REVISION No. : 02 − Jan 09/01

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 transmitts Revision 02 of Service Bulletin A300−57−6037.

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 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 have also been made, as follows:

− Airworthiness Directive number 94−208−169 (B) added.

− Change Notices 1A and 1B incorporated.

− Aircraft effectivity updated.

CHANGES

Summary:

− EVALUATION TABLE added.

− EFFECTIVITY updated.

− Manhours revised to include the removal/installation of the refuel/defuel

pipes and the related system test.

Service Bulletin:

− Standard sentence PROPRIETARY INFORMATION added.

− Para.1.A.EFFECTIVITY (2) (a) − Aircraft MSN updated.

− Para.1.A.EFFECTIVITY (2) (b) − Operator and MSN number updated.

− Para.1.D.DESCRIPTION updated to include the removal/installation of the

refuel/defuel pipes and the related system test.

− Para.1.E.COMPLIANCE (2) (a) and (f) − Change Notice 1.A. incorporated

(Airworthiness Directive number 94−208−169 (B) added). The reduction of

the repeat inspection interval, introduced at Revision 01 of this Service

Bulletin, has been deleted.

− Para.E.COMPLIANCE (f) − MRB Adjustment for Range paragraph number has been

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

Printed in France © Airbus Industrie 1994, All rights reserved

Page : 1 of 2
REVISION No. : 02 − Jan 09/01

A300−600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

changed.

− Para.F.APPROVAL − Standard sentence updated.

− Para.G.MANPOWER − Standard sentence added and manhours revised to include

the removal/installation of the refuel/defuel pipes in the inspection area

and the related test.

− Para.J.REFERENCES − Updated.

− Para.2.MATERIAL INFORMATION B. − Change Notice 1.B. incorporated (Fastener

Table added).

− Para.3.ACCOMPLISHMENT INSTRUCTIONS A. (1) (f) − Removal of the

refuel/defuel pipes added.

− Para.B.INSPECTION (2) (a) and (b) − worksteps updated.

− Para.C.REPAIR − Reporting reference changed from AI/ST1 to AI/SE−A.

− Para.D.TEST − Functional test of the refuel/defuel system added.

− Para.E.CLOSE UP − Installation of the refuel/defuel pipes added.

− New Figure 3 added for the removal of the refuel/defuel pipes.

− New Figures 4 and 5 added − Inspection Flow Charts.

− Inspection Report changed to Figure 6.

− Layout changes due to the computerization of this revision are not

identified.

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 SEQUENCE

ORIGINAL : Aug 01/94

REVISION No. : 01 − Aug 31/95

REVISION No. : 02 − Jan 09/01

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

Printed in France © Airbus Industrie 1994, All rights reserved

Page : 2
 

EVALUATION TABLE

COMPLIANCE MANDATORY CANCELS INSPECTION

SB

NO

POTENTIAL AD 94−208−169 (B) A/C OPERATION

AFFECTED

NO

REVISION No. : 02 − Jan 09/01

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 3
EVALUATION TABLE

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. : 02 − Jan 09/01

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

MANPOWER

TOTAL MANHOURS 16.0

ELAPSED TIME (HOURS) 6.0

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

Printed in France © Airbus Industrie 1994, All rights reserved

Page : 2
REVISION No. : 02 − Jan 09/01

A300−600

SERVICE BULLETIN

SUMMARY

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 : 3
REVISION No. : 02 − Jan 09/01

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

Printed in France © Airbus Industrie 1994, All rights reserved

Page : 1 of 23
REVISION No. : 02 − Jan 09/01

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 : 2
 1.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. : 02 − Jan 09/01

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 : 3
 1.E.(2)(a) 

 1.E.(2)(b) 

 1.E.(2)(c) 

 1.E.(2)(d) 

 1.E.(2)(e) 

 1.E.(2)(f) 

 1.E.(2)(g) 

REVISION No. : 02 − Jan 09/01

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

Printed in France © Airbus Industrie 1994, All rights reserved

Page : 4
REVISION No. : 02 − Jan 09/01

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

Printed in France © Airbus Industrie 1994, All rights reserved

Page : 5
REVISION No. : 02 − Jan 09/01

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 Blank
 

Hole

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. : 02 − Jan 09/01

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

Printed in France © Airbus Industrie 1994, All rights reserved

Page : 7
REVISION No. : 02 − Jan 09/01

A300−600

SERVICE BULLETIN

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

Printed in France © Airbus Industrie 1994, All rights reserved

Page : 8

This Page Intentionally Left Blank
 3.A.(1)(a) 

 3.A.(1)(b) 

 3.A.(1)(c) 

 3.A.(1)(d) 

 3.A.(1)(e) 

 3.A.(1)(f) 

 3.A.(1)(g) 

 3.A.(2)(a) 

 3.A.(2)(b) 

 3.A.(2)(c) 

 3.A.(2)(d) 

 3.A.(2)(e) 

 3.A.(2)(f) 

 3.A.(2)(g) 

REVISION No. : 02 − Jan 09/01

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

Printed in France © Airbus Industrie 1994, All rights reserved

Page : 9
 3.B.(1) 

 3.B.(2) 

 3.B.(2)(a) 

 3.B.(2)(b) 

 3.B.(3) 

 3.C.(1) 

 3.C.(1)(a) 

 3.C.(1)(a)1 

 3.C.(1)(a)2 

 3.C.(1)(b) 

 3.C.(1)(c) 

 3.C.(1)(c)1 

 3.C.(1)(c)1 a 

 3.C.(1)(c)1 b 

REVISION No. : 02 − Jan 09/01

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

Printed in France © Airbus Industrie 1994, All rights reserved

Page : 10
 3.C.(1)(c)2 

 3.C.(1)(c)2 a 

 3.C.(1)(c)2 b 

 3.C.(1)(c)3 

 3.C.(1)(c)4 

 3.C.(1)(c)4 a 

 3.C.(1)(c)4 b 

 3.C.(1)(c)5 

 3.C.(1)(c)6 

 3.C.(1)(c)6 a 

 3.C.(1)(c)6 b 

 3.C.(1)(d) 

 3.C.(1)(d)1 

 3.C.(1)(d)1 a 

 3.C.(1)(d)1 b 

 3.C.(1)(d)2 

REVISION No. : 02 − Jan 09/01

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

Printed in France © Airbus Industrie 1994, All rights reserved

Page : 11
 3.C.(1)(d)2 a 

 3.C.(1)(d)2 b 

 3.C.(1)(d)3 

 3.C.(1)(d)4 

 3.C.(1)(d)4 a 

 3.C.(1)(d)4 b 

 3.C.(2) 

 3.C.(2)(a) 

 3.C.(2)(a)1 

 3.C.(2)(a)2 

 3.C.(2)(b) 

 3.C.(2)(c) 

 3.C.(2)(c)1 

 3.C.(2)(c)2 

 3.C.(2)(d) 

REVISION No. : 02 − Jan 09/01

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 : 12
 3.C.(2)(e) 

 3.C.(2)(e)1 

 3.C.(2)(e)2 

 3.C.(2)(f) 

 3.C.(2)(g) 

 3.C.(2)(g)1 

 3.C.(2)(g)1 a 

 3.C.(2)(g)1 b 

 3.C.(2)(g)2 

 3.C.(2)(g)2 a 

 3.C.(2)(g)2 b 

 3.C.(2)(g)3 

 3.C.(2)(g)4 

 3.C.(2)(g)4 a 

 3.C.(2)(g)4 b 

REVISION No. : 02 − Jan 09/01

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 : 13
 3.C.(2)(g)5 

 3.C.(2)(g)6 

 3.C.(2)(g)6 a 

 3.C.(2)(g)6 b 

 3.C.(2)(h) 

 3.C.(2)(h)1 

 3.C.(2)(h)1 a 

 3.C.(2)(h)1 b 

 3.C.(2)(h)2 

 3.C.(2)(h)2 a 

 3.C.(2)(h)2 b 

 3.C.(2)(h)3 

 3.C.(2)(h)4 

 3.C.(2)(h)4 a 

 3.C.(2)(h)4 b 

 3.C.(3) 

REVISION No. : 02 − Jan 09/01

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 : 14
 3.D.(1) 

 3.E.(1) 

 3.E.(2) 

 3.E.(3) 

 3.E.(4) 

 3.E.(5) 

 3.E.(6) 

 3.E.(7) 

 3.E.(8) 

 3.E.(9) 

REVISION No. : 02 − Jan 09/01

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 functional test of the

refuel/defuel system (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 : 15
REVISION No. : 02 − Jan 09/01

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 Boom
REVISION No. : 02 − Jan 09/01

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 Boom
REVISION No. : 02 − Jan 09/01

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 Access
REVISION No. : 02 − Jan 09/01

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 Bulletin
REVISION No. : 02 − Jan 09/01

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 Bulletin
REVISION No. : 02 − Jan 09/01

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 Report
REVISION No. : 02 − Jan 09/01

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 Bulletin
REVISION No. : 02 − Jan 09/01

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 Bulletin
REVISION No. : 02 − Jan 09/01

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 :

Accepted for embodiment...........YES/NO

Embodied on MSN :.................................

..................................................

Rejected YES/NO

If YES, please provide

short explanation

From Airline : ..............................................................

 Name/Title : ..............................................................

 Signature : ..................... Date : .............

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 1
REVISION No. : 02 − Jan 09/01

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

Printed in France © Airbus Industrie 1994, All rights reserved

Page : 1 of 1