REVISION No. : 03 − Jan 11/02 L7 

# A300−600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61 93 33 33 Telex: AIRBU 530526 F Fax : (33) 5 61 93 42 51 ATA SYSTEM : TITLE : 57 WINGS − OUTER WING − INSPECT FRONT AND REAR SPAR BOTTOM BOOM − INBOARD AND OUTBOARD OF RIB 9 MODIFICATION No. : None This page transmits Revision No.03 of Service Bulletin No. A300−600−57−6037. ADDITIONAL WORK No additional work is required by this revision for aircraft inspected/repaired by any previous issue of this Service Bulletin. REASON This revision has been issued to clarify the test requirements if the refuel/defuel pipes are removed for easier access to the inspection area. The test requirement is a system leak test in accordance with the applicable Aircraft Maintenance Manual. CHANGES Service Bulletin: − para.3.D.TEST − reference to functional test deleted and system leak test added. − Figure 4 − referenced NTM number corrected. FILING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete Service Bulletin. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS Revision 01 was issued to give a reduction in the repeat inspection interval from 9000FC to 4800FC. This reduction followed in−service findings. Revision 02 was issued following an operators request to include the removal of the refuel/defuel pipes in the inspection area. This will allow easier access for sealant removal. Other changes were also made, as follows: − Airworthiness Directive number 94−208−169 (B) added. − Change Notices 1A and 1B incorporated. − Aircraft effectivity updated.

DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 1 of 2REVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET REVISION SEQUENCE ORIGINAL : Aug 01/94 REVISION No. : 01 − Aug 31/95 REVISION No. : 02 − Jan 09/01 REVISION No. : 03 − Jan 11/02

DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 2REVISION No. : 03 − Jan 11/02 L7 

# A300−600 SERVICE BULLETIN SUMMARY AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61 93 33 33 Telex: AIRBU 530526 F 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 : TITLE : 57 WINGS − OUTER WING − INSPECT FRONT AND REAR SPAR BOTTOM BOOM − INBOARD AND OUTBOARD OF RIB 9 MODIFICATION No. : None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During full scale fatigue tests, cracks were found starting from the bolt holes, inboard and outboard of rib 9, on the front and rear spar bottom booms at 58,650 simulated Flight Cycles (FC). There have been six reports of cracks found in the front and rear spar bottom booms at the rib 9 joint on A300−B2 aircraft in service. The cracks were found at between 19,500 FC and 29,700 FC. There is a possibility of similar cracks on A300−600 aircraft which would need lengthy and expensive repairs. Mandatory ultrasonic inspections of the front and rear spar bottom boom, inboard and outboard of rib 9 are to be done at or before 17000 FC. Repeat inspections are to be done at intervals not exceeding 4800 FC. Modification No.08842H5298 (Service Bulletin No.A300−57−6039) introduces first oversize fasteners with an option for fitting second oversize fasteners if first oversize fasteners have already been installed. When Modification No.08842H5298 (Service Bulletin No.A300−57−6039) has been embodied, the first subsequent inspection is to be done at no later than 17,000 further flight cycles and repeat inspections are to be done at intervals not exceeding 4,800 FC.

DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 1 of 3EVALUATION TABLE COMPLIANCE MANDATORY CANCELS INSPECTION SB NO POTENTIAL AD 94−208−169 (B) A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING YES ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO KIT PRICE (USD) NO KIT

REVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN SUMMARY

EFFECTIVITY This Service Bulletin is applicable to these operators: AAL AWW CAL CES DLH F2I G8E JAS KAC KAL LFA MON MSR OAL PFD QTR SUD SVA TAR THA UAE NOTE : This Service Bulletin is applicable to aircraft pre−modification 10161H5329. The Modification 10161H5329 is embodied before delivery on aircraft MSN 0723 and subsequent. CONCURRENT REQUIREMENTS None REFERENCES/REPERCUSSIONS TFU : None OEB : None AOT : None SIL : None LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No OTHER : None NATURE OF THE WORK AIRCRAFT : Yes EQUIPMENT : No HARD : No SOFT : No OBRM : No

DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
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# A300−600 SERVICE BULLETIN SUMMARY MANPOWER TOTAL MANHOURS 16.0 ELAPSED TIME (HOURS) 6.0 MATERIAL INFORMATION AIRCRAFT DATA None APPENDICES None

DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 3REVISION No. : 03 − Jan 11/02 L7 B4−601 B4−603 B4−605R B4−620 B4−622 B4−622R C4−620 

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

# MANDATORY MANDATORY MANDATORY ATA SYSTEM : TITLE : 57 WINGS − OUTER WING − INSPECT FRONT AND REAR SPAR BOTTOM BOOM − INBOARD AND OUTBOARD OF RIB 9 MODIFICATION No. : None This document contains Airbus Industrie PROPRIETARY INFORMATION and shall at all times remain the property of Airbus Industrie; no intellectual property right or licence is granted by Airbus Industrie in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or part to third parties and shall not be duplicated in any manner (except for the purpose of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without Airbus Industrie’s prior written consent. 1. PLANNING INFORMATION A. EFFECTIVITY (1) Models (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN: 0252 0284 0294 0301 0307 0312 0317 0321 0336 0341 0344 0348 0351 0354 0358 0361 0365 0368 0371 0377 0380 0384 0388 0391 0395 0398 0401 0405 0408 0411 0414 0417 0420 0423 0459−0466 0469−0471 0474 0477 0479 0505−0518 0521 0525 0529−0530 0532−0533 0536 0540 0543 0546 0553−0561 0563 0566 0569 0572 0575 0577 0579 0581−0582 0584 0601−0619 0621 0623 0625−0633 0635 0637 0639 0641 0643 0645 0657 0659 0662 0664 0666 0668 0670 0673 0675 0677 0679 0681 0683 0685 0688 0690 0692 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721−0722

DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
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# A300−600 SERVICE BULLETIN NOTE : This Service Bulletin is applicable to aircraft pre−modification 10161H5329. The Modification 10161H5329 is embodied before delivery on aircraft MSN 0723 and subsequent. (b) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to Airbus Industrie. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. OPERATOR MSN AAL 0420 0423 0459 0460 0461 0462 0463 0465 0466 0469 0470 0471 0474 0506 0507 0508 0509 0510 0511 0512 0513 0514 0515 0516 0517 0606 0610 0612 0615 0619 0626 0639 0643 0645 0675 AWW 0633 0688 CAL 0529 0533 0536 0555 0559 0625 0666 0677 CES 0521 0525 0532 0707 0709 0713 0715 DLH 0380 0391 0401 0405 0408 0411 0414 0546 0553 0618 0623 F2I 0344 G8E 0584 JAS 0602 0617 0621 0637 0641 0670 0679 0683 0703 0711 KAC 0673 0694 0699 0719 0721 KAL 0358 0361 0365 0388 0417 0477 0479 0543 0554 0560 0582 0609 0614 0627 0631 0657 0659 0662 0685 0692 0717 0722 LFA 0611 0613 MON 0540 0556 0604 0605 MSR 0557 0561 0572 0575 0579 0581 0601 0607 0616 OAL 0603 0632 0696 PFD 0354 QTR 0630 0664 0668 0690 SUD 0252 0505 0530 SVA 0284 0294 0301 0307 0312 0317 0321 0336 0341 0348 0351 TAR 0558 0563 THA 0368 0371 0377 0384 0395 0398 0464 0518 0566 0569 0577 0628 0629 0635 0681 0705 UAE 0608 0701 (c) Effectivity by MSN and Kit/Configuration None (3) Spares None B. CONCURRENT REQUIREMENTS None DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 21.D.(1) 1.D.(2) 1.D.(3)

1.D.(4) 1.D.(5) 1.D.(6) 1.D.(7) 1.D.(8) 1.D.(9)

REVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN C. REASON (1) History During full scale fatigue tests, cracks were found starting from the bolt holes, inboard and outboard of rib 9, on the front and rear spar bottom booms at 58,650 simulated Flight Cycles (FC). There have been six reports of cracks found in the front and rear spar bottom booms at the rib 9 joint on A300−B2 aircraft in service. The cracks were found at between 19,500 FC and 29,700 FC. There is a possibility of similar cracks on A300−600 aircraft which would need lengthy and expensive repairs. Modification No.08842H5298 (Service Bulletin No.A300−57−6039) introduces first oversize fasteners with an option for fitting second oversize fasteners if first oversize fasteners have already been installed. This modification does not take the aircraft to design life goals (2) Objective/Action To do an ultrasonic inspection of 2 holes inboard and 2 holes outboard of rib 9 on the front and rear spar bottom booms (8 holes per wing). (3) Advantages Early detection of cracks can prevent expensive and time consuming repairs. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to: (1) Defuel the aircraft. (2) Remove the manhole covers 542EB, 543AB, 642EB and 643AB. (3) If required for access, remove the refuel/defuel pipes in the inspection area. (4) Do an ultrasonic inspection of the fastener holes for cracks. (5) Do any necessary repairs. (6) If removed, install the refuel/defuel pipes in the inspection area. (7) Install the manhole covers 542EB, 543AB, 642EB and 643AB. (8) Refuel the aircraft. (9) If the refuel/defuel pipes were removed/installed, do a functional test of the refuel/defuel system. E. COMPLIANCE (1) Classification Mandatory DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 31.E.(2)(a)

1.E.(2)(b)

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REVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN (2) Accomplishment Timescale (a) This Service Bulletin is rendered MANDATORY by Airworthiness Directive (Consigne de Navigabilite) No.94−208−169 (B). (b) Mandatory inspections of the front and rear spar bottom booms, inboard and outboard of Rib 9, are to be done at or before 17000 FC. (c) Mandatory repeat inspections are to be done at intervals not exceeding 4800 FC. (d) When Modification No.08842H5298 (Service Bulletin No.A300−57−6039) has been embodied, the next subsequent inspection is to be done not later than 17000 further FC and repeat inspections are to be done at intervals not exceeding 4800 FC. (e) For aircraft approaching or that have exceeded the first inspection threshold, this inspection is to be done within the limits that follow: − for aircraft that are between 2000 FC less than the threshold and not more than 3000 FC beyond the threshold, the first inspection is to be done within 2000 FC from the date of receipt of this Service Bulletin. − for aircraft that have exceeded the threshold by more than 3000 FC, the first inspection is to be done within 1000 FC from the date of receipt of this Service Bulletin. (f) The thresholds and intervals given in this Service Bulletin are established and valid for aircraft operated with the individual average airborne flight time of 2.1 hours. Therefore, when aircraft are operated with different flight times, inspection thresholds and intervals are to be adjusted in accordance with the MRB Document, Section D, Paragraph 8: Adjustment for Range. For this Service Bulletin, the Fatigue Rating (FR) to be applied to determine the Adjustment Factor is 0.13. (g) The number of touch and go flights can be ignored when they are less than five percent of the total number of flights between two consecutive inspections. When the percentage of touch and go flights is more than five percent of the total number of flights between two consecutive inspections, each touch and go flight beyond five percent has to be counted as a flight cycle. A touch and go is a landing in which an aircraft touches the runway and does not come to a full stop before commencing an additional flight. F. APPROVAL The technical content of this Service Bulletin has been approved under the authority of the DGAC Design Organisation Approval No. F.JA.02. If an aircraft listed in the effectivity has a modification or repair DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
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# A300−600 SERVICE BULLETIN embodied that is not of AIRBUS origin, which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labour 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 time for paints, sealants etc and general administration work are also not included. Manhours: Get access 7.0 Inspection 1.0 Test 1.0 Close up 7.0 TOTAL MANHOURS 16.0 ELAPSED TIME (HOURS) 6.0 H. WEIGHT AND BALANCE Not changed I. ELECTRICAL LOAD DATA None J. REFERENCES Aircraft Maintenance Manual (AMM) : 12−11−28 24−00−00 28−00−00 28−10−00 28−11−22 28−25−00 Structural Repair Manual (SRM) : 51−10−13 51−40−21 51−40−44 51−40−47 51−43−00 51−75−10 51−75−20 51−76−20 Nondestructive Testing Manual (NTM) : 51−10−01 Part 6 51−10−08 Part 6 57−21−04 Part 4 Service Bulletin (SB) : A300−57−6039 Repair Instruction : R571 40141 Maintenance Review Board (MRB) : Section D, Para.8 Airworthiness Directive : 94−208−169 (B) K. PUBLICATIONS AFFECTED None L. INTERCHANGEABILITY/MIXABILITY None DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
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# A300−600 SERVICE BULLETIN

DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 6 This Page Intentionally Left BlankHole Nominal Fastener First Oversize Fastener Second Oversize Fastener Nut Washer S NSA5486V6R18N NSA5487V6R18N NSA5488V6R18N NSA5472−6K7 NSA5353D06B T NSA5486V7R19N NSA5487V7R19N NSA5488V7R19N NSA5472−7K7 NSA5353D07B U NSA5486V7R24N NSA5487V7R24N NSA5488V7R24N NSA5472−7K7 NSA5353D07B V NSA5486V6R21N NSA5487V6R21N NSA5488V6R21N NSA5472−6K7 NSA5353D06B W NSA5486V6R18N NSA5487V6R18N NSA5488V6R18N NSA5472−6K7 NSA5353D06B X NSA5486V7R21N NSA5487V7R21N NSA5488V7R21N NSA5472−7K7 NSA5353D07B Y NSA5486V7R21N NSA5487V7R21N NSA5488V7R21N NSA5472−7K7 NSA5353D07B Z NSA5486V6R18N NSA5487V6R18N NSA5488V6R18N NSA5472−6K7 NSA5353D06B

REVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN 2. MATERIAL INFORMATION A. MATERIAL − PRICE AND AVAILABILITY (1) Material None (2) Price and Availability None B. INDUSTRY SUPPORT INFORMATION NOTE : Oversize fasteners (Operator supply) are listed below. The quantities required will depend on damage found.

C. LIST OF COMPONENTS None D. LIST OF MATERIALS − OPERATOR SUPPLIED Refer to para.2.B.INDUSTRY SUPPORT INFORMATION. E. PARTS TO BE RE IDENTIFIED BY THE OPERATOR None F. TOOLING − PRICE AND AVAILABILITY None G. SPECIAL TOOLS None

DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
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# A300−600 SERVICE BULLETIN

DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
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REVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL WARNING : OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : PUT THE SAFETY DEVICES AND WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: − THE FLIGHT CONTROLS − THE FLIGHT CONTROL SURFACES − LANDING GEAR AND RELATED DOORS − COMPONENTS THAT MOVE. WARNING : OBEY ALL THE FUEL SAFETY PROCEDURES (REFER TO AMM 28−00−00 Page block 301). (1) Preparation (a) Electrically ground the aircraft (Refer to AMM 24−00−00 Page block 301). (b) Defuel the aircraft (Refer to AMM 28−10−00 Page block 301and AMM 28−25−00 Page block 301). (c) Put access platforms in position. (d) Remove the manhole covers 542EB, 543AB, 642EB and 643AB (Refer to AMM 28−11−22 Page block 401). (e) Identify the fastener holes to be inspected (Refer to Figure 1 and Figure 2 ). (f) If required, for better access to remove the sealant in the inspection area, remove and retain the applicable refuel/defuel pipes (Refer to Figure 3 and AMM 28−00−00 Page block 401). (g) Remove the sealant from the spar flanges at the bolt holes to be inspected. An area of 25.0mm (1.0in.) should be removed from the inboard and outboard side of the bolts. (2) Standard Practices (a) For fastener removal and installation refer to SRM 51−40−21 Page block 1. (b) For hole and drill data refer to SRM 51−40−44 . (c) For countersinking procedures refer to SRM 51−40−47 Page block 1. (d) For torque values refer to SRM 51−43−00 Page block 1. (e) For the removal and application of sealant refer to SRM 51−76−20 Page block 201. (f) For the removal of paint coatings refer to SRM 51−75−20 Page block 201. (g) For the repair and replacement of paint coatings refer to SRM 51−75−10 Page block 201. DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
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REVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN B. INSPECTION (1) Do an ultrasonic inspection of the front and rear spar flange, adjacent to the fastener holes (Refer to NTM 57−21−04 , Part 4). Refer to Figure 1 and Figure 2 (2) If a crack is detected, refer to paragraph 3.C.REPAIR and do one of the applicable worksteps that follows before the next flight: (a) If modification 08842H5298 (SB A300−57−6039) is not to be accomplished at the same time as this Service Bulletin do the worksteps in para.C.REPAIR (1). (b) If modification 08842H5298 (SB A300−57−6039) is to be accomplished at the same time as this Service Bulletin do the worksteps in para.C.REPAIR (2). (3) If a crack is not detected, do paragraphs 3.D.TEST and 3.E.CLOSE UP. C. REPAIR CAUTION: WHEN YOU DO ANY OF THE REPAIRS THAT FOLLOW, IT IS IMPORTANT THAT ONLY ALTERNATE FASTENERS ARE REMOVED SO THAT CLAMPING IS MAINTAINED AT ALL TIMES. SUITABLE SLAVE BOLTING IS PERMITTED. CAUTION: ALL OVERSIZING INSTRUCTIONS IN THE REPAIR INSTRUCTIONS THAT FOLLOW APPLY TO HOLES WHICH HAVE NOT BEEN OVERSIZED BEFORE. ANY HOLES FOUND TO HAVE BEEN OVERSIZED BEFORE MUST BE REPORTED TO AI/SE−A BEFORE ANY FURTHER ACTION IS TAKEN. (1) To repair cracked fastener holes found during the inspection, do the worksteps that follow (Refer to the Flow Chart Figure 4 ). (a) Remove the fastener where a crack was detected and inspect the fastener hole to confirm the indication (Refer to NTM 51−10−01 , Part 6, Procedure C). 1 If a crack is not indicated, ream the hole to the first oversize diameter and install the correct diameter taper−lok fastener. 2 If a crack is indicated, do the worksteps in para.C.(1)(b). (b) Remove the four adjacent fasteners on both sides of the cracked fastener hole. For holes which contain taper−lok fasteners do workstep C.(1) (c). For holes which contain parallel fasteners do workstep C.(1) (d). (c) Taper−lok Holes 1 Inspect the fastener holes for cracks (Refer to NTM 51−10−01 , Part 6, Procedure C). a If cracks are not indicated record all findings and contact AI/SE−A for an approved repair procedure which is to be embodied before the next flight . b If cracks are indicated, do the worksteps in para.C.(1) DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
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REVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN (c) 2. 2 Inspect the top surface of the structure around the hole circumference for cracks (Refer to NTM 51−10−08 , Part 6). a If a crack is indicated, repeat the requirements of workstep C.(1)(b). b If cracks are not indicated, do the worksteps in para.C.(1) (c) 3 and 4. CAUTION: THE OVERSIZING PROCEDURE THAT FOLLOWS IS FOR HOLES WITH NOMINAL FASTENER DIAMETERS OF 0.25 to 0.75IN. (6.35 TO 19.05MM) ONLY. CAUTION: THE OVERSIZING THAT FOLLOWS MAY ONLY BE DONE IF THE HOLE EDGE DISTANCE IS NOT LESS THAN 1.75D AND THE HOLE CENTER PITCH IS NOT LESS THAN 3.5D. 3 Ream the cracked fastener hole to the first oversize diameter. 4 Inspect the oversize fastener hole for cracks (Refer to NTM 51−10−01 , Part 6, Procedure C). a If the crack is completely removed by first oversizing, record all findings and actions taken and contact AI/SE−A for an approved repair procedure which is to be embodied before the next flight. b If a crack is still indicated, do the worksteps in para.C.(1) (c) 5 and 6. 5 Ream the cracked fastener hole to the second oversize diameter. 6 Inspect the oversize fastener hole for cracks (Refer to NTM 51−10−01 , Part 6, Procedure C). a If the crack is not removed by second oversizing, repeat the worksteps in para.C.(1) (b). b If the crack is completely removed by second oversizing record all findings and actions taken and contact AI/SE−A for an approved repair which is to be embodied before the next flight. (d) Parallel Holes 1 Inspect the holes for cracks (Refer to NTM 51−10−01 , Part 6, Procedure B). a If cracks are not indicated, record all findings and contact AI/SE−A for an approved repair which is to be embodied before the next flight. b If a crack is indicated, do the worksteps in para.C.(1) (d) 2. 2 Inspect the top surface of the structure around the hole circumference for cracks (Refer to NTM 51−10−08 , Part 6). DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
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REVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN
a If a crack is indicated at the top surface repeat the worksteps in para.C.(1) (b). b if cracks are not indicated at the top surface do the worksteps in para.C.(1) (d) 3 and 4. CAUTION: THE OVERSIZING THAT FOLLOWS MAY ONLY BE DONE IF THE HOLE EDGE DISTANCE IS NOT LESS THAN 1.75D AND THE HOLE CENTER PITCH IS NOT LESS THAN 3.5D. CAUTION: CONTACT AI/SE−A BEFORE YOU DO THE COLD EXPANSION THAT FOLLOWS. 3 Oversize the cracked fastener hole to the cold expansion start hole diameter for the next nominal fastener size. 4 Inspect the oversize fastener hole for cracks (Refer to NTM 51−10−01 , Part 6, Procedure B). a If all crack indications have been removed, record all findings and actions taken and contact AI/SE−A for an approved repair which is to be embodied before the next flight. b If a crack is indicated, repeat the worksteps in para.C.(1) (b). (2) To repair cracked holes found during accomplishment of Modification No.08842H5298 (SB A300−57−6039), do the worksteps that follow (Refer to the Flow Chart Figure 5 ). (a) Inspect the top surface of the structure around the hole circumference for cracks (Refer to NTM 51−10−08 , Part 6). 1 If a crack is indicated at the top surface do the requirements of workstep C.(2) (f). 2 If cracks are not indicated at the top surface do the worksteps in para.C.(2) (b) and (c). CAUTION: THE OVERSIZING PROCEDURE THAT FOLLOWS IS FOR HOLES WITH NOMINAL FASTENER DIAMETERS OF 0.25 TO 0.75IN. (6.35 TO 19.05MM) ONLY. CAUTION: THE OVERSIZING THAT FOLLOWS MAY ONLY BE DONE IF THE HOLE EDGE DISTANCE IS NOT LESS THAN 1.75D AND THE HOLE CENTER PITCH IS NOT LESS THAN 3.5D. (b) Ream the cracked fastener hole to the first oversize diameter. (c) Inspect the oversize fastener hole for cracks (Refer to NTM 51−10−01 , Part 6, Procedure C). 1 If the crack indication is completely removed by first oversizing, install a new fastener in accordance with the Modification SB A300−57−6039. 2 If a crack is still indicated do the worksteps in para.C.(2) (d) and (e). (d) Ream the cracked fastener hole to the second oversize DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 123.C.(2)(e)

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REVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN diameter. (e) Inspect the oversize fastener hole for cracks (Refer to NTM 51−10−01 , Part 6, Procedure C). 1 If the crack indication is not removed by second oversizing, do the worksteps in para.C.(2) (f). 2 If the crack indication is completely removed by second oversizing, install a new fastener in accordance with the Modification SB A300−57−6039. (f) Remove the four adjacent fasteners on both sides of the cracked fastener hole. For holes which contained taper−lok fasteners do the worksteps in para.C.(2) (g). For holes which contained parallel fasteners do the worksteps in para.C.(2) (h). (g) Taper−lok Holes 1 Inspect the fasteners holes for cracks (Refer to NTM 51−10−01 , Part 6, Procedure C). a If cracks are not indicated record all findings and contact AI/SE−A for an approved repair which is to be embodied before the next flight. b If a crack is indicated do the worksteps in para.C.(2) (g) 2. 2 Inspect the top surface of the structure around the hole circumference for cracks (Refer to NTM 51−10−08 , Part 6. a If a crack is indicated at the top surface repeat the worksteps in para.C.(2) (f). b If cracks are not indicated at the top surface do the worksteps in para.C.(2) (g) 3 and 4. CAUTION: THE OVERSIZING PROCEDURE THAT FOLLOWS IS FOR HOLES WITH NOMINAL FASTENER DIAMETERS OF 0.25 TO 0.75IN. (6.35 TO 19.05MM) ONLY. CAUTION: THE OVERSIZING THAT FOLLOWS MAY ONLY BE DONE IF THE HOLE EDGE DISTANCE IS NOT LESS THAN 1.75D AND THE HOLE CENTER PITCH IS NOT LESS THAN 3.5D. 3 Ream the cracked fastener hole to the first oversize diameter. 4 Inspect the oversize fastener hole for cracks (Refer to NTM 51−10−01 , Part 6, Procedure C). a If the crack indication is completely removed by first oversizing record all findings and actions taken and contact AI/SE−A for an approved repair which is to be embodied before the next flight. b If a crack is still indicated, do the worksteps in para.C.(2) (g) 5 and 6. DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 133.C.(2)(g)5
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REVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN 5 Ream the cracked fastener hole to the second oversize diameter. 6 Inspect the oversize fastener hole for cracks (Refer to NTM 51−10−01 , Part 6, Procedure C). a If the crack indication is not removed by second oversizing repeat the worksteps in para.C.(2) (f). b If the crack indication is completely removed by second oversizing record all findings and actions taken and contact AI/SE−A for an approved repair which is to be embodied before the next flight. (h) Parallel Holes 1 Inspect the fastener holes for cracks (Refer to NTM 51−10−01 , Part 6, Procedure B). a If cracks are not indicated, record all findings and contact AI/SE−A for an approved repair procedure which is to be embodied before the next flight. b If a crack is indicated at the fastener hole, do the worksteps in para.C.(2) (h) 2. 2 Inspect the top surface of the structure around the hole circumference for cracks (Refer to NTM 51−10−08 , Part 6). a If a crack is indicated at the top surface repeat the worksteps in para.C.(2) (f). b If cracks are not indicated at the top surface do the worksteps in para.C.(2) (h) 3 and 4. CAUTION: THE OVERSIZING PROCEDURE THAT FOLLOWS IS FOR HOLES WITH NOMINAL FASTENER DIAMETERS OF 0.25 TO 0.75IN. (6.35 TO 19.05MM) ONLY. CAUTION: CONTACT AI/SE−A BEFORE YOU DO THE COLD EXPANSION THAT FOLLOWS. 3 Oversize the cracked fastener hole to the cold expansion start hole diameter for the next nominal interference−fit fastener size. 4 Inspect the oversize fastener hole for cracks (Refer to NTM 51−10−01 , Part 6, Procedure B). a If all crack indications have been removed, record all findings and actions taken and contact AI/SE−A for an approved repair which is to be embodied before the next flight. b If a crack is indicated, repeat the worksteps in para.C.(2) (f). (3) Results of inspections, including nil findings and repair actions, must be sent immediately to AI/SE−A after completion of the inspection/repairs. Use the Inspection Report (Figure 6 ) provided DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 143.D.(1)

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REVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN in this Service Bulletin. Details of holes that are still cracked, edge margins, pitch and hole diameters, must also be included (Refer to SRM 51−10−13 Page block 1. D. TEST (1) If you removed the refuel/defuel pipes for access, complete the worksteps in para.E.CLOSE UP and do a system leak test (Refer to AMM 28−25−00 Page block 501). E. CLOSE UP (1) Replace any fasteners that have been removed. (2) In the inspection area, apply sealant as required. (3) If removed for access, install the refuel/defuel pipes (Refer to AMM 28−00−00 Page block 401). (4) Replace paint coatings as required. (5) Make sure that the work areas are clean and clear of tools and other items of equipment. (6) Install the manhole covers 542EB, 543AB, 642EB and 643AB (Refer to AMM 28−11−22 Page block 401). (7) Refuel the aircraft (Refer to AMM 12−11−28 Page block 1). (8) Do an external inspection for fuel leaks. (9) Remove the access platforms. F. DOCUMENTATION Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 15REVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN

Figure 1 Sheet 1
DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 16 Holes To Be Inspected − Front Spar Bottom BoomREVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN

Figure 2 Sheet 1
DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 17 Holes To Be Inspected − Rear Spar Bottom BoomREVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN

Figure 3 Sheet 1
DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 18 Removal of the Refuel/Defuel Pipes for AccessREVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN

Figure 4 Sheet 1

DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 20 Repair Flow Chart For Cracked Holes Found During Accomplishment Of The Inspection Service BulletinREVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN

Figure 5 Sheet 1

DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 22 Repair Flow Chart For Cracked Holes Found During Accomplishment Of The Modification Service BulletinREVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN

Figure 6 Sheet 1
DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 23 Inspection ReportREVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN

Figure 4 Sheet 1 DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037 Page : 19/20 Printed in France © Airbus Industrie 1994, All rights reserved Repair Flow Chart For Cracked Holes Found During Accomplishment Of The Inspection Service BulletinREVISION No. : 03 − Jan 11/02 

# A300−600 SERVICE BULLETIN

Figure 5 Sheet 1 DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037 Page : 21/22 Printed in France © Airbus Industrie 1994, All rights reserved Repair Flow Chart For Cracked Holes Found During Accomplishment Of The Modification Service BulletinREVISION No. : 03 − Jan 11/02 L7 

# A300−600 SERVICE BULLETIN REPORTING SHEET TITLE : WINGS − OUTER WING − INSPECT FRONT AND REAR SPAR BOTTOM BOOM − INBOARD AND OUTBOARD OF RIB 9 MODIFICATION No. : None Please complete the appropriate item (A or B): A − SB WILL BEembodied . . . . . . . . . . . . . .YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment: . . . . . . . . . . . . . . . . . . . . . . . . . .

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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B − SB HAS BEENembodied on aircraft: . . . . . . . . . . . . . . . . . . . . .

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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Operator comments: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . From Airline: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Name/Title: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Signature: . . . . . . . . . . . . Date: . . . . . . . . . . . If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either: Advance data . . . . . . . . . . . . . . . . . . . . . . YES/NO Or : Intermediate/Temporary revision . . . . . . . . . . . . YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus Industrie 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 Industrie shall automatically include them in the manual revisions. Refer to SIL 00−037 for detailed information. Please return this completed sheet to: AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: AI/SE−D32 Technical Data and Documentation Services Fax: (+33) 5 61 93 28 06 or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
Printed in France © Airbus Industrie 1994, All rights reserved Page : 1 of 1REVISION No. : 03 − Jan 11/02 L7 

# 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 4 3 2 1 − Quality rating of the Accomplishment Instructions 4 3 2 1 − Quality rating of the Illustrations 4 3 2 1 − Is this SB easy to understand ? Y / N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit Content X Preparation X Reason X List of Materials X Mod/Inspection X Manpower Operator Supplied X Test X References X Re−identification X Close−up X Publication X Tooling X Illustrations Comments :

Operator : Date: Name/Title : Please return this form to : AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX Attn : AI/SE−T1 Service Bulletins Management FAX : (33) 5 61 93 42 51 or via your Resident Customer Support Office.
DATE : Aug 01/94 SERVICE BULLETIN No. : A300−57−6037
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