAL LOAD DATA Not changed J. REFERENCES Get access 14.0 Rotating probe inspection 13.0 Test 8.0 Close-up 12.0 TOTAL MANHOURS 47.0 ELAPSED TIME (HOURS) 23.0 Rework for one hole 2.0 TOTAL MANHOURS 2.0 ELAPSED TIME (HOURS) 2.0 Cut out fitting (for one fitting) 8.0 TOTAL MANHOURS 8.0 ELAPSED TIME (HOURS) 8.0 Aircraft Maintenance Manual (AMM) : 06-41-53 20-21-12 24-40-00 24-41-00 28-00-00 28-10-00 28-11-00 28-11-29 28-11-41 28-21-00 28-22-00 28-25-00 29-14-00 29-25-00 29-31-00 29-33-00 33-42-00 51-23-10 Consumable Material List (CML) 10 ### Page 18 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Non-Destructive Testing Manual (NTM) 57-10-50, Part 6, Procedures A and B Maintenance Review Board Document (MRB) Section 5 Service Bulletin No. A300-28-6028 Service Bulletin No. A300-57-6050 Service Bulletin No. A300-57-6069 Service Bulletin No. A300-57-6086 Appendix 1 K. PUBLICATIONS AFFECTED None L. INTERCHANGEABILITY/MIXABILITY None Elec. Std. Practices Manual (ESPM) : 20-55-00 Service Information Letter (SIL) : 53-057 Structural Repair Manual (SRM) : 51-40-31 51-40-32 51-40-40 51-40-47 51-40-50 51-43-00 51-76-10 11 ### Page 19 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved This Page Intentionally Left Blank 12 ### Page 20 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 2. MATERIAL INFORMATION A. MATERIAL — PRICE AND AVAILABILITY (1) Material Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is : Airbus Spares Support and Services Weg beim Jaeger 150 D-22335 Hamburg Germany For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 25 90 (2) Price and Availability Kit 576049A01R05 Cost : 727.00 US Dollars Availability : 90 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 576049A02R06 Cost : 2,080.00 US Dollars Availability : 90 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 576049A03R09 Cost : 2,998.00 US Dollars Availability : 150 calendar days from receipt of order 13 ### Page 21 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 576049A04R06 Cost : 1,140.00 US Dollars Availability : 120 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 576049A05R06 Cost : 1,270.00 US Dollars Availability : 150 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 576049A06R04 Cost : 2,090.00 US Dollars Availability : 120 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 576049A07R03 Cost : 5,780.00 US Dollars Availability : 120 calendar days from receipt of order 14 ### Page 22 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 576049A08R01 Cost : 1,600.00 US Dollars Availability : 120 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 576049A09R00 Cost : 4,198.00 US Dollars Availability : 99 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. Kit 576049A10R00 Cost : 3,602.00 US Dollars Availability : 99 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. B. INDUSTRY SUPPORT INFORMATION Airbus will not provide industrial support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS Kit 576049A01R05 15 ### Page 23 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 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 576049A02R06 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 576049A03R09 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 5 NSA5351V7-36 2 Bolt 10 NSA5351V8-36 2 Bolt 35 NSA5050-7 2 Nut 36 NSA5050-8 2 Nut ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 2 ASNA0093-7-36 2 Bolt 3 ASNA0093-8-36 2 Bolt 42 NAS1726-7E 2 Nut 43 NAS1726-8E 2 Nut ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 7 NSA5351V8-28 2 Bolt 16 NSA5357-8-28 2 Pin 31 NSA5359-8-28 2 Bolt 36 NSA5050-8 2 Nut 38 NSA5059-4 2 Nut 39 NSA5059-5 4 Nut 40 NSA5060-4 1 Nut 43 NAS1726-8E 2 Nut 47 MS24665-152 6 Pin 48 MS24665-153 1 Pin 49 NSA5368PD616B 5 Washer 50 NSA5368PD716B 10 Washer 51 NSA5368PD816B 10 Washer 52 NSA5368PD916B 2 Washer 16 ### Page 24 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 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 576049A04R06 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 576049A05R06 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 576049A06R04 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 4 NSA5351V6-36 2 Bolt 5 NSA5351V7-36 2 Bolt 9 NSA5351V8-34 2 Bolt 10 NSA5351V8-36 2 Bolt 19 NSA5357-8-34 2 Bolt 30 NSA5359-8-34 2 Bolt 34 NSA5050-6 2 Nut 35 NSA5050-7 2 Nut 36 NSA5050-8 4 Nut 43 NAS1726-8E 4 Nut ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 1 ASNA0093-6-36 2 Bolt 2 ASNA0093-7-36 2 Bolt 3 ASNA0093-8-36 2 Bolt 9 NSA5351V8-34 2 Bolt 19 NSA5357-8-34 2 Bolt 30 NSA5359-8-34 2 Bolt 36 NSA5050-8 2 Nut 41 NAS1726-6E 2 Nut 42 NAS1726-7E 2 Nut 43 NAS1726-8E 6 Nut 17 ### Page 25 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 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 576049A07R03 ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 6 NSA5351V8-25 4 Bolt 8 NSA5351V8-30 2 Bolt 11 NSA5351V9-25 2 Bolt 12 NSA5351V9-30 2 Bolt 21 NSA5359-8-25 2 Pin 29 NSA5359-8-31 2 Bolt 32 NSA5351V8-31 2 Bolt 36 NSA5050-8 8 Nut 37 NSA5050-9 4 Nut 43 NAS1726-8E 4 Nut ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 4 NSA5351V6-36 2 Bolt 5 NSA5351V7-36 2 Bolt 7 NSA5351V8-28 2 Bolt 10 NSA5351V8-36 2 Bolt 11 NSA5351V9-25 2 Bolt 12 NSA5351V9-30 2 Bolt 13 NSA5357-8-25 10 Bolt 14 NSA5357-8-26 2 Pin 15 NSA5357-8-27 2 Pin 16 NSA5357-8-28 2 Pin 17 NSA5357-8-30 2 Bolt 18 NSA5357-8-31 2 Bolt 19 NSA5357-8-34 2 Bolt 21 NSA5359-8-25 10 Pin 26 NSA5359-8-26 2 Pin 27 NSA5359-8-27 2 Pin 28 NSA5359-8-30 2 Bolt 29 NSA5359-8-31 2 Bolt 30 NSA5359-8-34 2 Bolt 31 NSA5359-8-28 2 Bolt 34 NSA5050-6 2 Nut 35 NSA5050-7 2 Nut 36 NSA5050-8 4 Nut 18 ### Page 26 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 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 576049A08R01 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 576049A09R00 37 NSA5050-9 4 Nut 38 NSA5059-4 2 Nut 39 NSA5059-5 4 Nut 40 NSA5060-4 1 Nut 43 NAS1726-8E 24 Nut 47 MS24665-152 6 Pin 48 MS24665-153 1 Pin 49 NSA5368PD616B 5 Washer 50 NSA5368PD716B 10 Washer 51 NSA5368PD816B 10 Washer 52 NSA5368PD916B 2 Washer ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 20 NSA5359-6-36 2 Bolt 21 NSA5359-8-25 4 Pin 28 NSA5359-8-30 2 Bolt 29 NSA5359-8-31 2 Bolt 30 NSA5359-8-34 2 Bolt 41 NAS1726-6E 2 Nut 43 NAS1726-8E 10 Nut ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 6 NSA5351V8-25 6 Bolt 13 NSA5357-8-25 6 Bolt 14 NSA5357-8-26 2 Pin 15 NSA5357-8-27 2 Pin 22 NSA5351V8-26 2 Bolt 23 NSA5351V8-27 2 Bolt ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 19 ### Page 27 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 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 576049A10R00 NOTE : Refer to the AIRBUS Standards Manual (SM) if you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relationship. D. LIST OF MATERIALS — OPERATOR SUPPLIED (1) Consumable Materials (2) Components None E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR None 36 NSA5050-8 10 Nut 43 NAS1726-8E 10 Nut ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 21 NSA5359-8-25 6 Pin 26 NSA5359-8-26 2 Pin 27 NSA5359-8-27 2 Pin 43 NAS1726-8E 10 Nut DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C INST DISP Fuel Tank Sealant Polysulfide 09-001 As required Corrosion Interfay Sealant 09-005 As required Solvant General Purpose 11-026 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Anti-Corrosion Primer (Epoxy-Imprvdadhesion) 16-006 As required External Top Coat (Polyurethane) 16-018 As required ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 20 ### Page 28 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved F. TOOLING — PRICE AND AVAILABILITY To acomplish this Servive Bulletin it is necessary to use the following tools and equipment — Equipment and materials for check of holes as per Non-Destructive Testing Manual (NTM) 57-10-50, Part 6, Procedures A and B G. SPECIAL TOOLS None 21 ### Page 29 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved This Page Intentionally Left Blank 22 ### Page 30 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. 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. IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00. (1) Preparation (a) Electrically ground the aircraft (Refer to AMM 24-40-00 Page block 301). (b) Put the access platforms in position. (c) Defuel center fuel tank (Refer to AMM 28-25-00 Page block 301). (d) Perform degassing of center fuel tank (Refer to AMM 28-00-00 Page block 301) and (Refer to AMM 28-10-00 Page block 301). NOTE : Make certain that safety precautions regarding access to, and working in, center fuel tank are strictly adhered to. (e) Open the access doors 147AZ and 148AZ (Refer to AMM 06-41-53) and (Refer to AMM 28-11-29 Page block 401). (f) Open, safety and tag these circuit breakers: PANEL DESIGNATION FIN LOCATION 132VU LIGHTING-EXRERIOR LT-LAND L SUPPLY 1LB N 80 132VU LIGHTING-EXRERIOR LT-LAND R SUPPLY 2LB M 78 132VU LIGHTING-EXRERIOR LT-LAND L SUPPLY 3LB M 81 132VU LIGHTING-EXRERIOR LT-LAND R CTL 4LB M 77 23 ### Page 31 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (2) Standard Practices (a) For inspection 1 For the specification of the material numbers (Mat. No.), refer to CML. 2 To clean the surface to be sealed with Solvant General Purpose (Mat No. 11-026) . 3 Do the sealing processes (Refer to SRM 51-76-10). 4 Torque the standard threaded fasteners (Refer to AMM 20-21-12) and (Refer to SRM 51-43-00). 5 For alternative and substitute fasteners, (Refer to SRM 51-40-32). 6 Install the fasteners with Corrosion Interfay Sealant (Mat No. 09-005) and encapsulate exposed parts of fasteners with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . (b) For repair 1 Drill fastener holes (Refer to SRM 51-40-40). 2 For oversized fasteners (Refer to SRM 51-40-31). 3 For fastener spacing and margin data (Refer to SRM 51-40-50). 4 For alternative and substitute fasteners, (Refer to SRM 51-40-32). 5 To countersink data (Refer to SRM 51-40-47). 133VU RSVR/WARN 1GR 333/T 58 133VU ENG1/PUMP CTL/G 99GK 331/U 58 133VU ENG2/PUMP CTL/G 100GK 332/U 58 133VU ELEC/PUMPS/WARN 4GE 331/V 60 133VU PTU CTL/G/B 1GL 332/U 59 133VU ENG1/PUMP CTL/B 31GJ 331/V 57 133VU PTU CTL/G/Y 6GL 332/U 60 133VU ENG2/PUMP CTL/Y 1GD 332/U 57 133VU RAT/TEST 1GF 331/V 59 133VU ACCU PRESS/CTL &/CARGO DOOR/PUMP 7GX 333/T 51 101VU ELEC/HYD/PUMP 23GX GEN2/B 8 133VU RSVR/WARN 1GQ 333/T 59 PANEL DESIGNATION FIN LOCATION 24 ### Page 32 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 6 To renew protective finish (Refer to AMM 51-23-10) using Chemical Conversion Coating Yellow Aluminum (Mat No. 13-002) , Anti-Corrosion Primer (Epoxy-Imprvdadhesion) (Mat No. 16-006) (for fuel tank), External Top Coat (Polyurethane) (Mat No. 16-018) (for external applications). B. INSPECTION (1) Get access to the inspection area. Refer to figures 4 , 5 , 6 , 7 (a) Removal of LH hydraulic panel. 1 Remove Fairings (refer to figure 4 ) 2 In zone 542, disconnect plugs 43QA-A and 49QA-A. 3 In zone 571, remove ties and disconnect plugs 3GHA, 11QB-A, 11QQ-A,24GQ-A, 33GR-A, 51QA-A, 57QA-A, 1935VC-A, 1937VC-A and ground connections 536VN and 538VN. NOTE : Plugs 11QQ-A and 12QQ-A: Available only on A/C with Mod. No. 08679, 08680 (Service Bulletin No. A300-28-6028 ). 4 Remove hydraulic panel (refer to figure 5 ) (b) Removal of RAT (Ram Air Turbine) panel 1 Remove fairings (refer to figure 4 ) 2 Fairings Item (60) Retain 4 Inserts Item (61) Retain 2 Bushes Item (62) Retain 2 Fairings Item (63) Retain 2 Bolts Item (64) Retain 2 Bolts Item (65) Retain 4 Nuts Item (66) Retain 1 Hydraulic panel assy Item (59) Retain 6 Guides Item (67) Retain 6 Bolts Item (68) Retain 1 Bolt Item (69) Retain 2 Bolts Item (70) Retain 2 Washers Item (71) Retain 1 Washer Item (72) Retain 1 Nut Item (38) Discard 2 Nut Item (39) Discard 3 Cotter pins Item (47) Discard 25 ### Page 33 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 2 Remove hydraulic lines CAUTION: PLUG/CAP PORTS AND ALL OPEN LINE ENDS. — Return filter line — Pressurization line — Overflow line — Return line 3 Remove adjustable rod/crank link of RAT (refer to figure 6 ) WARNING : BEFORE PROCEEDING WITH ANY WORK ON RAT, MAKE CERTAIN THAT UPLOCK UNIT ACTUATING LEVER RIGGING PIN IS CORRECTLY INSERTED. 4 In zone 671, remove ties and disconnect plugs 12QB-A, 12QQ-A, 52QA-A, 58QA-A, 1936VC-A, 1983VC-A. 5 Remove RAT panel, refer to figure 7 (2) For the inspection area and holes location, refer to figure 1 , sheets 1 and 2 . 2 Fairings Item (60) Retain 4 Inserts Item (61) Retain 2 Bushes Item (62) Retain 2 Fairings Item (63) Retain 2 Bolts Item (64) Retain 2 Bolts Item (65) Retain 4 Nuts Item (66) Retain 1 Bolt Item (74) Retain 1 Nut Item (40) Discard 1 Sleeve Item (75) Retain 1 Washer Item (76) Retain 1 Cotter pin Item (48) Discard 1 Hydraulic panel assy Item (58) Retain 3 Guides Item (67) Retain 3 Guides Item (73) Retain 6 Bolts Item (68) Retain 1 Bolt Item (69) Retain 2 Bolts Item (70) Retain 2 Washers Item (71) Retain 1 Washer Item (72) Retain 1 Nut Item (38) Discard 2 Nuts Item (39) Discard 3 Cotter pin Item (47) Discard 26 ### Page 34 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (3) Do a rotating probe inspection (a) Config. No. 01 or 02 or 03 Refer to figure 2 , sheets 1 thru 9 . (b) Config. No. 04 Refer to figure 3 , sheets 1 thru 9 . (4) For the Inspection Report, refer to Appendix 01 . C. REPAIR (1) Replace fasteners, hole H (config.No 01 or 02 or 03). Refer to figure 8 and figure 9 . NOTE : During the installation, if the fasteners are too long, +1.6mm(0.063in.), it is possible to add one washer NSA5368 (for oversize bolt) with a new nut the reference of which must be the same as the reference of removed nut. (a) Kit 576049A04R06 (b) Kit 576049A05R06 (c) Kit 576049A08R01 (d) Kit 576049A01R05 (e) Kit 576049A02R06 2 Bolt NSA5351V6-36 Item 4 2 Bolt NSA5351V7-36 Item 5 2 Bolt NSA5351V8-36 Item 10 2 Nut NSA5050-6 Item 34 2 Nut NSA5050-7 Item 35 2 Nut NSA5050-8 Item 36 2 Bolt ASNA0093-6-36 Item 1 2 Bolt ASNA0093-7-36 Item 2 2 Bolt ASNA0093-8-36 Item 3 2 Nut NAS1726-6E Item 41 2 Nut NAS1726-7E Item 42 2 Nut NAS1726-8E Item 43 2 Bolt NSA5359-6-36 Item 20 2 Nut NAS1726-6E Item 41 2 Bolt NSA5351V7-36 Item 5 2 Bolt NSA5351V8-36 Item 10 2 Nut NSA5050-7 Item 35 2 Nut NSA5050-8 Item 36 27 ### Page 35 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (2) Replace fasteners, hole I (config.No 01 or 02 or 03). Refer to figure 8 and figure 10 . NOTE : During the installation, if the fasteners are too long, +1.6mm(0.063in.), it is possible to add one washer NSA5368 (for oversize bolt) with a new nut the reference of which must be the same as the reference of removed nut. (a) Kit 576049A04R06 (b) Kit 576049A08R01 (c) Kit 576049A04R06 (d) Kit 576049A03R09 (3) Replace fasteners, holes K and N (config.No 01 or 02 or 03) Refer to figure 8 , figure 11 and figure 14 . NOTE : During the installation, if the fasteners are too long, +1.6mm(0.063in.), it is possible to add one washer NSA5368 (for oversize bolt) with a new nut the reference of which must be the same as the reference of removed nut. (a) Kit 576049A06R04 2 Bolt ASNA0093-7-36 Item 2 2 Bolt ASNA0093-8-36 Item 3 2 Nut NAS1726-7E Item 42 2 Nut NAS1726-8E Item 43 2 Bolt NSA5351V8-34 Item 9 2 Bolt NSA5357-8-34 Item 19 2 Nut NSA5050-8 Item 36 2 Nut NAS1726-8E Item 43 2 Bolt NSA5359-8-34 Item 30 2 Nut NAS1726-8E Item 43 2 Bolt NSA5359-8-34 Item 30 2 Nut NAS1726-8E Item 43 2 Bolt NSA5351V8-28 Item 7 2 Bolt NSA5357-8-28 Item 16 2 Bolt NSA5359-8-28 Item 31 2 Nut NSA5050-8 Item 36 2 Nut NAS1726-8E Item 43 5 Washer NSA5368PD616B Item 49 10 Washer NSA5368PD716B Item 50 10 Washer NSA5368PD816B Item 51 2 Washer NSA5368PD916B Item 52 28 ### Page 36 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (b) Kit 576049A08R01 (c) Kit 576049A06R04 (4) Replace fasteners, holes L and M (config.No 01 or 02 or 03). Refer to figure 8 , figure 11 and figure 14 . NOTE : During the installation, if the fasteners are too long, +1.6mm(0.063in.), it is possible to add one washer NSA5368 (for oversize bolt) with a new nut the reference of which must be the same as the reference of removed nut. (a) Kit 576049A06R04 (b) Kit 576049A08R01 (c) Kit 576049A06R04 (5) Replace the fasteners of the holes U, V, W, X and Y (config. No.01 or 02 or 03). Refer to figure 8 , figure 12 , sheets 1 and 2 . NOTE : During the installation, if the fasteners are too long, +1.6mm(0.063in.), it is possible to add one washer NSA5368 (for oversize bolt) with a new nut the reference of which must be the same as the reference of removed nut. (a) Kit 576049A09R00 2 Bolt NSA5351V8-25 Item 6 2 Bolt NSA5351V8-30 Item 8 4 Nut NSA5050-8 Item 36 2 Bolt NSA5359-8-25 Item 21 2 Bolt NSA5359-8-30 Item 28 4 Nut NAS1726-8E Item 43 2 Bolt NSA5351V9-25 Item 11 2 Bolt NSA5351V9-30 Item 12 4 Nut NSA5050-9 Item 37 2 Bolt NSA5351V8-25 Item 6 2 Bolt NSA5351V8-31 Item 32 4 Nut NSA5050-8 Item 36 2 Bolt NSA5359-8-25 Item 21 2 Bolt NSA5359-8-31 Item 29 4 Nut NAS1726-8E Item 43 2 Bolt NSA5359-8-31 Item 29 2 Bolt NSA5359-8-25 Item 21 4 Nut NAS1726-8E Item 43 29 ### Page 37 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (b) Kit 576049A10R00 (6) Replace fasteners, hole H (config. No.04). Refer to figure 8 and figure 13 NOTE : During the installation, if the fasteners are too long, +1.6mm(0.063in.), it is possible to add one washer NSA5368 (for oversize bolt) with a new nut the reference of which must be the same as the reference of removed nut. (a) Kit 576049A07R03 (b) Kit 576049A07R03 (7) Replace fasteners, hole I (config. No.04). Refer to figure 8 and figure 13 . NOTE : During the installation, if the fasteners are too long, +1.6mm(0.063in.), it is possible to add one washer NSA5368 (for oversize bolt) with a new nut the reference of which must be the same as the reference of removed nut. (a) Kit 576049A07R03 6 Bolt NSA5351V8-25 Item 6 2 Bolt NSA5351V8-26 Item 22 2 Bolt NSA5351V8-27 Item 23 6 Bolt NSA5357-8-25 Item 13 2 Bolt NSA5357-8-26 Item 14 2 Bolt NSA5357-8-27 Item 15 10 Nut NSA5050-8 Item 36 10 Nut NAS1726-8E Item 43 6 Bolt NSA5359-8-25 Item 21 2 Bolt NSA5359-8-26 Item 26 2 Bolt NSA5359-8-27 Item 27 10 Nut NAS1726-8E Item 43 2 Bolt NSA5351V6-36 Item 4 2 Bolt NSA5351V7-36 Item 5 2 Bolt NSA5351V8-36 Item 10 2 Nut NSA5050-6 Item 34 2 Nut NSA5050-7 Item 35 2 Nut NSA5050-8 Item 36 2 Bolt NSA5351V7-36 Item 5 2 Bolt NSA5351V8-36 Item 10 2 Nut NSA5050-7 Item 35 2 Nut NSA5050-8 Item 36 2 Bolt NSA5357-8-34 Item 19 2 Nut NAS1726-8E Item 43 30 ### Page 38 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (b) Kit 576049A07R03 (c) Kit 576049A07R03 (8) Replace fasteners, holes K and N (config. No.04). Refer to figure 8 and figure 13 . NOTE : During the installation, if the fasteners are too long, +1.6mm(0.063in.), it is possible to add one washer NSA5368 (for oversize bolt) with a new nut the reference of which must be the same as the reference of removed nut. (a) Kit 576049A07R03 (b) Kit 576049A07R03 (9) Replace fasteners, holes L and M (config. No.04). Refer to figure 8 and figure 13 . NOTE : During the installation, if the fasteners are too long, +1.6mm(0.063in.), it is possible to add one washer NSA5368 (for oversize bolt) with a new nut the reference of which must be the same as the reference of removed nut. (a) Kit 576049A07R03 (b) Kit 576049A07R03 2 Bolt NSA5359-8-34 Item 30 2 Nut NAS1726-8E Item 43 2 Bolt NSA5351V8-28 Item 7 2 Bolt NSA5357-8-28 Item 16 2 Bolt NSA5359-8-28 Item 31 2 Nut NSA5050-8 Item 36 2 Nut NAS1726-8E Item 43 2 Bolt NSA5357-8-25 Item 13 2 Bolt NSA5359-8-25 Item 21 2 Bolt NSA5357-8-30 Item 17 2 Bolt NSA5359-8-30 Item 28 4 Nut NAS1726-8E Item 43 2 Bolt NSA5351V9-25 Item 11 2 Bolt NSA5351V9-30 Item 12 4 Nut NSA5050-9 Item 37 2 Bolt NSA5357-8-25 Item 13 2 Bolt NSA5359-8-25 Item 21 2 Bolt NSA5357-8-31 Item 18 2 Bolt NSA5359-8-31 Item 29 4 Nut NAS1726-8E Item 43 31 ### Page 39 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (10) Replace fasteners, holes U, V, W, X, Y (config. No.04). Refer to figure 8 and figure 13 . NOTE : During the installation, if the fasteners are too long, +1.6mm(0.063in.), it is possible to add one washer NSA5368 (for oversize bolt) with a new nut the reference of which must be the same as the reference of removed nut. (a) Kit 576049A07R03 (11) Install RAT panel assembly Refer to figures 6 and 7 (a) Install panel (Refer to figure 7) NOTE : Items (58), (67), (73), (68), (69), (70), (71), (72) were retained at removal. (b) In zone 671, install ties and connect plugs 12QB-A, 12QQ-A, 52QA-A, 58QA-A, 1936VC-A, 1938VC-A. (c) Install adjustable rod/crank link of RAT (refer to figure 6) 2 Bolt NSA5359-8-25 Item 21 2 Bolt NSA5359-8-31 Item 29 4 Nut NAS1726-8E Item 43 6 Bolt NSA5357-8-25 Item 13 6 Bolt NSA5359-8-25 Item 21 2 Bolt NSA5357-8-26 Item 14 2 Bolt NSA5359-8-26 Item 26 2 Bolt NSA5357-8-27 Item 15 2 Bolt NSA5359-8-27 Item 27 10 Nut NAS1726-8E Item 43 1 Panel assy Item (58) 3 Guides Item (67) 3 Guides Item (73) 6 Bolts Item (68) 1 Bolt Item (69) 2 Bolts Item (70) 2 Washer Item (71) 1 Washer Item (72) 1 Nut NSA5059-4 Item 38 2 Nuts NSA5059-5 Item 39 3 Cotter pin MS24665-152 Item 47 1 Bolt Item (74) 1 Nut NSA5060-4 Item 40 32 ### Page 40 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Items (74), (75), (76) were retained et removal. (d) Install hydraulic lines: — Return filter line — Pressurization line — Overflow line — Return line. (12) Installation of LH hydraulic panel Refer to figure 5 (a) Install hydraulic panel NOTE : Items (59), (67), (68), (69), (70), (71), (72) were retained at removal. (b) In zone 571, install ties and connect plugs 3GH-A, 11QB-A, 11QQ-A, 24GQ-A, 33GR-A, 51QA-A, 57QA-A, 1935VC-A, 1937VC-A and ground connections 536VN and 538VN. (13) Install fairings, on LH and RH sides. Refer to figure 4 (a) Install on LH side 1 Sleeve Item (75) 1 Washer Item (76) 1 Cotter pin MS24665-153 Item 48 1 Hydraulic panel assy Item (59) 6 Guides Item (67) 6 Bolt Item (68) 1 Bolt Item (69) 2 Bolt Item (70) 2 Washer Item (71) 1 Washer Item (72) 1 Nut NSA5059-4 Item 38 2 Nuts NSA5059-5 Item 39 3 Cotter pin MS24665-152 Item 47 2 Fairing Item (60) 4 Insert Item (61) 2 Bushes Item (62) 2 Fairing Item (63) 2 Bolt Item (64) 33 ### Page 41 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : Items (60), (61), (62), (63), (64), (65), (66) were retained at removal. (b) Install on RH side NOTE : Items (60), (61), (62), (63), (64), (65), (66) were retained at removal. (c) In zone 542, connect plugs 43QA-A and 49QA-A. D. TEST (1) Job set-up (a) Connect electrical ground power unit and energize the aircraft electrical network and make certain that electronics racks are ventilated (Refer to AMM 24-41-00 Page block 301). (b) Close access doors 147AZ, 148AZ (Refer to AMM 28-11-29 Page block 401). (c) Refuel center tank (Refer to AMM 28-25-00 Page block 301). (2) Test (a) Perform operational test of landing lights (Refer to AMM 33-42-00 Page block 501). (b) Perform functional test of hydraulic fluid tank pressurizing system (Refer to AMM 29-14-00 Page block 501). (c) Perform operational test of hydraulic fluid temperature indicating system (Refer to AMM 29-33-00 Page block 501). (d) Perform adjustment of rod/crank of RAT (Refer to AMM 29-25-00 Page block 501). (e) Perform functional test of yellow auxiliary power (RAT) (Refer to AMM 29-25-00 Page block 501). (f) Perform functional test of hydraulic fluid indicating system (Refer to AMM 29-31-00 Page block 501). 2 Bolt Item (65) 4 Nut Item (66) 2 Fairing Item (60) 4 Insert Item (61) 2 Bushes Item (62) 2 Fairing Item (63) 2 Bolt Item (64) 2 Bolt Item (65) 4 Nut Item (66) 34 ### Page 42 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (g) Perform leak test (Refer to AMM 28-11-00 Page block 501). (h) Perform operational test of pressure switch booster pumps 1 and 2, LH and RH inner tank (Refer to AMM 28-21-00 Page block 501). (i) Perform operational test of actuator isolation valves, LH and RH inner tank (Refer to AMM 28-22-00 Page block 501). (j) Perform test procedure of fuel pump water scavenge, LH and RH inner tank, described below. NOTE (01) This test is only required on aircraft yhat have Mod. No.08679, No.08680 or Service Bulletin No. A300-28-6028 accomplished. NOTE (02) Plugs 11QQ-A and 12QQ-A: available A/C only with Mod. No.08679, No.08680 or Service Bulletin No. A300-28-6028 accomplished. (k) Open, safety and tag these circuit breakers: (l) Make sure that these circuit breakers are closed. — Energize the aircraft electrical circuits (Refer to AMM 24-41-00 Page block 301). — On the panel 9VU, make sure that the ENG1 and ENG2 HP valve control levers are in OFF position. — Refuel the aircraft to get a minimum fuel quantity between 1500 kgs (3300 lbs) and 2000 kgs (4400 lbs) (Refer to AMM 28-11-41 Page block 501). PANEL DESIGNATION FIN LOCATION 101VU FUEL/L INNER TK/PUMP 2/SUPPLY 1QA ESS1/B 01 101VU FUEL/R INNER TK/PUMP 1/SUPPLY 2QA ESS1/A 01 101VU FUEL/L INNER TK/PUMP 1/SUPPLY 7QA GEN2/A 20 101VU FUEL/R INNER TK/PUMP 2/SUPPLY 8QA GEN2/A 17 101VU FUEL/CTR TK/L PUMP SUPPLY 99BA ESS/B 04 101VU FUEL/CTR TK/R PUMP SUPPLY 100QA GEN2/B 14 132VU SCAVENGE SYSTEM/PUMP/INNER L 1QQ 325/K 60 132VU SCAVENGE SYSTEM/PUMP/INNER R 2QQ 325/K 61 132VU SCAVENGE SYSTEM/PUMP/TT 3QQ 325/K 62 PANEL DESIGNATION FIN LOCATION 132VU SCAVENGE SYSTEM/PUMP/CONTROL 13QQ 325/K 63 132VU FUEL/AUTO FEED CTL 65QA 323M 55 132VU LIGHTING/MAINT PANEL/ANN & MFA 1WB 324/L 78 132VU LIGHTING/MAINT PANEL/ANN & MFA 22WB 324/L 79 35 ### Page 43 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved — On the overhead panel 430VU, mak sure that the fuel pump switches that follow are in the OFF position:L outer tank pump 1,L outer tank pump 2,R outer tank pump 1,R outer tank pump 2,Trim tank pump 1,Trim tank pump 2. — On the over head 430VU, make sure that the trim TK MODE oushbutton switch is in AUTO position. — Do this test: ACTION RESULT 1. On the maintenance panel 472VU: — Put the ANN LT switch in the TEST position. — The fault light on the scavenge system annunciator comes ON. — Put the ANN LT switch in the READ position. — Push in the MFA RESET switch. — The fault light on the scavenge system annunciator goes OFF. 2. On the overhead panel 430VU: — Press (in) all the INR TK pump pushbutton switshes (p/bsw). — The OFF lights on the INR TK PUMP p/bsw go OFF. — Press (in) both the CTR TK PUMP p/bsw. — The OFF lights on both the CTR TK PUMP p/bsw go OFF. 3. On the maintenance panel 472VU: — ANN LT switch which is in READ position from above. — The fault light on the scavenge system annunciator comes ON. 4. On the overhead panel 430VU: — Release (out) both the CTR TK PUMP p/bsw. — The OFF lights on the CTR TK PUMP p/bsw come ON. 5. On the maintenance panel 472VU: — Push in the MFA RESET switch. — The FAULT light on the scavenge system annunciator goes OFF. 6. On the panel 132VU: — Remove the tags and close circuit breakers 1QQ, 2QQ and 3QQ. 7. On the overhead panel 430VU: — Push (in) both the the CTR TK PUMP p/bsw. — The OFF lights on the CTR TK PUMP p/bsw go OFF. 8. On the maintenance panel 472VU: — With the ANN LT switch still in the READ position. — The FAULT light on the scavenge system annunciator stays OFF. 36 ### Page 44 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved — De-energize the aircraft electrical circuits (Refer to AMM 24-41-00 Page block 301). — Remove the tag and close these circuit breakers: 9. On the panel 132VU: — Open, safety and tag circuit breaker 1QQ. — L INR scavenge pump stops running. 10. On the maintenance panel 472VU: — With the ANN LT switch still in the READ position. — The FAULT light on the scavenge system annunciator comes ON. 11. On the panel 132VU: — Remove the tags and close circuit breakers 1QQ. 12. On the maintenance panel 472VU: — Push in the MFA RESET switch. — The FAULT light on the scavenge system annunciator goes OFF. 13. On the panel 132VU: — Open, safety and tag circuit breaker 2QQ. — R INR scavenge pump stops running. 14. On the maintenance panel 472VU: — With the ANN LT switch in the READ position. — The FAULT light on the scavenge system annunciator comes ON. 15. On the panel 132VU: — Remove the tags and close circuit breakers 2QQ. 16. On the maintenance panel 472VU: — Push in the MFA RESET switch. — The FAULT light on the scavenge system annunciator goes OFF. — Put the ANN LT switch in the OFF position. PANEL DESIGNATION FIN LOCATION 101VU FUEL/L INNER TK PUMP2/SUPPLY 1QA ESS1/B 01 101VU FUEL/R INNER TK PUMP1/SUPPLY 2QA ESS1/A 01 101VU FUEL/L INNER TK PUMP1/SUPPLY 7QA GEN2/A 20 101VU FUEL/R INNER TK PUMP2/SUPPLY 8QA GEN2/A 17 101VU FUEL/CTR TK/L PUMP SUPPLY 99QA ESS/B 04 101VU FUEL/CTR TK/L PUMP SUPPLY 100QA GEN2/B 14 37 ### Page 45 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved E. CLOSE UP (1) Make sure that the work areas are clean and clear of tools and other items. (2) Remove the access platforms. (3) Restore the systems and the aircraft to normal operating condition. F. DOCUMENTATION Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. 38 ### Page 46 @ A300-600 SERVICE BULLETIN DATE : Sep 09/94 SERVICE BULLETIN No. : A300—57—6049 REVISION No. : 07 — Dec 22/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 1 Sheet 1 Location 39 ### Page 47 (OCR) A300-600 SERVICE BULLETIN RIB1 WING CENTER BOX WING SPAR BOX HOLE M HOLE Y HOLE U HOLE V HOLE L A - HOLE K HOLE H HOLE I HOLE N HOLE W HOLE X WING CENTER BOX - INTERNAL VIEW LEFT SIDE SHOWN RIGHT SIDE SYMMETRICAL SECTION A-A HOLE I FR47 DATUM FRONT FITTING FR47 • ASB5 576049 AC 00 d INTERNAL ANGLE SHIM VALID ALL CONFIG. Figure 1 Sheet 2 Location DATE : Sep 09/94 SERVICE BULLETIN No. : A300-57-6049 REVISION No. : 07 - Dec 22/06 Page : 40 Printed in FRANCE © AIRBUS, 2006 All rights reserved ### Page 48 (OCR) A300-600 SERVICE BULLETIN Hole H: INSPECTION • OF HOLE H do the rotating probe inspection ON FR47. NTM 57-10-50. Part 6. procedure of THIS VIEW SHOWS ONLY hole H, on internal threshold ONE LAYER and intervals per 1.E. (2) or (L1 = L2) apply Service Bulletin No. A300-57-6050 (Mod. No. 10454520572). Remove PR sealant around fastener, use exclusively non-metallic spatula in the event of scratches, polish surface and perform protection. CRACK Remove fast emat. 11-026. and clean QUESTION bore with ACTION Check bore diameter FINDING (nominal diameter or R1 or R2 oversize). Contact AI Perform rotating probe inspection Before in all the layers of hole H. next flight DIA (0.499in}} 12.7mm Cracks GO to sheet 2 If nominal fastener removed is not damaged, this fastener can be re-installed. If the fastener is damaged, replace it 2 fastener is removed, new same fastener. If R1 or R2 ASB5 576049 AD 00 d install next nominal fastener Ref. Para. 3.C.(1).(a)or (b) or(c) Do subsequent inspections in Para. intervals 1.E. (2) Perform PR sealing Figure 2 Sheet 1 Flow Chart (Config. 01 or 02 or 03) DATE : Sep 09/94 SERVICE BULLETIN No. : A300-57-6049 REVISION No. : 07 - Dec 22/06 Page : 41 Printed in FRANCE © AIRBUS, 2006 All rights reserved ### Page 49 (OCR) A300-600 SERVICE BULLETIN * For A/C SB A300-57-6050 config No. 02 Continuation of sheet 1 Mod. 10454520572 accomplished): contact AI es Cracks DIA. ≥ 12.7mm yes (0.499in.) Contact Al Before no next flight Crack L2 > 1.6mm Crack L2 ≤ 1.6mm (0.062in.) (0.062in.) Ream hole, step by Contact Al Before dimension: (0.499in.) 12.7mm step oversize max. dia. next flight and rotating do a inspection 87-18-50A. as Part 6. procedure NTM Residual crack Install oversize fasteners Ref Far a 3. C. (1). (d) or (e) ASB5 576049 AE 00 d Do Perform PR sealing subsequent inspections SEE A SHEET 1 at intervals giver in Para. 1.E. (2 Figure 2 Sheet 2 Flow Chart (Config. 01 or 02 or 03) DATE : Sep 09/94 SERVICE BULLETIN No. : A300-57-6049 REVISION No. : 07 - Dec 22/06 Page : 42 Printed in FRANCE © AIRBUS, 2006 All rights reserved ### Page 50 (OCR) A300-600 SERVICE BULLETIN Hole I: do the rotating probe inspection NTM 57-10-50 Part 6. procedure A ot hole interna para. at threshold INSPECTION OF HOLE I apply and Service intervals (Mod. No. Bulletin 10454520572). per No. A300-57-6050 1.E. (2) or THIS FITTING ON VIEW FR47 SHOWS REMOVED WITH ONLY ONE LAYER. Remove PR sealant around fastener, use exclusively a non-metallic spatula in the event of scratches, polish surface and perform protection. CRACK Remove fastener and clean bore with Mat. 11-026. * For A/C config No. 02 (SB А300-57-6050 Check bore diameter Mod. 10454S20572 (nominal diameter accomplished): or R1 or R2 oversize). contact AI Perform rotating probe inspection in all the layers of hole during the inspection Contact AI the possibility have Before wrong value. figure 8). next flight Cracks DIA. 13.5mm (0.531in.) DIA (0?531іп.) 13.5mm Contact Al ASB5 576049 AF 00 d no next Before flight If Install new fastener of same type the removed fastener IS not Ref. damaged, this ara. 3.c. (2) (0) or (6) re-installed GO to sheet Do subsequent Inspections at intervals JIver Perform PR sealing in Para. I.E.(2 Figure 2 Sheet 3 Flow Chart (Config. 01 or 02 or 03) DATE : Sep 09/94 SERVICE BULLETIN No. : A300-57-6049 REVISION No. : 07 - Dec 22/06 Page : 43 Printed in FRANCE © AIRBUS, 2006 All rights reserved ### Page 51 (OCR) A300-600 SERVICE BULLETIN Continuation of sheet 3 DIA (0?531in.) 13.5mm Crack L2 > 0.4mm Crack L2 ≤ 0.4mm (0.016in.) (0.016in.) Cut fitting as out external per Drill 815mm (0539) • max. Fig; thru 15 sheets 3 and do rotating probe L1 ≤ 5mm inspection as per (0.196in.) NTM 57-10-50 L2 5mm Part 6. procedure A. (0.196in.) L1 > 5mm (0.196in.) No crack Chamfering Residual 10x10mm max. crack Contact AI (0.393x0.393in.) Install oversize for inspection as per fastener program and sheet Ref. Para. 3.C. (2) (c) repair action Do inspection • as per Perform PR sealing NTM 57-10-50, Part 6, procedure B DO subsequent inspections at intervals give Residual crack in Para. = 12 Contact AI Before next flight See B sheet Install fasteners and conical ring with Mat. No. 09-005. Ref. Fig. 133 C. (2). (d) sheet and para. Do subsequent Inspections at intervals Iven Do subsequent inspection in Para. 1.E. (2) at intervals Para. 1.E. (2) per ASB5 576049 AG 00 d Perform PR sealing Crack No crack If the removed fastener is not damaged, this can be new instered of Contact AI install new fastener Before same type. 3. C.(2)(d) next flight Ref. Para. Figure 2 Sheet 4 Flow Chart (Config. 01 or 02 or 03) DATE : Sep 09/94 SERVICE BULLETIN No. : A300-57-6049 REVISION No. : 07 - Dec 22/06 Page : 44 Printed in FRANCE © AIRBUS, 2006 All rights reserved ### Page 52 (OCR) A300-600 SERVICE BULLETIN Hole K and N: do the rotating probe inspection NTM 57-10-50. Part procedure A of apply and holes, Service intervals (Mod. No. on artern angle at Bulletin as per 10454520572). No. at threshold A300-57-6050 1.E. (2) or THIS INSPECTION OF HOLE K AND N ON FR47 VIEW ONE LAYER SHOWS ONLY (L] = L2) Remove PR sealant around fastener, use exclusively a non-metallic spatula in the event of scratches, polish surface and perform protection. Remove fastener and clean CRACK bore with Mat. 11-026. * For A/C config No. 02 (SB A300-57-6050 Check bore diameter Mod. 10454S20572 (nominal diameter accomplished): or R1 or R2 oversize). contact AI Contact AI Perform rotating oprables spection Before in all the layers and next flight DIA: 14.3mm Cracks no (0.562in.) DIA (0.562in.) 14.3mm Contact AI Before nominal fastener removed is next flight not damaged, this fastener can be re-installed. GO to If replace the fastener it 3.C.(3) (a) or (b) new is damaged, same fastener. sheet 6 Ref. Para. ASB5 576049 AH 00 d subsequent inspections intervals gIven Perform PR sealing in Para. 1.E. (2) Figure 2 Sheet 5 Flow Chart (Config. 01 or 02 or 03) DATE : Sep 09/94 SERVICE BULLETIN No. : A300-57-6049 REVISION No. : 07 - Dec 22/06 Page : 45 Printed in FRANCE © AIRBUS, 2006 All rights reserved ### Page 53 (OCR) © A300-600 SERVICE BULLETIN Continuation of sheet 5 DIA 00.5621.3mm Crack L2 > 0.8mm Crack L2 ≤ 0.8mm (0.031in.) (0.031in.) Ream hole, step by Contact Al dimension, (0.562in.) step to oversize max. dia. next flight Before and per tain 51-10-50 14.3mm do a inspection Part 6. procedure Residual crack no Install oversize fasteners Ref. Para 3.C. (3) (c) Perform PR sealing ASB5 576049 AI 00 d DO subsequent inspections SEE C SHEET 5 at intervals given in Para. 1.E. (2) Figure 2 Sheet 6 Flow Chart (Config. 01 or 02 or 03) DATE : Sep 09/94 SERVICE BULLETIN No. : A300-57-6049 REVISION No. : 07 - Dec 22/06 Page : 46 Printed in FRANCE © AIRBUS, 2006 All rights reserved ### Page 54 (OCR) A300-600 SERVICE BULLETIN Hole L and M: do the rotating probe inspection NTM 57-10-50. Part 6. procedure A of apply and holes, Service intervals (Mod. No. on artern angle at Bulletin as per 10454520572). No. at threshold A300-57-6050 1.E. (2) or THIS INSPECTION OF HOLE L AND M VIEW ONE LAYER ON FR47 SHOWS ONLY (L] = L2) Remove PR sealant around fastener, D use exclusively a non-metallic spatula in the event of scratches, polish surface and perform protection. Remove fastener and clean CRACK bore with Mat. 11-026. * For A/C config No. 02 (SB A300-57-6050 Check bore diameter Mod. 10454S20572 (nominal diameter accomplished): or R1 or R2 oversize). contact AI Contact AI Perform rotating oprable inspection Before in all the layers and next flight Cracks no DIA. ≥ 13.5mm (0.531in.) DIA (0?531іn.) 13.5mm Contact AI Before nominal fastener removed is next flight not damaged, this fastener can be re-installed. If the fastener is damaged GO to replace Caro. 3.c.(4).(8)0r (b) new same fastener. sheet 8 Ref. ASB5 576049 AJ 00 d subsequent inspections intervals giver Perform PR sealing in Para. 1.E. (2 Figure 2 Sheet 7 Flow Chart (Config. 01 or 02 or 03) DATE : Sep 09/94 SERVICE BULLETIN No. : A300-57-6049 REVISION No. : 07 - Dec 22/06 Page : 47 Printed in FRANCE © AIRBUS, 2006 All rights reserved ### Page 55 (OCR) © A300-600 SERVICE BULLETIN Continuation of sheet 7 DIA. (0.531in.) 13.5mm Crack L2 > 0.4mm Crack L2 ≤ 0.4mm (0.016in.) (0.016in.) Ream hole, step by Contact Al dimension, (0.531in.) step to oversize max. dia. 13.5mm next flight Before and -otatino do a inspection per Part procedure Residual crack no Install oversize fasteners Ref. Par a 3.C (4). (c) Perform PR sealing ASB5 576049 AK 00 d Do subsequent inspections SEE D SHEET 7 at intervals given in Para. 1.E.(2) Figure 2 Sheet 8 Flow Chart (Config. 01 or 02 or 03) DATE : Sep 09/94 SERVICE BULLETIN No. : A300-57-6049 REVISION No. : 07 - Dec 22/06 Page : 48 Printed in FRANCE © AIRBUS, 2006 All rights reserved ### Page 56 (OCR) A300-600 SERVICE BULLETIN Hole U: V. W, X' inspection Y: do the rotating probe NTM 57-10-50. Part 6. procedure A of holes, on artern an eat at threshold and intervals as per 1.E. (2) or apply Service Bulletin No. A300-57-6050 (Mod. No. 10454520572). Remove PR sealant around fastener, use exclusively a non-metallic spatula in the event of scratches, polish surface and perform protection. Remove fastener and clean bore with Mat. 11-026. Check bore diameter (nominal diameter or R1 or R2 oversize). Perform in all the rotating v. W. layers X and probe of Y. inspection holes U. Contact Al next Before flight Cracks DIA (0 531in.) 13.5mm Contact Before next flight nominal fastener removed is not damaged, this fastener can be re-installed. If the fastener is damaged, ASB5 576049 BO 00 d replace it by new same fastener. Ref. Para. 3.C.(5). (a)or (b) Do subsequent inspections at intervals giver Perform PR sealing in Para. 1.E. (2) Figure 2 Sheet 9 Flow Chart (Config. 01 or 02 or 03) DATE : Sep 09/94 SERVICE BULLETIN No. : A300-57-6049 REVISION No. : 07 - Dec 22/06 Page : 49 Printed in FRANCE © AIRBUS, 2006 All rights reserved ### Page 57 (OCR) A300-600 SERVICE BULLETIN do the rotating Part Probe inspection Hole H: NTM 57-10-50. procedure of INSPECTION OF HOLE H hole Hintervals internal angle threshold ON FR47. and as per Para. 1.E. (2). THIS VIEW SHOWS ONLY ONE LAYER. (L1 L2) _L1 Remove PR sealant around fastener, use exclusively non-metallic spatula in the event of scratches, polish surface and perform protection. Remore with eat. and clean CRACK bore with 11-026. Check bore diameter (nominal diameter or R1 or R2 oversize). Contact Al Perform rotating probe inspection Before in all the layers of hole H next flight Cracks DIA (0.499іп.) 12.7mm Go to sheet 2 nominal fastener removed is not damaged, this fastener can De re-installed. the fastener is damaged, replace it by fastener new same fastener. R1 or R2 is removed, ASB5 576049 AL 00 d Ref. Paro. 3.C. (6) (a) Fastener. Ref. Para. Do subsequent inspections at intervals given Perform PR sealing Para. 1.E. (2) Figure 3 Sheet 1 Flow Chart (Config. 04) DATE : Sep 09/94 SERVICE BULLETIN No. : A300-57-6049 REVISION No. : 07 - Dec 22/06 Page : 50 Printed in FRANCE © AIRBUS, 2006 All rights reserved ### Page 58 (OCR) A300-600 SERVICE BULLETIN Continuation of sheet 1 es Cracks ye: DIA. ≥ 12.7mm (0.499in.) Contact AI Before next flight Crack L2 > 1.6mm Crack L2 ≤ 1.6mm (0.062in.) (0.062in.) Ream hole, step by Contact AIB dimension, (0.499in.) step oversize max. dia. next flight Before and 12.7mm rotating do a inspection probe as Part 6. procedure NTM ocedure A Residual crack Install oversize fasteners Ref. (6)(b) paro 3.C. ASB5 576049 AM 00 d Do Perform PR sealing subsequent inspections SEE A SHEET 1 at intervals giver in Para. 1.E. (2) Figure 3 Sheet 2 Flow Chart (Config. 04) DATE : Sep 09/94 SERVICE BULLETIN No. : A300-57-6049 REVISION No. : 07 - Dec 22/06 Page : 51 Printed in FRANCE © AIRBUS, 2006 All rights reserved ### Page 59 (OCR) A300-600 SERVICE BULLETIN Hole I: INSPECTION OF HOLE I the rotating probe inspection ON FR47 WITH NTM 57-10-50. Part procedure A of FITTING REMOVED hole 'intervals internal angle threshold THIS VIEW SHOWS ONLY and per Para. 1.E.(2). ONE LAYER Remove sealant around fastener, use exclusively non-metallic spatula the event of scratches, polish surface and perform protection. CRACK Remove fastener and clean bore with Mat. 11-026. Check bore diameter (nominal diameter or R1 or oversize). Perform rotating probe inspection in all the layers of hole Take care during the inspection of the Contact AI hole due to the possibility to have a Before wrong value. (see figure 8). next flight Cracks DIA (Ở.529in.) 13.44mm es DIA: (Ó.529in.) 13.44mm Contact Al Except for the first time of this Before inspection accomplishment, a new same next flight fastener can first spection be ASB5 576049 AN 00 d GO to If drill oversize hole direand it is the higher on the with aircraft, sheet 4 moderate Interterence 9000 tolerance. Install fastener Ref. Para. 3.C.(7)(a) Do subsequent inspections at in Para. intervals S.E. (2)г Perform PR sealing Figure 3 Sheet 3 Flow Chart (Config. 04) DATE : Sep 09/94 SERVICE BULLETIN No. : A300-57-6049 REVISION No. : 07 - Dec 22/06 Page : 52 Printed in FRANCE © AIRBUS, 2006 All rights reserved ### Page 60 (OCR) A300-600 SERVICE BULLETIN Continuation of sheet 3 DIA. (0.529 in.) 13:44mm Crack L2 > 0.4mm Crack L2 ≤ 0.4mm (0.016in.) (0.016in.) Cut out external Drill oversize stelia fitting as per step to • max. Fig; thru 15 13.44mm (0.529in.) sheets 3 and do rotating probe L1 ≤ 5mm inspection as per (0.196in.) NTM 57-10-50 L2 5mm Part 6. proceduré A (0.196in.) L1 > 5mm (0.196in.) No crack Chamfering Residual 10x10mm max crack for Contact inspection (0.393x0.393in.) as per Install fastener oversize program and sheet Ref. Para. 3.C. (7)(b) repair action Do inspection as per Perform PR sealing NTM 57-10-50, Part 6, procedure B DO subsequent inspections at intervals giver Residual crack in Para. = 12 Contact AI Before next flight See B sheet Install ringpet. with fasteners Mat. No. and 09-005. conical Fig. 15 sheet and Para. 3.C.(7) (c) Do subsequent Inspections at intervals Iven Do subsequent inspection in Para. 1.E. (2) at intervals Paro. I.E.(2) per ASB5 576049 AO 00 d Perform PR sealing Crack No crack If the removed fastener is not damaged, this can be re-installed, of Contact Al install new fastener Before same type. 3. C. (7)(c) next flight Ref. Para. Figure 3 Sheet 4 Flow Chart (Config. 04) DATE : Sep 09/94 SERVICE BULLETIN No. : A300-57-6049 REVISION No. : 07 - Dec 22/06 Page : 53 Printed in FRANCE © AIRBUS, 2006 All rights reserved The text continues at https://openairdocs.org/service-documents/airbus/a300-57-6049/file/b6c590234fb5.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.