# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORY MANDATORY MANDATORY ATA SYSTEM: 57 

## TITLE: WINGS - INSPECTION OF CENTER WING BOTTOM SKIN CORROSION AT RIB 1 MODIFICATION No.: None This page transmits Revision No.06 of Service Bulletin No.A300-57-6047 ADDITIONAL WORK **CONF ALL REASON Revision No. 06 issued to delete reference to MPD 571066 and to modify the threshold and Interval. CHANGES SUMMARY MODIFICATIONS Minor editorial or document structure change N REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES Minor editorial or document structure change N GENERAL EVALUATION Minor editorial or document structure change N MATERIAL PRICE INFORMATION Minor editorial or document structure change N EFFECTIVITY Minor editorial or document structure change N CONCURRENT REQUIREMENTS Minor editorial or document structure change N REFERENCES / REPERCUSSIONS Minor editorial or document structure change N NATURE OF THE WORK Minor editorial or document structure change N MANPOWER Minor editorial or document structure change N APPENDICES Minor editorial or document structure change N Fig. A-FSAAA Minor editorial or document structure change N Fig. A-FSAAA Sheet 01 Minor editorial or document structure change N PLANNING INFORMATION EFFECTIVITY Minor editorial or document structure change N Configuration definition Minor editorial or document structure change N CONF 001 Minor editorial or document structure change N DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 1 5

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Material Effectivity Minor editorial or document structure change N Minor editorial or document structure change N CONCURRENT REQUIREMENTS Minor editorial or document structure change N REASON Minor editorial or document structure change N History Minor editorial or document structure change N Objective/Action Minor editorial or document structure change N Advantages Minor editorial or document structure change N Operational/Maintenance Consequences Minor editorial or document structure change N DESCRIPTION Minor editorial or document structure change N COMPLIANCE Minor editorial or document structure change N Classification Minor editorial or document structure change N Accomplishment Timescale Minor editorial or document structure change N APPROVAL Minor editorial or document structure change N Minor editorial or document structure change N MANPOWER Minor editorial or document structure change N Minor editorial or document structure change N WEIGHT AND BALANCE Minor editorial or document structure change N ELECTRICAL LOAD DATA Minor editorial or document structure change N REFERENCES Minor editorial or document structure change N Minor editorial or document structure change N PUBLICATION AFFECTED Minor editorial or document structure change N Minor editorial or document structure change N INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N SPARES Minor editorial or document structure change N MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Minor editorial or document structure change N Procurement Addresses Minor editorial or document structure change N Price and Availability Minor editorial or document structure change N INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N LIST OF COMPONENTS Minor editorial or document structure change N LIST OF MATERIALS - OPERATOR SUPPLIED Minor editorial or document structure change N Consumable Materials Minor editorial or document structure change N Consumable CMLA01 Minor editorial or document structure change N Components Minor editorial or document structure change N Equipment Minor editorial or document structure change N PARTS TO BE RE-IDENTIFIED BY OPERATOR Minor editorial or document structure change N TOOLING Minor editorial or document structure change N Tooling - Price and Availability Minor editorial or document structure change N
DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 2 5

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Tools Minor editorial or document structure change N Special Tools Minor editorial or document structure change N ACCOMPLISHMENT INSTRUCTIONS TASK 576047- 832-801-001-Inspection Minor editorial or document structure change N Task associated data - 001 Minor editorial or document structure change N Subtask 576047-839-001-001 Minor editorial or document structure change N Subtask 576047-910-001-001 Minor editorial or document structure change N Subtask 576047-941-001-001 Minor editorial or document structure change N Subtask 576047-832-001-001 Minor editorial or document structure change N Subtask 576047-832-006-001 Minor editorial or document structure change N Subtask 576047-832-002-001 Minor editorial or document structure change N Subtask 576047-832-003-001 Minor editorial or document structure change N Subtask 576047-833-003-001 Minor editorial or document structure change N Subtask 576047-833-004-001 Minor editorial or document structure change N Subtask 576047-833-006-001 Minor editorial or document structure change N Subtask 576047-833-005-001 Minor editorial or document structure change N Subtask 576047-833-001-001 Minor editorial or document structure change N Subtask 576047-833-002-001 Minor editorial or document structure change N Subtask 576047-700-001-001 Minor editorial or document structure change N Subtask 576047-942-002-001 Minor editorial or document structure change N Fig. A-FBAAA Minor editorial or document structure change N Fig. A-FBAAA Sheet 01 Minor editorial or document structure change N Fig. A-FFAAA Minor editorial or document structure change N Fig. A-FFAAA Sheet 01 Minor editorial or document structure change N Fig. A-FFAAA Sheet 02 Minor editorial or document structure change N Fig. A-FBBAA Minor editorial or document structure change N Fig. A-FBBAA Sheet 01 Minor editorial or document structure change N Fig. A-FBCAA Minor editorial or document structure change N Fig. A-FBCAA Sheet 01 Minor editorial or document structure change N Fig. A-FBGAA Minor editorial or document structure change N Fig. A-FBGAA Sheet 01 Minor editorial or document structure change N Fig. A-FBDAA Minor editorial or document structure change N Fig. A-FBDAA Sheet 01 Minor editorial or document structure change N Fig. A-FBEAA Minor editorial or document structure change N Fig. A-FBEAA Sheet 01 Minor editorial or document structure change N Fig. A-FBEAA Sheet 02 Minor editorial or document structure change N Fig. A-FBEAA Sheet 03 Minor editorial or document structure change N Fig. A-FBFAA Minor editorial or document structure change N Fig. A-FBFAA Sheet 01 Minor editorial or document structure change N Fig. A-FBFAA Sheet 02 Minor editorial or document structure change N
DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 3 5

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Appendix 1- Inspection Report - APPENDIX CONTENT Minor editorial or document structure change N Fig. A-FRAAA Minor editorial or document structure change N Fig. A-FRAAA Sheet 01 Minor editorial or document structure change N Fig. A-FRAAA Sheet 02 Minor editorial or document structure change N Fig. A-FRAAA Sheet 03 Minor editorial or document structure change N Fig. A-FRAAA Sheet 04 Minor editorial or document structure change N Fig. A-FRAAA Sheet 05 Minor editorial or document structure change N Fig. A-FRAAA Sheet 06 Minor editorial or document structure change N Fig. A-FRAAA Sheet 07 Minor editorial or document structure change N Fig. A-FRAAA Sheet 08 Minor editorial or document structure change N Appendix 2- Repair Report - APPENDIX CONTENT Minor editorial or document structure change N Fig. A-FRBAA Minor editorial or document structure change N Fig. A-FRBAA Sheet 01 Minor editorial or document structure change N Fig. A-FRBAA Sheet 02 Minor editorial or document structure change N Fig. A-FRBAA Sheet 03 Minor editorial or document structure change N Fig. A-FRBAA Sheet 04 Minor editorial or document structure change N FILLING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS Revision No. 01 issued to clarify the permissable limits of rework and to update the effectivity. Revision No. 02 issued to inform the operators that the compliance has changed into mandatory and update the effectivity. Revision No. 03 issued to add aircraft model C4-605R/F, aircraft MSN 775 and 788 for customer CAL and aircraft 797 for customer JAS. Revision No. 04 issued to add customers AHK and UPS, to delete MSN 420 and 374, to add MSN 836, 837, 838 and to modify the Figure 4, Table B. Revision No. 05 issued to modify the Para. Pub. affected, to update the effectivity and to limit the effectivity as aircraft post production modification 10599S20695 (FUSELAGE - FUSELAGE CENTER SECTION - WING FUSELAGE JUNCTION - PROVIDE WET INSTALLATION OF FASTENERS) are now inspected as per MRBR task 571066, to update the Para. Approval and to modify the Figure 4. REVISION SEQUENCE ORIGINAL: Jan 04/96 DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 4 5

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET REVISION No.: 01 - Oct 16/96 REVISION No.: 02 - Apr 02/99 REVISION No.: 03 - Sep 28/99 REVISION No.: 04 - Mar 01/05 REVISION No.: 05 - May 27/08 REVISION No. : 06 - Oct 17/11

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 5 5

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 6 5

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# @A300-600 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft. 

# MANDATORY MANDATORY MANDATORY ATA SYSTEM: 57 

## TITLE: WINGS - INSPECTION OF CENTER WING BOTTOM SKIN CORROSION AT RIB 1 **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES Eight operators of A300 aircraft have reported 20 cases of corrosion on the lower wing root joint during scheduled maintenance. The aircraft have been in-service between 4 and 10 years. The corrosion was located in the wing bottom skin inboard and outboard of the external lower surface splice. One operator of an A310 aircraft has also reported severe corrosion in the same area. Most of the corrosion was found in the area aft of FR 43 and initiated at the edge of the countersinks of the fasteners. For A300 aircraft, no similar incidents have been reported by the operators. Most of the corrosion was found in the area aft of FR 43, althought corrosion has also been found forward of this area. The corrosion initiated at the edge of the contersinks of the fasteners. This Service Bulletin recommends a detailed visual inspection of the rib 1 external lower surface splice, between FR 40 and FR 47. Repair of the corrosion damage is by local blend-out and spotfacing. Once the corrosion has been removed, if the corrosion damage exceeds a certain limit, there would be a reduction in strenght margins, which could lead to cracking from the fastener holes. Non Destructive Testing or detailed visual inspections are then necessary to detect the presence of cracks around the fastener holes. A fatigue program inspection has been developed in this Service Bulletin to cover this possibility. Accomplishement of this Service Bulletin permits detection of corrosion in the wing bottom skin at an early stage. This will avoid extensive corrosion damage, resulting in extensive rework and/or repairs and possible fatigue cracks in the future.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 1 5

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# @A300-600 SERVICE BULLETIN SUMMARY This inspection is recommended at a threshold of 5 years, with a repetitive inspection of 5 years. For aircraft exceeding 5 years, the first inspection is to be performed within 6 months after receipt of this Service Bulletin. After corrosion removal, a repetitive inspection for possible fatigue damaged is recommended. The thresholds and intervals given for the fatigue inspection depend on the results of the corrosion inspection. Previous issue of this Service Bulletin was rendered mandatory by Airworthiness Directive No. 2008-0208R1. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) 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 YES VENDOR SB INVOLVED NO NOTE (1) : Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION No Material EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

30T 83V AAL ABD AIB AMU BCS CES F2I FDX G8E IRA IRM JAL KAC KAL MON MSR OHY QTR RNV SUD TAR THA UZB CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 53.15.00.021 OEB None AOT None SIL 38-013 LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 2 5

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# @A300-600 SERVICE BULLETIN SUMMARY SOFT NO OBRM NO MANPOWER Task 576047-832-801-001: Inspection TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 3.75 APPENDICES Appendix 1- Inspection Report - Appendix 2- Repair Report -

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 3 5

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# @A300-600 SERVICE BULLETIN SUMMARY
**CONF ALL 

# A

**B**

FR40 FR47 RIB1 AREAS TO INSPECT

PICK−UP ANGLE

INBOARD AREA OUTBOARD AREA EXTERNAL LOWER SURFACE SPLICE 

# B

D_SB_576047_5_SAAA_01_00 

# A **A**

Figure A-F SAAA - S heet 01
DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 4 5

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# @A300-600 SERVICE BULLETIN AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORY MANDATORY MANDATORY ATA SYSTEM: 57 

## TITLE: WINGS - INSPECTION OF CENTER WING BOTTOM SKIN CORROSION AT RIB 1 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 prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY (1) Models B4-603 B4-605R B4-620 B4-622 B4-622R C4-620 (2) Effectivity by MSN 0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 0358 0361 0365 0380 0388 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 0602-0615 0617-0618 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 (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 1 5

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# @A300-600 SERVICE BULLETIN
OPERATOR MSN 30T 0626 0643 83V 0423 0459 0460 0463 0466 0470 0474 0510 0511 0512 0615 0639 0675 AAL 0517 0612 ABD 0529 0557 AIB 0507 0508 0515 AMU 0677 BCS 0621 0637 0641 0670 0679 0711 CES 0521 0525 0532 0707 F2I 0284 0294 0301 0307 0312 0317 0321 0336 0348 0351 0461 0518 0606 0610 0645 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 G8E 0462 0465 0469 0506 0509 0513 0514 0516 IRA 0632 0696 IRM 0380 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701 JAL 0602 0617 0683 0703 KAC 0344 0673 0694 0699 0719 0721 KAL 0582 0609 0627 0631 0662 0685 0692 MON 0540 0556 0604 0605 MSR 0561 0607 OHY 0584 0603 QTR 0554 0560 0614 RNV 0464 SUD 0666 TAR 0505 0558 0563 THA 0566 0569 0577 0628 0629 0635 0681 0705 UZB 0717 (4) Configuration by MSN MSN CONFIGURATION 0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0423 0459 0460 0461 0462 0463 0464 0465 0466 0469 0470 0474 0477 0479 0505 0506 0507 0508 0509 0510 0511 0512 0513 0514 0515 0516 0517 0518 0521 0525 0529 0530 0532 0536 0540 0543 0546 0553 0554 0555 0556 0557 0558 0559 0560 0561 0563 0566 0569 0572 0575 0577 0579 0581 0582 0584 0602 0603 0604 0605 0606 0607 0608 0609 0610 0611 0612 0613 0614 0615 0617 0618 0621 0623 0625 0626 0627 0628 0629 0630 0631 0632 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 001

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 2 5

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# @A300-600 SERVICE BULLETIN (5) Configuration definition **CONF 001 Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Consumable CMLA01 1 Consumable CMLA02 1 Consumable CMLA03 1 Consumable CMLA04 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History Eight operators of A300 aircraft have reported 20 cases of corrosion on the lower wing root joint during scheduled maintenance. The aircraft have been in-service between 4 and 10 years. The corrosion was located in the wing bottom skin inboard and outboard of the external lower surface splice. One operator of an A310 aircraft has also reported severe corrosion in the same area. Most of the corrosion was found in the area aft of FR 43 and initiated at the edge of the countersinks of the fasteners. For A300 aircraft, no similar incidents have been reported by the operators. Most of the corrosion was found in the area aft of FR 43, althought corrosion has also been found forward of this area. The corrosion initiated at the edge of the contersinks of the fasteners. (2) Objective/Action This Service Bulletin recommends a detailed visual inspection of the rib 1 external lower surface splice, between FR 40 and FR 47. Repair of the corrosion damage is by local blend-out and spotfacing. Once the corrosion has been removed, if the corrosion damage exceeds a certain limit, there would be a reduction in strenght margins, which could lead to cracking from the fastener holes. Non Destructive Testing or detailed visual inspections are then necessary to detect the presence of cracks around the fastener holes. A fatigue program inspection has been developed in this Service Bulletin to cover this possibility.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 3 5

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# @A300-600 SERVICE BULLETIN (3) Advantages Accomplishement of this Service Bulletin permits detection of corrosion in the wing bottom skin at an early stage. This will avoid extensive corrosion damage, resulting in extensive rework and/or repairs and possible fatigue cracks in the future. (4) Operational/Maintenance Consequences This inspection is recommended at a threshold of 5 years, with a repetitive inspection of 5 years. For aircraft exceeding 5 years, the first inspection is to be performed within 6 months after receipt of this Service Bulletin. After corrosion removal, a repetitive inspection for possible fatigue damaged is recommended. The thresholds and intervals given for the fatigue inspection depend on the results of the corrosion inspection. Previous issue of this Service Bulletin was rendered mandatory by Airworthiness Directive No. 2008-0208R1. D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 576047-832-801-001: Inspection (1) Do a Detailed Inspection of rib 1 between FR40 and FR47 (2) Do a Detailed Inspection of the Protection (3) Do a Detailed Inspection of the rework depth of rib 1 between FR40 and FR47 (4) Do a Non Destructive Test of rib 1 between FR40 and FR47 (5) Do a Surface Treatment for a New Protection Coating (6) Remove the corrosion of rib 1 between FR40 and FR47 (7) Do a Surface Treatment for a New Protection Coating ( D =< 5% ) (8) Do a Surface Treatment for a New Protection Coating ( 5% < D =< d ) (9) Replace the Fasteners (10) Do the Sealing E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 4 5

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# @A300-600 SERVICE BULLETIN (2) Accomplishment Timescale Condition Action Compliance Time Repetitive Interval Config.001 Do a Detailed Inspection of rib 1 between FR40 and FR47, refer to subtask 576047-832-001-001 See Note (1) In 5 years
Corrosion is not detected and the protection is not missing or damaged Do a repeat Inspection for corrosion In 5 years None Corrosion is not detected and the protection is missing or damaged Do a Surface Treatment for a New Coating, Refer to Subtask 576047-833-003-001 and Do the Sealing, Refer to Subtask 576047-833-002-001 Before next flight None

Corrosion is detected Remove the corrosion of rib 1 between FR40 and FR 47, Refer to Subtask 576047-833-004-001 See Note (2) Before next flight None

The rework is not the permissible limits Contact AIRBUS Before next flight None The reworked depth (D) is higher than permissible limit of the reworked depth per area (d) Contact AIRBUS Before next flight None
The reworked depth (D) is less or equal to 5 % of the initial thickness of the panel (E) Do a Surface Treatment for a New Protection Coating (5% =< D), Refer to Subtask 576047-833-006-001 and Do the Sealing, Refer to Subtask 576047-833-002-001 Before next flight None

The reworked depth (D) is higher than 5 % of the initial thickness of the panel (E) and less or equal to the permissible limit of the reworked depth per area (d) and cracks are not detected Do a Surface Treatment for a New Protection Coating (5% < D =< d), Refer to Subtask 576047-833-005-001 and Inspect for fatigue damage: Refer to Fig.A-BGAA Sheet 01 and Do the Sealing, Refer to Subtask 576047-833-002-001, See Note(3) Before next flight None

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 5 5

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# @A300-600 SERVICE BULLETIN
Condition Action Compliance Time Repetitive Interval The reworked depth (D) is higher than 5 % of the initial thickness of the panel (E) and less or equal to the permissible limit of the reworked depth per area (d) and cracks are detected Contact AIRBUS Before next flight None

Table 1, Detailed Inspection of rib 1 between FR40 and FR47 NOTE (1) : The corrosion inspection is to be done on aircraft which have been in service for 5 years or more from the date of delivery. The inspection must be repeated every 5 years. Aircraft that have been in service more than 5 years should be inspected within the timescales given below : - Aircraft with more than 5 years but less than 15 years service should be inspected not later than 18 months from receipt of this Service Bulletin, or at the next C-check, whichever occurs last. - Aircraft with more than 15 years but less than 20 years service should be inspected not later than 12 months from receipt of this Service Bulletin. - Aircraft with more than 20 years service since delivery should be inspected within 6 months from receipt of this Service Bulletin. NOTE (2) : If you find corrosion around the fasteners remove and replace the fasteners, Refer to SUBTASK 576047-833-001-001 NOTE (3) : A grace period of 500FC / 1050FH is granted to aircraft which have exceeded the revised threshold / intervals after receipt of the SB without exceeding previous SB revision value. F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approv al 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.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 6 5

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# @A300-600 SERVICE BULLETIN G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. Task 576047-832-801-001: Inspection Get Access 0.50 On Aircraft Do a Detailed Inspection of rib 1 between FR40 and FR47 0.25 Do a Detailed Inspection of the Protection 0.25 Do a Detailed Inspection of the rework depth of rib 1 between FR40 and FR47 0.50 Do a Non Destructive Test of rib 1 between FR40 and FR47 0.50 Do a Surface Treatment for a New Protection Coating 0.50 Remove the corrosion of rib 1 between FR40 and FR47 0.50 Do a Surface Treatment for a New Protection Coating ( D =< 5% ) 0.50 Do a Surface Treatment for a New Protection Coating ( 5% < D =< d ) 0.50 Replace the Fasteners 1.50 Do the Sealing 1.00 Close-Up 1.00 TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 3.75 H. WEIGHT AND BALANCE None I. ELECTRICAL LOAD DATA None

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 7 5

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# @A300-600 SERVICE BULLETIN J. REFERENCES

Airworthiness Directive (AD) Airworthiness Directive No. 2008-0208R1 Aircraft Maintenance Manual (AMM) 12-11-28 24-00-00 24-41-00 28-00-00 28-10-00 28-11-22 28-25-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-04 51-10-05 51-10-08 Structural Repair Manual (SRM) 51-22-00 51-23-00 51-23-10 51-23-20 51-40-20 51-40-21 51-40-40 51-40-44 51-40-46 51-40-47 51-43-00 51-49-00 51-74-10 51-75-20 51-76-10 51-76-20 53-23-20 K. PUBLICATION AFFECTED None L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 8 5

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# @A300-600 SERVICE BULLETIN 2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses None (2) Price and Availability None B. INDUSTRY SUPPORT INFORMATION No Material Set C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfid(no Longeravailable 09-002 As required Corrosion Inhibitingsealant Sprayable 09-025 As required Anti-Corrosion Primer (polyurethane) 16-001 As required Wash Primer 16-020 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 9 5

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# @A300-600 SERVICE BULLETIN F. TOOLING (1) Tooling - Price and Availability None (2) Tools To accomplish this Service Bulletin it is necessary to use the tools listed in NTM and SRM tasks mentioned in paragraphs: - Equipment and materials for inspection, refer to NTM 51-10-04, NTM 51-10-05 and NTM 51-10-08. - Equipment and tools for repair, refer to SRM 51-40-21, SRM 51-40-44, SRM 51-40-47, SRM 51-43-00and SRM 51-74-10. (3) Special Tools None

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 10 5

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# @A300-600 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 576047-832-801-001 - Inspection 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. Task Associated Data Zone 541 641 Manpower TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 3.75 A. GENERAL (1) Subtask 576047-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. (2) Subtask 576047-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 11 5

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# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-23-00 51-23-10 51-23-20 51-40-20 51-40-21 51-40-40 51-40-44 51-40-46 51-40-47 51-49-00 51-75-20 (a) If paint stripping is required (Refer to SRM 51-75-20). (b) To drill and deburr the holes (Refer to SRM 51-40-40 and SRM 51-40-44). (c) Countersinking (Refer to SRM 51-40-46 and SRM 51-40-47). (d) Data for installation and removal fasteners (Refer to SRM 51-40-20 and SRM 51-40-21). (e) To torque standard threaded fasteners (Refer to SRM 51-49-00). (f) If paint coating is required (Refer to SRM 51-23-00, SRM 51-23-10 and SRM 51-23-20). B. PREPARATION (1) Subtask 576047-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00 28-00-00, Page Block 301 28-10-00, Page Block 301 28-11-22, Page Block 401 28-25-00, Page Block 301 (a) De-energize the aircraft electrical network and connect the aircraft to ground (Refer to AMM 24-41-00 and AMM 24-00-00, Page Block 301). (b) Put the access platforms in position.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 12 5

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# @A300-600 SERVICE BULLETIN WARNING : TO REPLACE THE FASTENERS, DRAIN THE CENTER AND INNER FUEL TANKS. BEFORE UNDERTAKING MAINTENANCE WORK ON THE FUEL SYSTEM, PERSONNEL MUST RIGOROUSLY OBSERVE THE FOLLOWING SAFETY PRECAUTIONS. THE DESCRIPTIONS SHOULD BE READ AT THE SAME TIME AS THE SPECIAL INSTRUCTIONS AND SAFETY MEASURES CONCE RNING SPECIFIC MAINTENANCE PROCEDURES AND, IN PARTICULAR, THE FOLLOWING OPERATIONS : NOTE : The operations below are necessary only if the fasteners are removed, refer to SUBTASK 576047-833-001 001 Replace the Fasteners . 1 General servicing precaution (Refer to AMM 28-00-00, Page Block 301). 2 Tank defueling (Refer to AMM 28-25-00, Page Block 301). 3 Access to fuel tanks (Refer to AMM 28-10-00, Page Block 301). 4 Manhole cover removal the 541AB, 542 CB, 641AB and 642CB (Refer to AMM 28-11-22, Page Block 401). 5 Fuel tank working area (Refer to AMM 28-10-00, Page Block 301). 6 Use of flammable gas detection devices (Refer to AMM 28-10-00, Page Block 301). 7 Fuel tank ventilation (Refer to AMM 28-10-00, Page Block 301). C. PROCEDURE (1) Subtask 576047-832-001-001 - Do a Detailed Inspection of rib 1 between FR40 and FR47 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC (a) At the threshold given in the Planning Information Paragraph E.(2) : On the center wing bottom skin, inboard and outboard areas of rib 1 between frames 40 and 47, do a Detailed Inspection for corrosion around the fasteners and on the surface of panels without stripping off paint. 1 If no corrosion is detected : - Check condition of paint finish, touch up if necessary, refer to SUBTASK 576047-832-006 001 Do a Detailed Inspection of the Protection .

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 13 5

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# @A300-600 SERVICE BULLETIN
2 If corrosion is detected : - Refer to SUBTASK 576047-833-004 001 Remove the corrosion of rib 1 between FR40 and FR47 . (2) Subtask 576047-832-006-001 - Do a Detailed Inspection of the Protection Work Zones and Access Panels Zone Access/Work location 541 Work location from Frame 40 to Frame 47 641 Work location from Frame 40 to Frame 47 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC (a) If protection is missing or damaged : - Refer to SUBTASK 576047-833-003 001 Do a Surface Treatment for a New Protection Coating . (b) If protection is not missing or not damaged : - Next Visual inspection for corrosion in 5 years. (3) Subtask 576047-832-002-001 - Do a Detailed Inspection of the rework depth of rib 1 between FR40 and FR47 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC References Non Destructive Test Manual (NTM) 51-10-08 part 6 Structural Repair Manual (SRM) 51-23-00 51-23-10 53-23-20 Fig. A-FBCAA Permissible Limits of the Reworked Depth Sheet 01 Fig. A-FBGAA Inspection Program Sheet 01 NOTE : At the threshold given in the Planning Information Paragraph E.(2) : In this part of the inspection, the reference value is reworked depth (D) DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 14 5

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# @A300-600 SERVICE BULLETIN (result of corrosion inspection, SUBTASK 576047-832-001 001 Do a Detailed Inspection of rib 1 between FR40 and FR47 . The permissible limits (5%, d) are reference values with respect to the initial thickness of the panel (E). Permissible limit of reworked depth (D), 5% of the initial thickness of the panels (E), permissible limit of reworked depth per area (d) : Refer to Fig. A-FBCAA Sheet 01 Check the reworked depth (D) with respect to the initial thickness of the panel (E), and the permissible limit of the reworked depth per area (d) previously defined. NOTE : According to damaged areas, permissible limits of the reworked depth are specified : Refer to Fig. A-FBCAA Sheet 01 (a) If the reworked depth (D) is higher than 5% of the initial thickness of the panel (E) and less or equal to the permissible limit of the reworked depth per area (d), refer to SUBTASK 576047-832-003 001 Do a Non Destructive Test of rib 1 between FR40 and FR47 . (b) If the reworked depth (D) is less or equal to 5 percent of the initial thickness of the panel (E), refer to SUBTASK 576047-833-006 001 Do a Surface Treatment for a New Protection Coating ( D =< 5% ) . (c) If the reworked depth (D) is higher than permissible limit of the reworked depth per area (d) : - Contact AIB before next flight. (4) Subtask 576047-832-003-001 - Do a Non Destructive Test of rib 1 between FR40 and FR47 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC References Non Destructive Test Manual (NTM) 51-10-08 Part 6 Structural Repair Manual (SRM) 51-23-00 51-23-10 51-23-20 Fig. A-FBCAA Permissible Limits of the Reworked Depth Sheet 01 Fig. A-FBGAA Inspection Program Sheet 01
DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 15 5

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# @A300-600 SERVICE BULLETIN (a) The reworked depth (D) is higher than 5% of the initial thickness of the panel (E) and less or equal to the permissible limit of the reworked depth per area (d) : Refer to Fig. A-FBCAA Sheet 01 Detect presence of crack around the fasteners and on the surface of forward and aft lower surface panels. Do a Non Destructive Test (NDT) for fatigue damage, refer to NTM 51-10-08 Part 6. 1 If crack is detected : - Contact AIB before the next flight. 2 If no crack is detected : - Refer to SUBTASK 576047-833-005 001 Do a Surface Treatment for a New Protection Coating ( 5% < D =< d ) . (5) Subtask 576047-833-003-001 - Do a Surface Treatment for a New Protection Coating Work Zones and Access Panels Zone Access/Work location 541 Work location from Frame 40 to Frame 47 641 Work location from Frame 40 to Frame 47 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Anti-Corrosion Primer (polyurethane) 16-001 As required Wash Primer 16-020 As required References Structural Repair Manual (SRM) 51-23-00 51-23-10 51-23-20 (a) Apply : Wash Primer 16-020 As required

and DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 16 5

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# @A300-600 SERVICE BULLETIN
Anti-Corrosion Primer (polyurethane) 16-001 As required (b) Apply new protective coating, refer to SRM 51-23-00, SRM 51-23-10 and SRM 51-23-20. - Next visual inspection for corrosion in 5 years. (6) Subtask 576047-833-004-001 - Remove the corrosion of rib 1 between FR40 and FR47 Work Zones and Access Panels Zone Access/Work location 541 Work location from Frame 40 to Frame 47 641 Work location from Frame 40 to Frame 47 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC References Non Destructive Test Manual (NTM) 51-10-04 Part 4 51-10-05 Part 1 Structural Repair Manual (SRM) 51-22-00 51-40-20 51-40-21 51-74-10 Fig. A-FBBAA Evaluation Principle of Corrosion Sheet 01 For the correspondence of the different reference values used in this part of the inspection (W, L, delta 1, delta 2, D) : Refer to Fig. A-FBBAA Sheet 01 These values enable to determine the rework conditions and also to check the permissible limits. W : Rework length in flight direction L : Rework length in outboard direction Delta 1 : Distance between two adjacent rework areas in flight direction Delta 2 : Distance between two adjacent rework areas in outboard direction

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 17 5

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# @A300-600 SERVICE BULLETIN (a) Remove the corrosion, refer to SRM 51-22-00 and SRM 51-74-10. Obey the rework conditions specified below. REWORK CONDITIONS Refer to Fig. A-FBBAA Sheet 01 L/2 > 4 (D) And w/2 > 4 (D) NOTE : If you find corrosion around the fasteners, remove the fasteners, refer to SRM 51-40-20 and SRM 51-40-21. (b) Measure the reworked depth (D), do a Non Destructive Test (NTD), refer to NTM 51-10-04 Part 4 or NTM 51-10-05 Part 1. (c) Make sure that the rework is in the permissible limits specified below. REWORK PERMISSIBLE LIMITS Refer to Fig. A-FBBAA Sheet 01 W < 50 mm (1.968 in.) L < 100 mm (3.937 in.) Delta 1 > 50 mm (1.968 in.) Delta 2 > not limited 1 If the rework is not in the permissible limits : - Contact AIB before the next flight. 2 If the rework is in the permissible limits : - Continue the inspection, refer to SUBTASK 576047-832-002 001 Do a Detailed Inspection of the rework depth of rib 1 between FR40 and FR47 . (7) Subtask 576047-833-006-001 - Do a Surface Treatment for a New Protection Coating ( D =< 5% ) Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Anti-Corrosion Primer (polyurethane) 16-001 Wash Primer 16-020 As required
DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 18 5

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# @A300-600 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-23-00 51-23-10 51-23-20 Fig. A-FBGAA Inspection Program Sheet 01 Fig. A-FBCAA Permissible Limits of the Reworked Depth Sheet 01 (a) The reworked depth (D) is less or equal to 5 percent of the initial thickness of the panel : Refer to Fig. A-FBCAA Sheet 01 1 Apply : Wash Primer 16-020 As required and Anti-Corrosion Primer (polyurethane) 16-001 As required

2 Apply new protective coating, refer to SRM 51-23-00, SRM 51-23-10 and SRM 51-23-20. NOTE : Replace the fastener if they have been removed for the corrosion inspection, refer to SUBTASK 576047-833-001 001 Replace the Fasteners . - Next visual inspection for corrosion in 5 years. (8) Subtask 576047-833-005-001 - Do a Surface Treatment for a New Protection Coating ( 5% < D =< d ) Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Anti-Corrosion Primer (polyurethane) 16-001 As required Wash Primer 16-020 As required DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 19 5

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# @A300-600 SERVICE BULLETIN
References Non Destructive Test Manual (NTM) 51-10-08 Part 6 Structural Repair Manual (SRM) 51-23-00 51-23-10 51-23-20 Fig. A-FBGAA Inspection Program Sheet 01 (a) Apply on countersunk heads and reworked areas : Wash Primer 16-020 As required

and Anti-Corrosion Primer (polyurethane) 16-001 As required (b) Apply new protective coating, refer to SRM 51-23-00, SRM 51-23-10 and SRM 51-23-20. NOTE : Replace the fastener if they have been removed for the corrosion inspection, refer to SUBTASK 576047-833-001 001 Replace the Fasteners . (c) Inspection program : - Next visual inspection for corrosion in 5 years. - Next inspection for fatigue damage : Refer to Fig. A-FBGAA Sheet 01 NOTE : According to damaged areas, the fatigue inspection program gives the thresholds and intervals (FC or FH whichever comes first) applicable to the visual check or the Non Destructive Test (NDT) : Refer to Fig. A-FBGAA Sheet 01 (9) Subtask 576047-833-001-001 - Replace the Fasteners Manpower Resources Manhours 1.50 Minimum number of person 1 Subtask elapsed time 0.75 Skills NON SPECIFIC

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 20 5

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# @A300-600 SERVICE BULLETIN Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfid(no Longeravailable 09-002 As required Corrosion Inhibitingsealant Sprayable 09-025 As required Anti-Corrosion Primer (polyurethane) 16-001 As required Wash Primer 16-020 As required References Non Destructive Test Manual (NTM) 51-10-04 part 4 51-10-05 part 1 Structural Repair Manual (SRM) 51-23-00 51-23-10 51-23-20 51-40-40 51-40-44 51-40-46 51-40-47 51-43-00 51-76-10 51-76-20 Fig. A-FBDAA Replacement Principle of Fasteners and Sealing principle Sheet 01 Fig. A-FBEAA Location of Existing Fasteners on Forward and Aft Lower Surface Panels Sheet 01 Sheet 02 Sheet 03 Fig. A-FBFAA Location of Existing Fasteners on Forward and Aft Lower Surface Panels Sheet 01 Sheet 02 NOTE : Replace fasteners of damaged holes when sitting is not correct or/and the fasteners have been removed for rework. The reference value is the remaining thickness of the panel (X). The permissible remaining thickness varies depending on the fastener replacement area. Permissible remaining thickness minimum thickness (X) for the forward lower surface panel : 3.5 mm (0.138 in.) mini. Permissible remaining thickness minimum thickness (X) for the aft lower surface panel : 4.5 mm (0.177 in.) mini. The remaining minimun thickness (X) is the panel thickness below the DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 21 5

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# @A300-600 SERVICE BULLETIN head of the fastener. Refer to Fig. A-FBDAA Sheet 01 , View A and B (a) CAUTION : BEFORE YOU DO THE NEW COUNTERSINK OR THE SPOTFACING FOR THE NEW FASTENER, REFER TO Fig. A-FBDAA Sheet 01 , DO A CHECK OF THE REMAINING THICKNESS (X) REFER TO NON DESTRUCTIVE TEST (NDT), REFER TO NTM 51-10-04 part 4 and NTM 51-10-05 part 1. If the remaining minimum panel thickness is in the permissible limits : - Install an oversize countersunk head fastener : Refer to Fig. A-FBDAA Sheet 01 , View A FWD LOWER SURFACE PANEL X => 3.5 mm (138 in.) and AFT LOWER SURFACE PANEL X => 4.5 mm (0.177 in.) Do the subsequent steps to install an oversize countersunk head fastener. 1 Drill and deburr the holes, refer to SRM 51-40-40 and SRM 51-40-44. 2 Perform the new contersink for an oversize countersunk head fastener, refer to SRM 51-40-46 and SRM 51-40-47. 3 Do wet assembly of all parts and fasteners to be installed with : Corrosion Inhibitingsealant Sprayable 09-025 As required
Refer to SRM 51-76-10 and SRM 51-76-20 4 Torque standard threaded fasteners, refer to SRM 51-43-00. 5 Apply on countersunk heads and reworked areas : Wash Primer 16-020 As required and Anti-Corrosion Primer (polyurethane) 16-001 As required
NOTE : According to damaged areas, for each type of existing fastener DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 22 5

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# @A300-600 SERVICE BULLETIN to be replaced and associated tables which give the alternative fastener identification (First oversize or second oversize). Refer to Fig. A-FBEAA Sheet 01 , Fig. A-FBEAA Sheet 02 , Fig. A-FBEAA Sheet 03 , Fig. A-FBFAA Sheet 02 and Fig. AFBFAA Sheet 01 6 Apply on the head of the fasteners : Fuel Tank Sealant Polysulfid(no Longeravailable 09-002 As required
Make sure that the sealant does not come out of the skin : Refer to Fig. A-FBDAA Sheet 01 , View B 7 Apply new protective coating, refer to SRM 51-23-00, SRM 51-23-10 and SRM 51-23-20. (b) If the remaining minimum panel thickness is not in the limits to install an oversize contersunk head fastener : - Install an oversize protruding head fastener : Refer to Fig. A-FBDAA Sheet 01 , View B FWD LOWER SURFACE PANEL X = > 3.5 mm (138 in.) and AFT LOWER SURFACE PANEL X => 4.5 mm (0.177 in.) Do the subsequent steps to install an oversize protruding head fastener. 1 Drill and deburr the holes, refer to SRM 51-40-40 and SRM 51-40-44. 2 Do a spotfacing to insure a good seating for an oversize protruding head fastener 3 Do wet assembly of all parts and fasteners to be installed with (Refer to SRM 51-76-10 and SRM 51-76-20) : Corrosion Inhibitingsealant Sprayable 09-025 As required

4 Torque standard threaded fasteners, refer to SRM 51-43-00. 5 Apply on countersunk heads and reworked areas : Wash Primer 16-020 As required DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 23 5

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# @A300-600 SERVICE BULLETIN and Anti-Corrosion Primer (polyurethane) 16-001 As required
NOTE : According to damaged areas, for each type of existing fastener to be replaced and associated tables which give the alternative fastener identification (First oversize or second oversize). Refer to Fig. A-FBEAA Sheet 01 , Fig. A-FBEAA Sheet 02 , Fig. A-FBEAA Sheet 03 , Fig. A-FBFAA Sheet 02 and Fig. AFBFAA Sheet 01 6 Apply on the head of the fasteners : Fuel Tank Sealant Polysulfid(no Longeravailable 09-002 As required
Make sure that the sealant does not come out of the skin : Refer to Fig. A-FBDAA Sheet 01 , View B 7 Apply new protective coating, refer to SRM 51-23-00, SRM 51-23-10 and SRM 51-23-20. (10) Subtask 576047-833-002-001 - Do the Sealing Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfid(no Longeravailable 09-002 As required (a) Along the external lower surface splice and fuselage pick-up angle, apply : Fuel Tank Sealant Polysulfid(no Longeravailable 09-002 As required

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 24 5

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# @A300-600 SERVICE BULLETIN D. TEST (1) Subtask 576047-700-001-001 - Testing Manpower Resources Skills NON SPECIFIC None E. CLOSE-UP (1) Subtask 576047-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 12-11-28, Page Block 301 24-00-00, Page Block 301 24-41-00 28-11-22, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the manhole covers, refer to AMM 28-11-22, Page Block 401. (c) Fill the fuel tank, refer to AMM 12-11-28, Page Block 301. (d) Make an inspection for leaks of the manhole cover. (e) Remove the access platforms.(f) De-energize the aircraft electrical circuits and disconnect the electrical groundconnection (Refer to AMM 24-41-00 and AMM 24-00-00, Page Block 301). (g) Write in the applicable aircraft records that you have done all the work given in this service bulletin.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 25 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

D_SB_576047_5_BAAA_01_00 

# A

**B**

FR40 FR47 RIB1 AREAS TO INSPECT

PICK−UP ANGLE

INBOARD AREA OUTBOARD AREA

INSPECT A WIDE OF 50 mm (1.968 in.) ONLY EXTERNAL LOWER SURFACE SPLICE MANHOLE COVER 541 AB/541 AB MANHOLE

COVER 542 CB/542 CB



# B FWD LOWER SURFACE PANEL AFT LOWER SURFACE PANEL 

# A **A**

Figure A-F BAAA - S heet 01 Areas to Be Inspected DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 26 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING DO A DETAILLED VISUAL INSPECTION FOR CORROSION AROUND THE FASTENERS AND ON THE SURFACE OF PANELS

NO YES
REMOVE THE CORROSION (REFER TO SRM 51−22−00 ON THE CENTER WING BOTTOM SKIN, AT INBOARD AND OUTBOARD AREAS OK RIB1 BETWEEN FR40 AND FR47.

MAKE SURE THAT THE REWORK IS IN THE PERMISIBLE LIMITS (**) IS MISSING OR NO YES
SURFACE TREATMENT, APPLY NEW

REPEAT VISUAL INSPECTION FOR CORROSION AT 5 YEARS CORROSION

PROTECTION

DAMAGED

PROTECTION COATING. REFER TO SRM 51−23−00,

51−23−10 and 51−23−20 AND 51−74−10) SEE NOTE (1). OBEY THE REWORK

CONDITIONS (*), MEASURE THE REWORKED DEPTH (D) REFER TO NTM 51−10−04 PART 4 OR 51−10−05 PART 1

RESULTS NO YES

SEE FIG. A−FFAAA SHEET 2 CONTACT AIRBUS BEFORE SUBSEQUENT FLIGHT AT THRESHOLD: SEE TABLE LH AND RH CENTER WING BOTTOM SKIN INBOARD AND OUTBOARD AREAS, REFER TO FIG. A−FBGAA SHEET 01

**NOTE:** (1) IF YOU FIND CORROSION AROUND THE FASTENERS REMOVE THE FASTENERS. (REFER TO SRM 51−40−20 AND 51−40−21) (**) REWORK PERMISSIBLE LIMITS W 50mm (1.958 in) L 100mm (3.937 in)

1 50mm (1.958 in) 2 NOT LIMITED (*) REWORK CONDITIONS

L/2 4D AND W/2 4D REFER TO FIG. A−FBAAA SHEET 01

REFER TO FIG. A−FBCAA SHEET 01 REFER TO FIG. A−FBCAA SHEET 01

D_SB_576047_5_FAAA_01_02 

### Figure A-FFAAA - Sheet 01 - Flow Chart - DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 27 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING SURFACE TREATMENT, APPLY

REPEAT VISUAL INSPECTION FOR CORROSION AT 5 YEARS 5% D d **

NEW PROTECTION COATING.

REFER TO SRM 51−23−00,

51−23−10 and 51−23−20

CRACKS NO YES

CONTACT AIRBUS BEFORE NEXT FLIGHT

**NOTE:** (2) REPLACE THE FASTENERS IF THEY HAVE BEEN REMOVED FROM FIG. A−FFAAA SHEET 1

D 5% * D d **
NON DESTRUCTIVE TEST (NDT) FOR FATIGUE DAMAGE REFER TO NTM 51−10−08 PART 8 SEE NOTE (2)

SURFACE TREATMENT, APPLY NEW PROTECTION COATING.

REFER TO SRM 51−23−00,

51−23−10 and 51−23−20 SEE NOTE (2)
INSPECTION PROGRAM INSPECTION FOR CORROSION IN 5 YEARS INSPECTION FOR FATIGUE DAMAGE: SEE TABLE LH AND RH CENTER WING BOTTOM SKIN INBOARD AND OUTBOARD AREAS,

FOR THE CORROSION INSPECTION. * 5% : REFERENCE VALUE WITH RESPECT TO THE INITIAL THICKNESS OF THE PANEL (E). PERMISSIBLE LIMIT OF THE REWORKED DEPTH (D). (REFER TO FIG. A−FBCAA SHEET 01) ** d : REFERENCE VALUE WITH RESPECT TO THE INITIAL THICKNESS OF THE PANEL (E). ACCORDING TO DAMAGED AREAS, PERMISSIBLE **LEGEND:**

LIMITS OF THE REWORKED DEPTH PER AREA (d). REFER TO FIG. A−FBCAA SHEET 01

REFER TO FIG. A−FBGAA SHEET 01

(REFER TO FIG. A−FBCAA SHEET 01)
D_SB_576047_5_FAAA_02_02 

### Figure A-FFAAA - Sheet 02 - Flow Chart - DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 28 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

PICK−UP ANGLE INBOARD AREA

EXTERNAL LOWER SURFACE SPLICE AFT LOWER SURFACE

D_SB_576047_5_BBAA_01_00REWORKEDDEPTH REWORK CONDITION L/2 > 4D AND W/2 > 4D

REWORK PERMISSIBLE LIMITS W < 50mm (1.968in.) L < 100mm (3.937in.)

1 > 50mm (1.968in.) 2 NOT LIMITEDD W/2E PANEL RIB1 STIFFENER 44.2

LATTICE FLANGE 45

STIFFENER 45.1

STIFFENER 45.2

LATTICE FLANGE 46

STIFFENER 46.1

STIFFENER 46.2

REF. FR47



# A−A SECTION LEGEND: W: REWORK LENGTH IN FLIGHT DIRECTION L: REWORK LENGTH IN OUTBOARD DIRECTION 1: DISTANCE BETWEEN TWO ADJACENT

REWORK AREAS IN FLIGHT DIRECTION 2: DISTANCE BETWEEN TWO ADJACENT

REWORK AREAS IN OUTBOARD DIRECTION D: REWORKED DEPTH E: INITIAL THICKNESS OF THE PANELW

2 L 

# A **A**1



### Figure A-F BBAA - S heet 01 Evaluation Principle of Corrosion DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 29 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL 

# A

**B**

FR40 FR47 RIB1 AREAS TO INSPECT

PICK−UP ANGLE

INBOARD AREA OUTBOARD AREA EXTERNAL LOWER SURFACE SPLICE 

# B FWD LOWER SURFACE PANEL AFT LOWER SURFACE PANELRIB2RIB1
SPAR

EXTERNAL LOWER SURFACE SPLICE 

# A

**B**
FWD LOWER

SURFACE PANEL AFT LOWER SURFACE PANEL

EXTERNAL LOWER SURFACE SPLICE INBOARD AREA OUTBOARD AREA
STGR 2 1 STGR 3 STGR 4 STGR 5 STGR 6 STGR 7 STGR 8 STGR 9 STG R

10 STG R

11 STG R 12

STG R

19 STG R

18 STG R

17 STG R

16 STG R

15 STG R 14 STG R

13 CENTER SPAR FRONT STIFFENER 40.1 STIFFENER 40.2 LATTICE FLANGE 41 STIFFENER 41.1 STIFFENER 41.2 LATTICE FLANGE 42 STIFFENER 42.1 STIFFENER 42.2 LATTICE FLANGE 43 STIFFENER 43.1 STIFFENER 43.2

STIFFENER 44.1 STIFFENER 44.2 LATTICE FLANGE 45 STIFFENER 45.1 STIFFENER 45.2 LATTICE FLANGE 46 STIFFENER 46.1 LATTICE FLANGE 44

STIFFENER 46.2 REF. FR40

REF. FR47 SPAR AREAS TO INSPECT EXTERNAL LOWER

SURFACE SPLICE REARFWD LOWER SURFACE PANELAFT LOWER SURFACE PANELAREADAMAGE

2

3

4 5 6

7

8 LH AND RH CENTER WING BOTTOM SKIN INBOARD AND OUTBOARD AREAS

CONTACT AIRBUS

PICK−UP ANGLE NOTE: ACCORDING TO DAMAGED AREAS PERMISSIBLE LIMITS OF THE REWORKED DEPTH ARE SPECIFIED BELOW D_SB_576047_5_BCAA_01_00 PERMISSIBLE LIMITS OF THE REWORKED DEPTH 5% TO THE INITIAL TICKNESS OF THE PANEL (INBOARD AREA) mm (in.) 5% TO THE INITIAL TICKNESS OF THE PANEL (OUTBOARD AREA) mm (in.) PER AREA (d) mm (in.) CONTACT AIRBUS CONTACT AIRBUS

CONTACT AIRBUS CONTACT AIRBUS CONTACT AIRBUS 2.9mm (0.114in.)

2.1mm (0.082in.)

0.9mm (0.035in.)

2.6mm (0.102in.)

1.3mm (0.051in.)

1.6mm (0.062in.)

0.5mm (0.019in.)

0.57mm (0.022in.) 0.47mm (0.018in.) 0.4mm (0.015in.) 0.36mm (0.014in.)

0.57mm (0.022in.)



### Figure A-FBCAA - Sheet 01 Permissible Limits of the Reworked Depth DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 30 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL 

# A

**B**

FR40 FR47 RIB1 AREAS TO INSPECT

PICK−UP ANGLE

INBOARD AREA OUTBOARD AREA EXTERNAL LOWER SURFACE SPLICE 

# B FWD LOWER SURFACE PANEL AFT LOWER SURFACE PANELRIB2RIB1
SPAR

EXTERNAL LOWER SURFACE SPLICE 

# A

**B**
FWD LOWER

SURFACE PANEL AFT LOWER SURFACE PANEL

EXTERNAL LOWER SURFACE SPLICE INBOARD AREA OUTBOARD AREA
STGR 2 1 STGR 3 STGR 4 STGR 5 STGR 6 STGR 7 STGR 8 STGR 9 STG R 10 STG R 11 STG R 12

STG R

19 STG R

18 STG R

17 STG R 16 STG R

15 STG R 14 STG R 13 CENTER SPAR FRONT STIFFENER 40.1 STIFFENER 40.2 LATTICE FLANGE 41 STIFFENER 41.1 STIFFENER 41.2 LATTICE FLANGE 42 STIFFENER 42.1 STIFFENER 42.2 LATTICE FLANGE 43 STIFFENER 43.1 STIFFENER 43.2

STIFFENER 44.1 STIFFENER 44.2 LATTICE FLANGE 45 STIFFENER 45.1 STIFFENER 45.2 LATTICE FLANGE 46 STIFFENER 46.1 LATTICE FLANGE 44

STIFFENER 46.2 REF. FR40

REF. FR47 SPAR AREAS TO INSPECT EXTERNAL LOWER

SURFACE SPLICE REARFWD LOWER SURFACE PANELAFT LOWER SURFACE PANELAREADAMAGE

2

3

4 5 6

7

8 FATIGUE INSPECTION PROGRAME AIRCRAFT WITH AFT < 1.5 FH/FC THRESHOLD INTERVAL VISUAL NDT

15700 FC 23600 FH 13400 FC 20200 FH 15700 FC 23600 FH

15700 FC 23600 FH 13400 FC 20200 FH 15700 FC 23600 FH

7400 FC 11200 FH 6700 FC 10100 FH 5500 FC 8200 FH 5100 FC 7700 FH 5500 FC 8200 FH 2300 FC 3500 FH 1000 FC 1600 FH 2300 FC 3500 FH 5500 FC 8200 FH 5100 FC 7700 FH 5500 FC 8200 FH
6200 FC 9300 FH 5900 FC 8800 FH 6200 FC 9300 FH

2700 FC 4100 FH 2400 FC 3500 FH 2700 FC 4000 FH FATIGUE INSPECTION PROGRAME AIRCRAFT WITH AFT > 1.5 FH/FC THRESHOLD INTERVAL VISUAL NDT

14500 FC 31500 FH 12400 FC 26900 FH

6900 FC 14900 FH 6200 FC 13500 FH 5100 FC 11000 FH 4800 FC 10300 FH 2200 FC 4700 FH 1000 FC 2100 FH

5800 FC 12500 FH 5400 FC 11800 FH

2500 FC 5500 FH 2200 FC 4800 FH 14500 FC 31500 FH

14500 FC 31500 FH 12400 FC 26900 FH 14500 FC 31500 FH

7400 FC 11200 FH 6900 FC 14900 FH 5100 FC 11000 FH 2200 FC 4700 FH 5100 FC 11000 FH 4800 FC 10300 FH 5100 FC 11000 FH
5800 FC 12500 FH

2500 FC 5400 FH LH AND RH CENTER WING BOTTOM SKIN INBOARD AND OUTBOARD AREAS

CONTACT AIRBUS

CONTACT AIRBUS CONTACT AIRBUS

CONTACT AIRBUS PICK−UP ANGLE NOTE: ACCORDING TO DAMAGED AREAS THE FATIGUE INSPECTION PROGRAM BELOW GIVES THE THRESHOLDS AND INTERVALS (FC OR FH WICHEVER COMES FIRST) APPLICABLE TO THE VISUAL CHECK OR THE NON DESTRUCTRUCTIVE TEST (NDT) D_SB_576047_5_BGAA_01_01 

### Figure A-FBGAA - Sheet 01 Inspection Program DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 31 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

EXTERNAL LOWER SURFACE SPLICERIB1 DATUM

PICK−UP ANGLE
SEALANT USE MAT. NO. 09−002 

# C **B**

REMAINING

MINIMUM THICKNESS X (SEE NOTE 1) OVERSIZE FOR NEW PROTRUDING HEAD FASTENER INITIAL THICKNESS OF THE LOWER SURFACE PANEL E SEALANT USE MAT. NO. 09−002

NEW FASTENER (SEE NOTE 2) BASIC CONTOUR AND BASIC FASTENER REWORKED DEPTH (D) 

# A

INITIAL THICKNESS OF THE LOWER SURFACE PANEL E REMAINING

MINIMUM THICKNESS X (SEE NOTE 1) OVERSIZE FOR NEW COUNTERSUNK HEAD FASTENER BASIC CONTOUR AND BASIC FASTENER SEALANT USE MAT. NO. 09−002

NEW FASTENER (SEE NOTE 2) REWORKED DEPTH (D)

NOTE 1: PERMISSIBLE REMAINING MINIMUM THICKNESS (X) FOR THE FWD LOWER SURFACE PANEL : 3.6mm (0.138in.) PERMISSIBLE REMAINING MINIMUM THICKNESS (X) FOR THE AFT LOWER SURFACE PANEL : 4.5mm (0.177in.) NOTE 2: IN RELATION WITH THE DAMAGED AREAS, FOR EACH TYPE OF FASTENER THAT YOU MUST REPLACE, REFER TO FIG. A−FBEAA SHEET 01, 02 AND 03, FIG. A−FBFAA SHEET 01 AND 02 AND THEIR TABLES, WHICH GIVE THE ALTERNATIVE IDENTIFICATION OF THE FASTENER (1st OVERSIZE OR 2st OVERSIZE). D_SB_576047_5_BDAA_01_01 

### Figure A-FBDAA - Sheet 01 Replacement Principle of Fasteners and Sealing principle DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 32 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL EXTERNAL LOWER

SURFACE SPLICE 

# A **A**

**B** AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL

EXTERNAL LOWER

SURFACE SPLICE 

# B

BOTTOM STRUCTURE AREA TO INSPECT
EXTERNAL LOWER

SURFACE SPLICE FR47

FR40 RIB1 

# C LH AND RH CENTER WING BOTTOM SKIN (INTBOARD AREA)

DETAIL VALID FOR ADAPTATION SOLUTION 

# ASTIFFENER 40.2STIFFENER 40.1 P BRACKET FOR WATER DRAIN SYSTEM

A D C B D E F E F G H F

8

N 7
M 6
L K 5 4 3 2
J 1REF.FR40STIFFENER 40.1STIFFENER 40.2LATTICE FLANGE41STIFFENER 41.1STIFFENER 41.2LATTICE FLANGE42STIFFENER 42.1STIFFENER 42.2LATTICE FLANGE43STIFFENER 43.1STIFFENER 43.2STIFFENER 44.1STIFFENER 44.2STIFFENER 45.1STIFFENER 45.2STIFFENER 46.2STIFFENER 46.1REF.FR44LATTICE FLANGE45LATTICE FLANGE46REF.FR47

AREA AREA AREA AREA AREA AREA AREA AREA RIB1 PICK−UP ANGLE

EXTERNAL LOWER

SURFACE SPLICEFRONT SPARCENTER SPAR FWD LOWER SURFACE PANEL AFT LOWER SURFACE PANELREAR SPAR 

# C

SEE DETAIL 

# A **B** PICK−UP ANGLE
INBOARD AREA

D_SB_576047_5_BEAA_01_01 

### Figure A-F BEAA - S heet 01 Location of Existing Fasteners on Forward and Aft Lower Surface Panels DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 33 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

STANDARD MUMBER

A

B
C

D

E

F
G

H

NOTE: THE VALUES − XX ARE TO BE DETERMINED WITH RESPECT TO THE REMAINING THICKNESS (X) REFER TO FIG. A−FBDAA SHEET 01 OR
OR
OR
OR
OR
OR

OR
OR PIN (THREADED) (HI−LITE) PIN (THREADED) (HI−TIGUE) (SCREW) ITEM TYPE ASSOCIATED HARDWAIR (NUT)
OR
OR STANDARD MUMBER TYPE

PIN (THREADED) (HI−LITE) PIN (THREADED) (HI−TIGUE) PIN (THREADED) (HI−LITE) PIN (THREADED) (HI−TIGUE) PIN (THREADED) (HI−LITE) PIN (THREADED) (HI−TIGUE) PIN (THREADED) (HI−LITE) PIN (THREADED) (HI−TIGUE) PIN (THREADED) (HI−LITE) PIN (THREADED) (HI−TIGUE) PIN (THREADED) (HI−LITE) PIN (THREADED) (HI−TIGUE) PIN (THREADED) (HI−LITE) PIN (THREADED) (HI−TIGUE) ASSOCIATED HARDWAIR (NUT) STANDARD MUMBER TYPE ASSOCIATED HARDWAIR (NUT) EXISTING FASTENER IDENTIFICATION ALTERNATIVE FASTENER IDENTIFICATION REFER TO FIG. A−FBEAA SHEET 01 VIEW C

PIN (THREADED) (BULLNOSE) PIN (THREADED)

(BULLNOSE) PIN (THREADED)

(BULLNOSE) PIN (THREADED)

(BULLNOSE) PIN (THREADED)

(BULLNOSE) PIN (THREADED)

(BULLNOSE) PIN (THREADED)

(BULLNOSE) PIN (THREADED)

(BULLNOSE) PIN (THREADED)

(BULLNOSE) PIN (THREADED)

(BULLNOSE) PIN (THREADED)

(BULLNOSE) PIN (THREADED)

(BULLNOSE) PIN (THREADED)

(BULLNOSE) PIN (THREADED)

(BULLNOSE) PIN (THREADED)

(BULLNOSE) PIN (THREADED)

(BULLNOSE) NAS1726−6E ASNA2031−6 NAS1726−5E ASNA2031−5 NAS1726−6E ASNA2031−6 NAS1726−5E ASNA2031−5 NAS1726−4E ASNA2031−4 NAS1726−5E ASNA2031−5 NAS1726−5E ASNA2031−5 NAS1726−4E ASNA2031−4 NSA5479BV4−XX
NSA5479BV6−XX
NSA5479BV5−XX
NSA5479BV4−XX
NSA5479BV5−XX
NSA5479BV3−XX

NSA5479BV3−XX
NSA5479BV6−XX NAS1726−6E ASNA2031−4 NAS1726−5E ASNA2031−5 NAS1726−6E ASNA2031−6 NAS1726−5E ASNA2031−5 NAS1726−4E ASNA2031−4 NAS1726−5E ASNA2031−5 NAS1726−5E ASNA2031−5 NAS1726−4E ASNA2031−4

HLT901BJ12−XX NSA5477BV6−XX HLT901BJ14−XX NSA5477BV5−XX HLT901BJ10−XX NSA5477BV5−XX HLT901BJ14−XX NSA5477BV5−XX HLT901BJ4−XX NSA5477BV4−XX HLT901BJ10−XX NSA5477BV5−XX HLT901BJ10−XX NSA5477BV5−XX HLT901BJ4−XX NSA5477BV4−XX

NAS1726−4E ASNA2031−6 NAS1726−5E ASNA2031−5 NAS1726−6E ASNA2031−6 NAS1726−5E ASNA2031−5 NAS1726−4E ASNA2031−4 NAS1726−5E ASNA2031−5 NAS1726−5E ASNA2031−5 NAS1726−4E ASNA2031−4

ASNA2004V6−14 ASNA2026V6−14 ASNA2004V4−10 ASNA2026V4−10

ASNA2004V5−12 ASNA2026V5−12

ASNA2004V6−10 ASNA2026V6−10

ASNA2004V4−12 ASNA2026V4−12

ASNA2004V5−13 ASNA2026V5−13

ASNA2004V5−14 ASNA2026V5−14

ASNA2004V5−10 ASNA2026V5−10

D_SB_576047_5_BEAA_02_01 FIG. A−FBDAA SHEET 01 VIEW A) 1st OVERSIZE FOR COUNTERSUNK HEAD FASTENER (REFER TO 1st OVERSIZE FOR PROTRUDING FIG. A−FBDAA SHEET 01 VIEW A)

HEAD FASTENER (REFER TO



### Figure A-F BEAA - S heet 02 Location of Existing Fasteners on Forward and Aft Lower Surface Panels DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 34 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

STANDARD MUMBER

J

K
L

M

N

P OR
OR
OR
OR
OR
OR (SCREW) ITEM TYPE ASSOCIATED HARDWAIR (NUT) STANDARD MUMBER TYPE ASSOCIATED HARDWAIR (NUT) STANDARD MUMBER TYPE ASSOCIATED HARDWAIR (NUT) EXISTING FASTENER IDENTIFICATION ALTERNATIVE FASTENER IDENTIFICATION

NSA5154BVA6−XX
NSA5154BVA6−XX
NSA5154BVA9−XX
NSA5154BVA9−XX
NSA5154BVA9−XX
NSA5154BVA9−XX NAS1726−9E NAS1726−9E NAS1726−9E NAS1726−9E NAS1726−9E NAS1726−9E NAS1726−9E NAS1726−9E NAS1726−4E NAS1726−4E NAS1726−4E NAS1726−4E ASNA2012K9−17 NSA5022V9−17

ASNA2012K9−18 NSA5022V9−18

ASNA2012K9−19 NSA5022V9−19

ASNA2012K9−20 NSA5022V9−20

ASNA2012K9−21 NSA5022V9−21
NSA5022V9−22 NSA5022V9−23 TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK NSA5153VA6−XX
NSA5153VA6−XX
NSA5153VA9−XX
NSA5153VA9−XX
NSA5153VA9−XX
NSA5153VA9−XX TAPER−LOK
TAPER−LOK
TAPER−LOK
TAPER−LOK
TAPER−LOK
TAPER−LOK NAS1726−4E
NAS1726−4E
NAS1726−9E
NAS1726−9E
NAS1726−9E
NAS1726−9E TAPER−LOK
TAPER−LOK
TAPER−LOK
TAPER−LOK
TAPER−LOK
TAPER−LOK NAS1726−4E
NAS1726−4E
NAS1726−9E
NAS1726−9E
NAS1726−9E
NAS1726−9E

D_SB_576047_5_BEAA_03_01 NOTE: THE VALUES − XX ARE TO BE DETERMINED WITH RESPECT TO THE REMAINING THICKNESS (X) REFER TO FIG. A−FBDAA SHEET 01 REFER TO FIG. A−FBEAA SHEET 01 VIEW C

FIG. A−FBDAA SHEET 01 VIEW A) 1st OVERSIZE FOR COUNTERSUNK HEAD FASTENER (REFER TO 1st OVERSIZE FOR PROTRUDING FIG. A−FBDAA SHEET 01 VIEW A)

HEAD FASTENER (REFER TO



### Figure A-F BEAA - S heet 03 Location of Existing Fasteners on Forward and Aft Lower Surface Panels DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 35 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL EXTERNAL LOWER

SURFACE SPLICE 

# A **A**

**B** AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL EXTERNAL LOWER

SURFACE SPLICE 

# B

PICK−UP ANGLE AREA TO INSPECT

EXTERNAL LOWER

SURFACE SPLICE OUTBOARD AREA FR47

FR40 RIB1



# C


# C

1 2 3 4 5 6 7 8 AREA AREA AREA AREA AREA AREA AREA AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANELREAR SPARLATTICEFLANGE 47FRONT SPARREF.FR40 RIB1

EXTERNAL LOWER SURFACE SPLICECENTER SPAR

G F E D C D C B ACENTER SPARSTGR19STGR18STGR17STGR16STGR15STGR14STGR13STGR11STGR10STGR9STGR8STGR7STGR6STGR5STGR4STGR3STGR2 LH AND RH CENTER WING BOTTOM SKIN (OUTBOARD AREA)

AREA

D_SB_576047_5_BFAA_01_01LATTICEFLANGE 46LATTICEFLANGE 45LATTICEFLANGE 44LATTICEFLANGE 43LATTICEFLANGE 42LATTICEFLANGE 41



### Figure A-FBFAA - Sheet 01 Location of Existing Fasteners on Forward and Aft Lower Surface Panels DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 36 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

EXISTING FASTENER IDENTIFICATION ALTERNATIVE FASTENER IDENTIFICATION
ITEM TYPE (SCREW) HARDWARE (NUT) ASSOCIATED STANDARD NUMBER TYPE STANDARD NUMBER FIG. A−FBDAA SHEET 01 VIEW A) HARDWARE (NUT) ASSOCIATED TYPE STANDARD NUMBER HARDWARE (NUT) ASSOCIATED

NSA5092V6−15 NSA5092V7−17 NSA5092V7−19 NSA5092V7−20 NSA5092V7−21 NSA5092V7−22 NSA5092V7−23 TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK NSA5050−6 NSA5050−7 NSA5050−7 NSA5050−7 NSA5050−7 NSA5050−7 NSA5050−7 NSA5153VA6−XX NSA5153VA7−XX NSA5153VA7−XX NSA5153VA7−XX NSA5153VA7−XX NSA5153VA7−XX NSA5153VA7−XX TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK NAS1726−6E NAS1726−7E NAS1726−7E NAS1726−7E NAS1726−7E NAS1726−7E NAS1726−7E NSA5154VA6−XX NSA5154VA7−XX NSA5154VA7−XX NSA5154VA7−XX NSA5154VA7−XX NSA5154VA7−XX NSA5154VA7−XX TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK TAPER−LOK NAS1726−6E NAS1726−7E NAS1726−7E NAS1726−7E NAS1726−7E NAS1726−7E NAS1726−7E REFER TO FIG. A−FBFAA SHEET 01 VIEW C LH AND RH CENTER WING BOTTOM SKIN (OUTSGARD AREA)

NOTE: THE VALUES − XX ARE TO BE DETERMINED WITH RESPECT TO THE REMAINING THICKNESS (X) REFER TO FIG. A−FBDAA SHEET 01. A B C D E F G 1st OVERSIZE FOR COUNTERSUNK HEAD FASTENER (REFER TO 1st OVERSIZE FOR PROTRUDING FIG. A−FBDAA SHEET 01 VIEW A)

HEAD FASTENER (REFER TO

D_SB_576047_5_BFAA_02_01 

### Figure A-FBFAA - Sheet 02 Location of Existing Fasteners on Forward and Aft Lower Surface Panels DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 37 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 38 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN Appendix 1- Inspection Report - **CONF ALL The results of the inspection, including no findings, replacement or action to be done, must be forwarded to AIRBUS Departement SEES1, on the attached inspec tion report sheet.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 1 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN Appendix 1- Inspection Report -
**CONF ALL

SERVICE BULLETIN AREA REPAIRED IN ACCORDANCE WITH : PLEASE PRECISE OTHER FINDINGS THAN CORROSION: **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300−57−6047

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS EDDY CURRENT

AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL EXTERNAL LOWER

SURFACE SPLICE 

# A

**B** 

# B

BOTTOM STRUCTURE AREA TO INSPECT EXTERNAL LOWER

SURFACE SPLICE FR47

FR40 RIB1 

## C

DETAIL VALID FOR ADAPTATION SOLUTION 

# ASTIFFENER 46.2STIFFENER 46.1 P BRACKET FOR WATER DRAIN SYSTEM PICK−UP ANGLE INBOARD AREA A D C B D E F E F G H F

8

N 7
M 6
L K 5 4 3 2
J 1REF.FR40STIFFENER 40.1STIFFENER 40.2LATTICE FLANGE41STIFFENER 41.1STIFFENER 41.2LATTICE FLANGE42STIFFENER 42.1STIFFENER 42.2LATTICE FLANGE43STIFFENER 43.1STIFFENER 43.2STIFFENER 44.1STIFFENER 44.2STIFFENER 45.1STIFFENER 45.2STIFFENER 46.2STIFFENER 46.1REF.FR44LATTICE FLANGE45LATTICE FLANGE46REF.FR47

AREA AREA AREA AREA AREA AREA AREA AREA RIB1 PICK−UP ANGLE EXTERNAL LOWER

SURFACE SPLICEFRONT SPARCENTER SPAR FWD LOWER SURFACE PANEL AFT LOWER SURFACE PANELREAR SPAR 

# C

SEE DETAIL 

# A NOTE: PLEASE PRECISE THE DAMAGED AREA OR FASTENERS. LH CENTER WING BOTTOM SKIN (INBOARD AREA)

D_SB_576047_5_RAAA_01_01 

### Figure A-FRAAA - Sheet 01 - Inspection Report - DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 2 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN Appendix 1- Inspection Report -
**CONF ALL

AREA REPAIRED IN ACCORDANCE WITH : PLEASE PRECISE OTHER FINDINGS THAN CORROSION: **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300−57−6047

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS EDDY CURRENT
REPORT FOR CORROSION RESULT AERA DAMAGED
AERA mm in mm in mm in mm in mm in WIDTH

(W) LENGTH (L) DEPTH (D) DISTANCE A1 DISTANCE A2

AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL EXTERNAL LOWER

SURFACE SPLICE 

# A

**B** 

# B

AREA TO INSPECT EXTERNAL LOWER

SURFACE SPLICE FR47

FR40 RIB1

INBOARD AREA

D_SB_576047_5_RAAA_02_01 LH CENTER WING BOTTOM SKIN (INBOARD AREA)

PICK−UP ANGLE REFER TO FIG. A−FBEAA



### Figure A-FRAAA - Sheet 02 - Inspection Report - DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 3 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN Appendix 1- Inspection Report -
**CONF ALL

SERVICE BULLETIN AREA REPAIRED IN ACCORDANCE WITH : PLEASE PRECISE OTHER FINDINGS THAN CORROSION: **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300−57−6047

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS EDDY CURRENT 

# A

AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL

EXTERNAL LOWER

SURFACE SPLICE 

# B

DETAIL VALID FOR ADAPTATION SOLUTION 

# A

A D C B D E F E F G H F

8

N 7
M 6
L K 5 4 3 2
J 1REF.FR40STIFFENER 40.1STIFFENER 40.2LATTICE FLANGE41STIFFENER 41.1STIFFENER 41.2LATTICE FLANGE42STIFFENER 42.1STIFFENER 42.2LATTICE FLANGE43STIFFENER 43.1STIFFENER 43.2STIFFENER 44.1STIFFENER 44.2STIFFENER 45.1STIFFENER 45.2STIFFENER 46.2STIFFENER 46.1REF.FR44LATTICE FLANGE45LATTICE FLANGE46REF.FR47

AREA AREA AREA AREA AREA AREA AREA AREA RIB1 PICK−UP ANGLE EXTERNAL LOWER

SURFACE SPLICEFRONT SPARCENTER SPAR FWD LOWER SURFACE PANEL AFT LOWER SURFACE PANELREAR SPAR 

# C

SEE DETAIL 

# A **B**

BOTTOM STRUCTURE AREA TO INSPECT EXTERNAL LOWER SURFACE SPLICE

FR40 PICK−UP ANGLE INBOARD AREA RIB1 FR47 

# C

NOTE: PLEASE PRECISE THE DAMAGED AREA OR FASTENERS. RH CENTER WING BOTTOM SKIN (INBOARD AREA)STIFFENER 46.2STIFFENER 46.1
P BRACKET FOR WATER DRAIN SYSTEM

D_SB_576047_5_RAAA_03_01 

### Figure A-FRAAA - Sheet 03 - Inspection Report - DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 4 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN Appendix 1- Inspection Report -
**CONF ALL

AREA REPAIRED IN ACCORDANCE WITH : PLEASE PRECISE OTHER FINDINGS THAN CORROSION: **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300−57−6047

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS EDDY CURRENT
REPORT FOR CORROSION RESULT AERA DAMAGED
AERA mm in mm in mm in mm in mm in WIDTH

(W) LENGTH (L) DEPTH (D) DISTANCE A1 DISTANCE A2

AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in 

# A

AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL

EXTERNAL LOWER

SURFACE SPLICE 

# B **B**

BOTTOM STRUCTURE AREA TO INSPECT EXTERNAL LOWER SURFACE SPLICE

FR40 PICK−UP ANGLE INBOARD AREA RIB1 FR47 

# C

D_SB_576047_5_RAAA_04_01 RH CENTER WING BOTTOM SKIN (INBOARD AREA) REFER TO FIG. A−FBEAA



### Figure A-FRAAA - Sheet 04 - Inspection Report - DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 5 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN Appendix 1- Inspection Report -
**CONF ALL

SERVICE BULLETIN AREA REPAIRED IN ACCORDANCE WITH : PLEASE PRECISE OTHER FINDINGS THAN CORROSION: **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300−57−6047

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS EDDY CURRENT 

# A

AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL EXTERNAL LOWER

SURFACE SPLICE 

# C

1 2 3 4 5 6 7 8 AREA AREA AREA AREA AREA AREA AREA AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANELREAR SPARFRONT SPAR

RIB1

EXTERNAL LOWER SURFACE SPLICECENTER SPAR

G F E D C D C B ACENTER SPARSTGR19STGR18STGR17STGR16STGR15STGR14STGR13STGR11STGR10STGR9STGR8STGR7STGR6STGR5STGR4STGR3STGR2 AREA



# B

PICK−UP ANGLE AREA TO INSPECT
EXTERNAL LOWER SURFACE SPLICE OUTBOARD AREA FR47

FR40 RIB1



# CREF.FR40LATTICEFLANGE 41

D_SB_576047_5_RAAA_05_01 NOTE: PLEASE PRECISE THE DAMAGED AREA OR FASTENERS. RH CENTER WING BOTTOM SKIN (OUTBOARD AREA)LATTICEFLANGE 42LATTICEFLANGE 43LATTICEFLANGE 44LATTICEFLANGE 45LATTICEFLANGE 46LATTICEFLANGE 47



### Figure A-FRAAA - Sheet 05 - Inspection Report - DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 6 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN Appendix 1- Inspection Report -
**CONF ALL

AREA REPAIRED IN ACCORDANCE WITH : PLEASE PRECISE OTHER FINDINGS THAN CORROSION: **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300−57−6047

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS EDDY CURRENT
REPORT FOR CORROSION RESULT AERA DAMAGED
AERA mm in mm in mm in mm in mm in WIDTH

(W) LENGTH (L) DEPTH (D) DISTANCE A1 DISTANCE A2

AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in 

# A

AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL EXTERNAL LOWER

SURFACE SPLICE 

# B

PICK−UP ANGLE AREA TO INSPECT
EXTERNAL LOWER SURFACE SPLICE OUTBOARD AREA FR47

FR40 RIB1

D_SB_576047_5_RAAA_06_01 RH CENTER WING BOTTOM SKIN (OUTBOARD AREA) REFER TO FIG. A−FBFAA



### Figure A-FRAAA - Sheet 06 - Inspection Report - DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 7 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN Appendix 1- Inspection Report -
**CONF ALL

SERVICE BULLETIN AREA REPAIRED IN ACCORDANCE WITH : PLEASE PRECISE OTHER FINDINGS THAN CORROSION: **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300−57−6047

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS EDDY CURRENT 

# A

AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL EXTERNAL LOWER SURFACE SPLICE 

# B

PICK−UP ANGLE AREA TO INSPECT
EXTERNAL LOWER

SURFACE SPLICE OUTBOARD AREA FR47

FR40 RIB1



# C 

# C

1 2 3 4 5 6 7 8 AREA AREA AREA AREA AREA AREA AREA AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANELREAR SPARLATTICEFLANGE 47FRONT SPARREF.FR40 RIB1

EXTERNAL LOWER SURFACE SPLICECENTER SPAR

G F E D C D C B ACENTER SPARSTGR19STGR18STGR17STGR16STGR15STGR14STGR13STGR11STGR10STGR9STGR8STGR7STGR6STGR5STGR4STGR3STGR2 AREA

D_SB_576047_5_RAAA_07_01LATTICEFLANGE 46LATTICEFLANGE 45LATTICEFLANGE 44LATTICEFLANGE 43LATTICEFLANGE 42LATTICEFLANGE 41

NOTE: PLEASE PRECISE THE DAMAGED AREA OR FASTENERS. LH CENTER WING BOTTOM SKIN (OUTBOARD AREA)



### Figure A-FRAAA - Sheet 07 - Inspection Report - DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 8 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN Appendix 1- Inspection Report -
**CONF ALL

AREA REPAIRED IN ACCORDANCE WITH : PLEASE PRECISE OTHER FINDINGS THAN CORROSION: **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300−57−6047

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS EDDY CURRENT
REPORT FOR CORROSION RESULT AERA DAMAGED
AERA mm in mm in mm in mm in mm in WIDTH

(W) LENGTH (L) DEPTH (D) DISTANCE A1 DISTANCE A2

AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in AERA mm in mm in mm in mm in mm in 

# A

AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL EXTERNAL LOWER SURFACE SPLICE 

# B

PICK−UP ANGLE AREA TO INSPECT
EXTERNAL LOWER

SURFACE SPLICE OUTBOARD AREA FR47

FR40 RIB1



# C

D_SB_576047_5_RAAA_08_01 LH CENTER WING BOTTOM SKIN (OUTBOARD AREA) REFER TO FIG. A−FBFAA



### Figure A-FRAAA - Sheet 08 - Inspection Report - DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 9 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN Appendix 2- Repair Report - **CONF ALL The results of the inspection, including no findings, replacement or action to be done, must be forwarded to AIRBUS Departement SEES1, on the attached inspec tion report sheet.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 1 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN Appendix 2- Repair Report -
**CONF ALL

AREA REPAIRED IN ACCORDANCE WITH : PLEASE PRECISE OTHER FINDINGS THAN CORROSION: **REPAIR REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300−57−6047

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS EDDY CURRENT
REPORT FOR REPAIR RESULT1stOVERSIZE OVERSIZE FOR COUNTERSUNK HEAD FASTENER

SERVICE BULLETINAERADAMAGEDEXISTINGFASTENERDAMAGED

AREA ITEM2ndOVERSIZE STANDARD NUMBER TYPE OVERSIZE FOR PROTRUDING HEAD FASTENER STANDARD

NUMBER TYPE AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL EXTERNAL LOWER

SURFACE SPLICE 

# A

**B** 

# B

AREA TO INSPECT EXTERNAL LOWER

SURFACE SPLICE FR47

FR40 RIB1

INBOARD AREA LH CENTER WING BOTTOM SKIN (INBOARD AREA) REFER TO FIG. A−FBEAA

PICK−UP ANGLE

D_SB_576047_5_RBAA_01_00 

### Figure A-FRBAA - Sheet 01 - Repair Report - DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 2 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN Appendix 2- Repair Report -
**CONF ALL

AREA REPAIRED IN ACCORDANCE WITH : PLEASE PRECISE OTHER FINDINGS THAN CORROSION: SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300−57−6047

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS EDDY CURRENT

SERVICE BULLETIN 

# A

AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL

EXTERNAL LOWER

SURFACE SPLICE 

# B **B**

BOTTOM STRUCTURE AREA TO INSPECT EXTERNAL LOWER SURFACE SPLICE

FR40 PICK−UP ANGLE INBOARD AREA RIB1 FR47 

# C **REPAIR REPORT**

REPORT FOR REPAIR RESULT1stOVERSIZE OVERSIZE FOR COUNTERSUNK HEAD FASTENERAERADAMAGEDEXISTINGFASTENERDAMAGED

AREA ITEM2ndOVERSIZE STANDARD NUMBER TYPE OVERSIZE FOR PROTRUDING HEAD FASTENER STANDARD

NUMBER TYPE RH CENTER WING BOTTOM SKIN (INBOARD AREA) REFER TO FIG. A−FBEAA

D_SB_576047_5_RBAA_02_00 

### Figure A-FRBAA - Sheet 02 - Repair Report - DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 3 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN Appendix 2- Repair Report -
**CONF ALL

AREA REPAIRED IN ACCORDANCE WITH : PLEASE PRECISE OTHER FINDINGS THAN CORROSION: SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300−57−6047

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS EDDY CURRENT

SERVICE BULLETIN 

# A

AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL EXTERNAL LOWER

SURFACE SPLICE 

# B

PICK−UP ANGLE AREA TO INSPECT
EXTERNAL LOWER SURFACE SPLICE OUTBOARD AREA FR47

FR40 RIB1 **REPAIR REPORT**

REPORT FOR REPAIR RESULT1stOVERSIZE OVERSIZE FOR COUNTERSUNK HEAD FASTENERAERADAMAGEDEXISTINGFASTENERDAMAGED

AREA ITEM2ndOVERSIZE STANDARD NUMBER TYPE OVERSIZE FOR PROTRUDING HEAD FASTENER STANDARD

NUMBER TYPE RH CENTER WING BOTTOM SKIN (OUTBOARD AREA) REFER TO FIG. A−FBFAA

D_SB_576047_5_RBAA_03_00 

### Figure A-FRBAA - Sheet 03 - Repair Report - DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 4 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN Appendix 2- Repair Report -
**CONF ALL

AREA REPAIRED IN ACCORDANCE WITH : PLEASE PRECISE OTHER FINDINGS THAN CORROSION: SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300−57−6047

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR)

INSPECTION METHOD : VISUAL 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

STRUCTURE REPAIR MANUAL AIRBUS INSTRUCTIONS EDDY CURRENT

SERVICE BULLETIN 

# A

AFT LOWER SURFACE PANEL FWD LOWER SURFACE PANEL EXTERNAL LOWER SURFACE SPLICE 

# B

PICK−UP ANGLE AREA TO INSPECT
EXTERNAL LOWER

SURFACE SPLICE OUTBOARD AREA FR47

FR40 RIB1



# C

D_SB_576047_5_RBAA_04_00 **REPAIR REPORT**

REPORT FOR REPAIR RESULT1stOVERSIZE OVERSIZE FOR COUNTERSUNK HEAD FASTENERAERADAMAGEDEXISTINGFASTENERDAMAGED

AREA ITEM2ndOVERSIZE STANDARD NUMBER TYPE OVERSIZE FOR PROTRUDING HEAD FASTENER STANDARD

NUMBER TYPE LH CENTER WING BOTTOM SKIN (OUTBOARD AREA) REFER TO FIG. A−FBFAA



### Figure A-FRBAA - Sheet 04 - Repair Report - DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 5 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN REPORTING SHEET 

## TITLE: WINGS - INSPECTION OF CENTER WING BOTTOM SKIN CORROSION AT RIB 1 MODIFICATION No.: None Please complete the appropriate item (A or B): A - SB WILL BE embodied YES/NO (if NO please comment) If YES, aircraft concer ned (as per SB effectivity by default) and planned dates (month/year) of embodiment:
B - SB HAS BEEN embodied on aircraft: Operator comments: From Airline: Name/Title: Signature: Date: If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either: Modification Operational Impact (MOI), if available YES/NO Or : Intermediate revision YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - Updating of maintenance documentation to show pre and post SB data. - Updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. Please return this completed sheet to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: SDC32 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 1 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN QUALITY PERCEPTION FORM Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4321 - Quality rating of the Accomplishment Instructions 4321 - Quality rating of the Illustrations 4321 - Is this SB easy to understand ? Y/N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials Operator Supplied X Mod/Inspection X Manpower X Industry support X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments:

Operator: Date: Name/Title: Please return this form to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: Jan 04/96 SERVICE BULLETIN No.: A300-57-6047 REVISION No.: 06 - Oct 17/11 Page: 1 5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.