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 - OUTER WING - INSPECT FRONT AND REAR SPAR BOTTOM BOOM - INBOARD AND

OUTBOARD OF RIB 9

MODIFICATION No. : None

This page transmits revision No. 04 of Service BuLLetin A300-57.6037.

ADDITIONAL WORK

No additionaL work is required by this revision for aircraft inspected by any previous

revisionREASON

This Service BuLLetin has been issued at revision 04 to inform Operators that revised

inspection threshoLds, repeat intervaLs and grace periods have been introduced to support

aircraft operations to Extended Service GoaL 2 (ESG2). The new accomplishment timescaLes

are different for normaL range or short range operations. ALso the Repair procedure has

been revised.

CHANGES

SUMMARY:

. AIRBUS address has been amended.

- REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Text has been amended to add reference to the inspection

threshoLds and repeat intervaLs.

Modification 08842H5298 (Service BuLLetin A300-57-6039) sentence added.

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

REVISION No. : 04 Feb 24/11 PAGE : 1

Printed in France
îA300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- EVALUATION TABLE

. Potential AD changed to YES.

- EFFECTIVITY

. Effectivity has been updated.

SERVICE BULLETIN:

AIRBUS address has been amended.

Airbus Industrie has been changed to AIRBUS in the copyright statement.

PLANNING INFORMATION

- EFFECTIVITY

Para. (2)(a) Effectivity has been updated.

Para. (2)(b) Effectivity has been updated.

DESCRIPTION

. Para. (9) reference to functionaL test deLeted and system Leak test added.

COMPLIANCE

ACCOMPLISHMENT TIMESCALE

Para. (a) Airworthiness Directive (AD) statement has been updated.

Para. (b) Text and Tables have been added to incLude the revised inspection

thresholds, repeat intervaLs and grace periods.

. Para. (c) Text and table have been added for recommended embodiment of Mod.

08842H5298 (SB A300-57-6039).

- APPROVAL

. Approval statement has been amended.

REFERENCES

. References have been amended.

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

REVISION No. : 04 Feb 24/11 PAGE : 2

Printed in France
A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- ACCOMPLISHMENT INSTRUCTIONS

- INSPECTION

• Para. (2)(c) New paragraph reLated to post mod. 08842H5298

(SB A300-57-6039) has been added.

- REPAIR

. Repair procedure has been revised.

- TEST

System Leak test has been revised.

FIGURE 4

. Figure 4 has been deLeted and Figure 6 becomes Figure 4.

- FIGURE 5

. Figure 5 has been deLeted and new Figure has been added.

REPORTING SHEET:

. Airbus Industrie becomes Airbus.

AIRBUS address has been amended.

QUALITY PERCEPTION FORM:

AIRBUS address has been amended.

FILING INSTRUCTIONS

1. Remove and destroy pages 1, 2 and 3 of the Summary, pages 1, 2, 3, 4, 5, 6, 9,

10, 11, 12, 13, 14, 15, 16, 19/20, 21/22 and 23 of the Service BuLLetin, page 1

of 1 of the Reporting Sheet and page 1 of 1 of the QuaLity Perception Form.

2. Insert pages 1, 2 and 3/4 of the Summary, pages 1, 2, 2a, 2b, 3, 4, 5, 6, 9, 10,

11, 12, 13, 14, 14a, 14b, 14c, 14d, 15, 16, 16a, 16b, 16c, 16d, 19 and 20 of the

Service BuLLetin, page 1 of 1 of the Reporting Sheet and page 1 of 1 of the

QuaLity Perception Form.

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

REVISION No. : 04 Feb 24/11 PAGE : 3

Printed in France
A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Put this Revision TransmittaL Sheet in front of the Service BuLLetin.

HISTORY OF PREVIOUS REVISIONS

This is only appLicabLe for Revision 04 and subsequent. If information is required

for revisions issued previous to this, please check your copies of Revision

TransmittaL Sheet or contact AIRBUS.

REVISION SEQUENCE

ORIGINAL : Aug 01/94

REVISION No. : Dl - Aug 31/95

REVISION No. : 02 - Jan 09/01

REVISION No. : 03 - Jan 11/02

REVISION No. : 04 - Feb 24/11

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

REVISION No. : 04 Feb 24/11 PAGE : 4

Printed in France
A300-600

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Te L : (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 - 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 the thresholds and repeat intervals

given in the Accomplishment TimescaLe.

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.

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

REVISION No. : 04 Feb 24/11 PAGE : 1

Printed in France
© A300-600

SERVICE BULLETIN

SUMMARY

EVALUATION TABLE

COMPLIANCE MANDATORY CANCELS INSPECTION

SB

NO

POTENTIAL AD YES A/C OPERATION

AFFECTED

NO

RELIABILITY

AFFECTED

NO PAX COMFORT

AFFECTED

NO

COST SAVING YES ETOPS AFFECTED NO

STRUCTURAL LIFE

EXTN

NO VENDOR SB INVOLVED NO

KIT PRICE (USD) NO KIT

EFFECTIVITY

This Service BuLLetin is applicable to these operators:

AAL, AWW, ABD, AMU, BKV, CES, DLH, F21, FDX, G8E, IRA, JAL, KAC, KAL, LAA, MON,

NSR, OHY, QTR, SUD, TAR, THA, UZB

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

REVISION No. : 04 Feb 24/11 Page : 2

Printed in France ©Airbus industrie 1994, Al rights reserved
WA L'7a Ti WTaTa

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

REVISION No. : 04 Feb 24/11 Page : 3/4

Printed in France ©Airbus Industrie 1994, Al rights reserved
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 -- OUTER WING - INSPECT FRONT AND REAR SPAR BOTTOM BOOM - INBOARD

AND OUTBOARD OF RIB 9

MODIFICATION No. : None

This document contains AIRBUS PROPRIETARY INFORMATION and shaLL at aLL times remain

the property of AIRBUS; no inteLLectuaL property right or License is granted by

AIRBUS in connection with any information contained in it. It is deLivered on the

express condition that said document and the information contained in it shaLL be

treated as confidentiaL, shaLL not be used for any purpose other than that for which

it is hereby deLivered. It shaLL not be disclosed in whoLe or 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

A.EFFECTIVITY

(1) ModeLs

B4-601, B4-603, B4-605R, B4-620, B4-622, B4.622R, C4-620

(2) Aircraft

(a) Effectivity by MSN

The Service Bulletin is appLicabLe to aircraft MSN:

0284 0294 0301 0307 0312 0317 0321 0336 0341 0344 0348 0351 0354 0358

0361 0365 0368 0380 0388 0398 0405 0408 0411 0414 0417 0423 0459 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

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57.6037

I

REVISION No. : 04 Feb 24/11 PAGE : 1

Printed in France
$A300 -boo

SERVICE BULLETIN

0530 0532 0536 0540 0543

0561 0563 0566 0569 0572

0604 0605 0606 0607 0608

0618 0619 0621 0623 0625

0637 0639 0641 0643 0645

0677 0679 0681 0683 0685

0709 0711 0713 0715 0717

0546 0553

0575 0577

0609 0610

0626 0627

0657 0659

0688 0692

0719 0721

0554

0579

0611

0628

0662

0694

0722

0555 0556

0581 0582

0612 0613

0629 0630

0664 0666

0696 0699

0557

0584

0614

0631

0668

0701

0558

D601

0615

0632

0670

0703

0559 0560

0602 0603

0616 0617

0633 0635

0673 0675

0705 0707

NOTE : This Service BuLLetin is appLicabLe to aircraft premodification 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. 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 0423 0459 0460 0461 0463 0466 0469

0470 0474 0506 0507 0508 0509 0510

0511 0512 0513 0514 0515 0516 0517

0606 0610 0612 0615 0619 0626 0639

0643 0645 0675

AAW 0354

ABD 0529 0557

AMU 0677

BKV 0411 0414 0546 0553 0608

CES 0521 0525 0532 0707

DLH 0380 0405 0408 0618 0623 0701

F21 0284 0294 0301 0307 0312 0317 0321

0336 0341 0348 0351

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

REVISION No. : 04 Feb 24/11 PAGE : 2

Printed in France
^A3O0-boo

SERVICE BULLETIN

OPERATOR MSN

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

IRA 0632 0696

JAL 0602 0617 0621 0637 0641 0670 0679

0683 0703 0711

KAC 0344 0673 0694 0699 0719 0721

KAL 0582 0609 0627 0631 0662 0685 0692

LAA 0601 0616

MON 0540 0556 0604 0605

MSR 0561 0607

OHY 0584 0603

QTR 0554 0560 0614

SUD 0666

TAR 0505 0558 0563

THA 0368 0398 0464 0518 0566 0569 0577

0628 0629 0635 0681 0705

UZB 0717 0722

(c) Effectivity by MSN and Kit/Configuration

None

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

REVISION No. : 04 Feb 24/11 PAGE : 2a

Printed in France
S A300-600

SERVICE BULLETIN

(3) Spares

None

B.CONCURRENT REQUIREMENTS

None

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

I REVISION No. : 04 Feb 24/11 PAGE : 2b

Printed in France
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

repai rs.

(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 system Leak

test of the refuel/defueL system.

E. COMPLIANCE

(1) Classification

Mandatory

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

I

REVISION No. : 04 Feb 24/11 Page : 3

Printed in France © Airbus Industrie 1994, AlI rights reserved
A300 -boa

SERVICE BULLETIN

(2) AccompLishment TimescaLe

(a) Accomplishment of this Service BuLLetin has been rendered mandatory

by the issue of an Airworthiness Directive (AD) published by the

European Aviation Safety Agency (EASA). The AD must be used as the

reference document for the mandatory accomplishment timescaLe.

(b) Mandatory instructions of the front and rear spar bottom booms,

inboard and outboard of Rib 9, are to be done at or before the

threshoLds and subsequent repeat intervals given in Tables 1 and 2.

TabLe 1 NormaL Range Operations

ThreshoLd Repeat IntervaL Grace Period Inspection

Inspection Method

FC FH FC FH FC FH

Pre Mod. US 14,100 30,400 3,900 8,400 1,600 3,400

08842

Post Mod.

08842 or US 14,100 30,400 3,900 8,400 1,600 3,400

R571 40657

TabLe 2 Short Range Operations (Average Flight Time < 1-5 hours)

ThreshoLd Repeat Interval Grace Period Inspection

Inspection Method

FC FH FC FH FC FH

Pre Mod. US 15,200 22,800 4,200 6,300 1,700 2,500

08842

Post Mod.

08842 or US 15,200 22,800 4,200 6,300 1,700 2,500

R571 40657

(c) Modification 08842H5298 (SB A300-57-6039) is recommended for

embodiment at the threshoLds given in TabLe 3.

TabLe 3 Recommended Embodiment of Modification 08842H5298 (SB A300-57-6039)

Embodiment Point

NormaL Operation Short Range

FC FH FC FH

14,100 30,400 15,200 22,800

DATE: Aug 01/94 SERVICE BULLETIN No. : A300-57.6037

REVISION No. : 04 Feb 24/11 PAGE : 4

Printed in France
A300 -600

SERVICE BULLETIN

(d) 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

f Light.

F. APPROVAL

Approved under EASA Design Organisation Approval EASA.21J.031. If the aircraft

Listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, which affects the content of this Service BuLLetin, the

operator is responsible for obtaining approval by its airworthiness authority

for any adaptation necessary before incorporation of the Service BuLLetin.

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 experience 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

Inspection

Test

CLose up

TOTAL MANHOURS

ELAPSED TIME (HOURS)

DATE: Aug 01/94

7.0

1.0

1.0

7.0

16.0

6.0

SERVICE BULLETIN No. : A300.57-6037

I

REVISION No. : 04 Feb 24/11 PAGE : 5

Printed in France
A300-600

SERVICE BULLETIN

H.

I

J

K

L.

WEIGHT AND BALANCE

Not changed

ELECTRICAL LOAD DATA

None

REFERENCES

Aircraft Maintenance Manual (AMM)

Structural Repair ManuaL (SRM)

Nondestructive Testing ManuaL (NTM)

Service Bulletin (SB)

Repair Instruction

Maintenance Review Board (MRB)

Airworthiness Directive

PUBLICATIONS AFFECTED

None

INTERCHANGEABILITY/MIXABILITY

None

12-11-28 24-00-00 24-41-00 28.00-00

28-10-00 28-11-22 28.11-29 28-25-15

28-25-18 28-25-22 28-42-44 32-12-11

32-12-11

51-10-13 51-40 -21 51-40-44

51-40-47 51-43-00 51-75-10

51.75-20 51-76-20

51-10-01 Part 6 51-10-08 Part 6

57-21-04 Part 4

A300-57-6039

R571 40141

Section D, Para.8

94-208-169 (B)

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

REVISION No. : 04 Feb 24/11 PAGE : 6

Printed in France
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.

Hole

Nominal

Fastener

First

Oversize

Fastener

Second

Oversize

Fastener Nut Washer

S NSA5486V6R18N NSA5487V6R18N NSA54SSV6R18N NSA5472-6K7 NSA5353DO6B

T NSA5486V7R19N NSA5487V7R19N NSA5488V7R19N NSA5472-7K7 NSA5353DO7B

U NSA5486V7R24N NSA5487V7R24N NSA5488V7R24N NSA5472-7K7 NSA5353D07B

V NSA5486V6R21N NSA5487V6R21N NSA5488V6R21N NSA5472-6K7 NSA5353DO6B

W NSA5486V6R18N NSA5487V6R18N NSA5488V6R18N NSA5472-6K7 NSA5353DO6B

X NSA5486V7R21N NSA5487V7R21N NSA5488V7R21N N5A5472-7K7 NSA5353D07B

Y NSA5486V7R21N NSA5487V7R21N NSA5488V7R21N NSA5472-7K7 NSA5353D07B

Z NSA5486V6R18N NSA5487V6R18N NSA5488V6R18N NSA5472-6K7 NSA5353D06B

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

REVISION No. : 04 Feb 24111 Page 7

Printed in France ©Airbus Industrie 1994, AlI rights reserved
SERVICE BULLETIN

This Page Intentionally Left Blank

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

I REVISION No. : 04 Feb 24/11 Page : 8

Printed in France ©Airbus Industrie 1994, Al rights reserved
W A300--600

SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERA L

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 301

and 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 ANN 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

I REVISION No. : 04 Feb 24/11 Page : 9

Printed in France ©Abus Industrie 1994, All rights reserved
A300-600

SERVICE BULLETIN

B.INSPECTION

(1) Do an inspection of the front and rear spar flange, adjacent to the

fastener hoLes (Refer to NTM 57-21-04, Part 4 if boLts are instaLLed, or

NTM 51-10-01, Part 6 procedure C if boLts are removed), 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).

I

(c) If modification 08842H5298 (SB A300-57-6039) has already been

embodied do the worksteps in para.C.REPAIR (3).

(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 AIRBUS

BEFORE ANY FURTHER ACTION IS TAKEN.

I (1) To repair cracked fastener hoLes found during the inspection, do the

worksteps that foLLow:

(a) Remove the fastener where a crack was detected and do a roto -probe

inspection of 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 do a roto -probe inspection of the

reamed hoLe (Refer to NTM 51-10-01, Part 6, Procedure C).

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

REVISION No. : 04 Feb 24/11 PAGE : 10

Printed in France
A300-600

SERVICE BULLETIN

a If a crack is not indicated, instaLL the correct

diameter fastener and continue with the inspection

programme.

b If a crack is indicated, do the worksteps in para.

C.(1) (b).

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

Inspect the hoLes, where fasteners were removed in workstep

C.(1) (b). for cracks (Refer to NTM 51-10-01, Part 6,

Procedure C).

If cracks are not indicated record aLL findings and

contact AIRBUS for an approved repair to be embodied

before the next fLight.

b If cracks are indicated, do the worksteps in

para.C.(1) (c) 2.

2 Inspect the top surface of the structure around the hoLe(s)

circumference for cracks (Refer to NTM 51-10-08, Part 6).

a If a crack is indicated, record aLL findings and

contact AIRBUS for an approved repair to be embodied

before the next fLight.

b If additional 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(s) to the first oversize

diameter.

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

REVISION No : 04 Feb 24/11 PAGE : 11

Printed in France
A300-600

SERVICE BULLETIN

4 Inspect the oversize fastener hoLe(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure C).

a If the cracks are completely removed by the first

oversizing, record aLL findings and actions taken and

contact AIRBUS for an approved repair 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 hoie(s) to the second oversize

diameter.

6 Inspect the oversize fastener hoLe(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure C). Record aLL findings and

actions taken and contact AIRBUS for an approved repair to be

embodied before the next fLight.

(d) ParalLeL HoLes

1 Inspect the hoLes, where fasteners were removed in workstep

C.(1) (b), for cracks (Refer to NTM 51-10-01, Part 6,

Procedure A)-

a If cracks are not indicated, record aLL findings and

contact AIRBUS for an approved repair 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(s)

circumference for cracks (Refer to NTM 51-10-08, Part 6).

a If a crack is indicated, record aLL findings and

contact AIRBUS for an approved repair to be embodied

before the next fLight.

b If additionaL cracks are not indicated at the top

surface to the worksteps in para.C.(1) Cd) 3 and 4.

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

REVISION No. : 04 Feb 24/11 PAGE : 12

Printed in France
A300-600

SERVICE BULLETIN

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 AIRBUS BEFORE YOU DO THE COLD EXPANSION THAT

FOLLOWS.

3 Oversize the cracked fastener hole(s) to the coLd expansion

start hoLe diameter for the first oversize fastener.

4 Inspect the oversize fastener hoLe(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure A)-

a If aLL crack indications have been removed, record aLL

findings and actions taken and contact AIRBUS for an

approved repair to be embodied before the next fLight.

b If a crack is stiLL indicated, do the worksteps in

para.C.C1) Cd) 5 and 6.

5 Ream the cracked fastener hoLe(s) to the second oversize

coLd working start diameter.

6 Inspect the oversize fastener hole(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure A).

a If a crack is stiLL indicated do the worksteps on

para.C.(1) (d) 7 and 8.

b If the cracks are compLeteLy removed by second

oversizing record aLL findings and actions taken and

contact AIRBUS for an approved repair which is to be

embodied before the next fLight.

7 Ream the cracked fastener hole(s) to the next nominal coLd

working start diameter.

8 Inspect the oversize fastener hoLe(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure A).

a If the cracks are not removed by oversizing, record aLL

findings and actions taken and contact AIRBUS for an

approved repair to be embodied before the next fLight.

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

I REVISION No. . 04 Feb 24/11 PAGE : 13

Printed in France
} A300-600

SERVICE BULLETIN

b If the cracks are compLeteLy removed by oversizing

record all findings and actions taken and contact

AIRBUS for an approved repair to be embodied

before the next flight.

(2) To repair cracked holes found during accomplishment of Modification No.

08842H5298 (SB A3D0-57-6039), do the worksteps that foLLow:

(a) Inspect the top surface of the structure around the hoLe(s)

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.

CAUTIONTHE 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(s) to the first oversize diameter.

(c) Inspect the oversize fastener hoLe(s) for cracks (Refer to NTM 51-

10-01, Part 6, Procedure C).

1 If the crack indications are compLeteLy removed do para.C.(2)

(f).

2 If a crack is stilL indicated do the worksteps in para.C.(2)

(d) and (e).

(d) Ream the cracked fastener hoLe(s) to the second oversize diameter.

(e) Inspect the oversize fastener hoLe(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure C).

1 On completion of the inspection do para.C.(2) (f).

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

REVISION No. : 04 Feb 24/11 PAGE : 14

Printed in France
A300-600

SERVICE BULLETIN

(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 hoLes, where fasteners were removed in workstep

C.(2) (f), for cracks (Refer to NTM 51-10-01, Part 6,

Procedure C).

a If cracks are not indicated record aLL findings and

contact AIRBUS for an approved repair to be embodied

before the next fLight.

b If the crack is indicated do the worksteps in

para.C.(2) (g) 2.

2 Inspect the top surface of the structure around the hoLe(s)

circumference for cracks (Refer to NTM 51-10-08, Part 6).

a If a crack is indicated at the top surface, record aLL

findings and contact AIRBUS for an approved repair to

be embodied before the next fLight.

b If additional 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 0.751N. (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(s) to the first oversize

diameter.

4 Inspect the oversize fastener hoLe(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure C).

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

REVISION No. : 04 Feb 24/11 PAGE : 14a

Printed in France
A3oo - 600

SERVICE BULLETIN

I

a If the crack indications are compLeteLy removed by

first oversizing, record aLL findings and actions taken

and contact AIRBUS for an approved repair 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.

J 5 Ream the cracked fastener hoLe(s) to the second oversize

diameter.

6 Inspect the oversize fastener hole(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure C). Record aLL findings and

actions taken and contact AIRBUS for an approved repair to be

embodied before the next flight.

(h) ParaLLeL Holes

1 Inspect the holes, where fasteners were removed in workstep

C.(2) (f), for cracks (Refer to NTM 51-10-01, Part 6,

Procedure A).

a If cracks are not indicated, record aLL findings and

contact AIRBUS for an approved repair to be embodied

before the next Right.

b If a crack is indicated at the fastener hoLe(s), do the

worksteps in para.C.(2) (h) 2.

2 Inspect the top surface of the structure around the hoLe(s)

circumference for cracks (Refer to NTM 51-10-08, Part 6).

a If the crack is indicated, record aLL findings and

contact AIRBUS for an approved repair to be embodied

before the next fLight.

b If additional 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.

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

REVISION No. : 04 Feb 24/11 PAGE : 14b

Printed in France
A300-600

SERVICE BULLETIN

CAUTION

CONTACT AIRBUS BEFORE YOU DO THE COLD EXPANSION

THAT FOLLOWS.

3 Oversize the cracked fastener hole(s) to the coLd expansion start

hole diameter for the first oversize fastener.

4 Inspect the oversize fastener hoLe(s) for cracks (Refer to NTM

51-10-01, Part 6, Procedure A).

a If aLL crack indications have been removed, record aLL

findings and actions taken and contact AIRBUS for an approved

repair to be embodied before the next fLight.

b If a crack is stiLL indicated, do the worksteps in para.C.(2)

(h) 5 and 6.

5 Ream the cracked fastener hoLe(s) to the second oversize coLd

working start diameter.

6 Inspect the oversize fastener hoLe(s) for cracks (Refer to

NT1 51-10-01, Part 6, Procedure A).

a If a crack is still indicated do the worksteps on para.C.(1)

(h) 7 and 8.

b If the cracks are compLeteLy removed by second oversizing

record aLl findings and actions taken and contact AIRBUS for

an approved repair to be embodied before the next flight.

7 Ream the cracked fastener hoLe(s) to the next nominal coLd working

start diameter.

8 Inspect the oversize fastener hoLe(s) for cracks (Refer to

NTM 51-10-01, Part 6, Procedure A).

a If the cracks are not removed by oversizing, record all

findings and actions taken and contact AIRBUS for an

approved repair to be embodied before the next fLight.

b If the cracks are completely removed by oversizing

record aLL findings and actions taken and contact

AIRBUS for an approved repair to be embodied before the next

ftight.

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

REVISION No. : 04 Feb 24/11 PAGE : 14c

Printed in France
'A3oo -boo

SERVICE BULLETIN

(3) Remove the fastener where a crack was detected and do a roto -probe inspection

to confirm the indication (Refer to NTM 51-10-01, Part 6, Procedure C).

(a) If a crack is not indicated, contact AIRBUS for an approved repair

to be embodied before the next fLight.

(b) If a crack is indicated, inspect the top surface around the cracked

fastener hoLe (Refer to NTM 51-10-08, Part 6). Remove the four adjacent

fasteners on both sides of the cracked fastener hoLe. Do a roto -probe

inspection of the eight fastener hoLes (Refer to NTM 51-10-10, Part 6,

Procedure C).

1 If cracks are not indicated in the eight fastener hoLes, record alL

findings and contact AIRBUS for an approved repair to be embodied

before the next fLight.

2 If cracks are indicated, inspect the top surface around the cracked

fastener hoLes (Refer to NTM 51-10-08, Part 6). Record aLL findings

and contact AIRBUS for an approved repair to be embodied before the

next fLight.

(4) ResuLts of inspections, including niL findings and repair actions, must be sent

immediately to AIRBUS after compLetion of the inspection/repairs. Use the

Inspection Report (Figure 4) provided 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).

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

I

REVISION No. : 04 Feb 24/11 PAGE : 14d

Printed in France
A300-600

SERVICE BULLETIN

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.

Note : This procedure is applicable to aircraft with the refuel coupling

is on the RH wing.

(a) Job Set-Up

1 Open access door 144DR.

2 On panel 110VU, make sure that TRANSF. VALVE switch is in

CLOSED position and guarded.

3 Defuel all tanks (Refer to AMM 28-25.00 Page bLock 301).

4 Open main landing gear bay door (Refer to AMM 32-12-11 Page

block 301) and position access platform.

5 Open, safety and tag the foLLowing circuit breakers:

PANEL SERVICE IDENT LOCATION

22VU FUEL/OUTR TK PUMP 2/L TK/CTL 61QA 201/J15

22VU FUEL/OUTR TK PUMP 2/R TK/CTL 68QA 201/J18

132VU FUEL/CTR TK/L PUMP CTL 63QA 322/N58

132VU FUEL/CTR TK/R PUMP CTL 64QA 323/M59

132VU FUEL/L INR TK/PUMP 1/CTL 69QA 322/N60

132VU FUEL/R INT TK/PUMP 1/CTL 60QA 322/N62

132VU FUEL/L INR TK/PUMP 2/CTL 59QA 323/M61

132VU FUEL/R INT TK/PUMP 2/CTL 704A 323/M63

132VU FUEL/L OUTR TK/PUMP 1/CTL 67QA 322/N56

132VU FUEL/R OUTR TK/PUMP 1/CTL 62QA 323/M57

132VU FUEL/X FEED VALVE/MOTOR 1 2QE 324/L60

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

REVISION No. : 04 Feb 24/11 PAGE : 15

Printed in France
A300-600

SERVICE BULLETIN

PANEL SERVICE IDENT LOCATION

132VU FUEL/X FEED VALVE/MOTOR 2 1QE 324/L61

132VU FUEL/FUELLING/XFR/VALVE 2QU 321/P55

6 Position access pLatforms 4.5m (15ft) at each wing.

7 Remove wing tank manhoLe covers 542 CB, (642 CB) between STA71

(RIB 2) and STA 142 (RIB 3) (Refer to AMM 28-11-22 Page bLock

401).

8 Remove center tank manhoLe cover 147AZ (Refer to AMM 28-11-29

Page bLock 401).

9 Remove cadensicon (Refer to AMM 28-42-44 Page bLock 401).

10 Remove drain valve (2) (Refer to AMM 28-25-18 Page bLock 401)

and bLank refuel gallery drain Line (1). Refer to Figure 5.

11 Remove the diffusers (Refer to AMM 28-25-15, Page block 401).

12 Install a bLank, complete with a bleed valve, on each diffuser

Line end (3).

13 Remove reLevant wing tank manhole covers (Refer to AMM

28-11-22 Page bLock 401) to allow inspection of refuel/defuel

Lines.

14 Connect fuel system pressurization unit to one refueL/defueL

coupling.

15 Energize the aircraft electrical network and make certain that

electronic racks are ventilated (Refer to AMM 24-41-00 Page

bLock 301).

16 Make certain that the following circuit breaker is closed:

PANEL SERVICE IDENT LOCATION

132VU FUEL/FUELLING/CTL & REFUEL VALVE 1QU 321/P56

WARNING: BEFORE PRESSURIZING THE AIRCRAFT SYSTEM, THE FUEL SYSTEM

PRESSURIZATION UNIT SAFETY SYSTEM MUST BE SET AND TESTED TO 4 BAR

(58 psi), AND ALL BLANKS SAFELY INSTALLED AND TIGHTENED.

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

I

REVISION No. : 04 Feb 24/11 PAGE : 16

Printed in France
A300-600

SERVICE BULLETIN

(b) Test

ACTION RESULT

1. On paneL 110VU:

- make certain that PWR SUPPLY

switch is in NORM position and

guarded.

- raise guard and pLace MODE

SELECTOR in REFUEL position.

- raise guard and place right

outer tank REFUEL/DEFUEL

VALVES switch in OPEN position.

2. Using fuel system

pressurization unit, fiLL right outer

tank refuel Line with fuel. Bleed at

diffuser line end until Line is fuLL,

then tighten bLeed valve.

3. On paneL 110VU:

- raise guards and pLace each tank

REFUEL/DEFUEL VALVES switch in OPEN

position and fill each tank refuelling

line in sequence.

- bLeed at diffuser blank bLeed

valves.

- Pressurize system to 3.5 bar No Leaks permitted

(51 psi) and maintain pressure

For 15 min.

- Release pressure by opening

diffuser blank bLeed valves.

4. On panel 110VU:

- place aLL REFUEL/DEFUEL VALVES switches

is in NORMAL position and guarded.

- place MODE SELECTOR switch in OFF

position and guarded.

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

REVISION No. : 04 Feb 24/11 PAGE : 16a

Printed in France
A300-600

SERVICE BULLETIN

(c) CLose-Up

1 De-energize the aircraft eLectricaL network (Refer to AMM

24-41-00 Page bLock 301).

2 Disconnect fuel system pressurization unit.

CAUTION: DURING THIS OPERATION THE CONTENTS OF THE REFUEL

LINES WILL DRAIN INTO THE TANKS.

3 Remove blanks from diffuser Line ends (3).

4 InstalL the diffusers (Refer to AMM 28-25-15 Page bLock

401).

5 Remove blank from refuel gaLLery drain (1) and instatL

drain valve (2) (Refer to AMM 28-25-18 Page bLock 401).

6 Install cadensicon (Refer to AMM 28-42-44 Page bLock 401).

7 Make certain that working area is clean and cLear of tooLs

and miscellaneous items of equipment.

8 Install manhole covers (Refer to AMM 28-11-22 Page bLock

401) and (Refer to AMM 28-11-29 Page bLock 401).

9 Remove safety cLips and tags and cLose circuit breakers

61QA, 68QA, 63QA, 64QA, 69QA, 59QA, 60QA, 70QA, 67QA, 62QA,

2QE, 1QE, 2QU.

10 Remove access platforms from each wing.

11 Remove access platform and cLose main Landing gear bay door

(Refer to AMM 32-12-11 Page bLock 301).

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

REVISION No. : 04 Feb 24/11 PAGE : 16b

Printed in France
A300-600

SERVICE BULLETIN

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

I REVISION No. : 04 Feb 24/11 PAGE : 16c

Printed in France
© A300-600

SERVICE BULLETIN

INNER

!AP

STRAP

FRONT

U

NQ

•o

ti

ti

HOLE POSITION S T U V

BOLT LOCATION NO. (REFER 163 164

R571 40141 SHEET 12)

BOLT LOCATION NO. (REFER 7

8 R571 40141 SHEET 16)

WING DATUM PLANE B

® ;

II

1 VIEW ON

I

i i 0 0 O Q II I I

li FWD. FACE

F RONT

of

 SPAR

,^^,^O O' ,000 0 o 0OoÔ io+'r

0)0000 oo Ooh

{ J 5 Î ^"`— I O O O `O _ yQ O O b i ^ -^ L^_^[ I c

--SKIN

4 A I ^ OUTER JOINT STRAP (REF)

UNDER SPAR STRAP (REF) INNER JOINT STRAP (REF)

Figure 1 Sheet 1

HoLes To Be Inspected - Front Spar Bottom Boom

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

REVISION No. : 04 Feb 24/11 Page : 16d

Printed in France © Airbus Industrie 1994, Al rights reserved
1R

HOLE X

u HOLE W

u ^y

¢ i

ti

M

ti

© A300-600

SERVICE BULLETIN

INTERNAL EXTERNAL r UNDER SPAR

JOINT PLATE JOINT PLATE STRAP

HOLE POSITION W X Y 2

BOLT LOCATION NO. (REFER 939 937 R571 40141 SHEET 15)

BOLT LOCATION NO. (REFER 558 557 R571 40141 SHEET 16)

RIB 9 DATUM

o r

¢° 0 0 0 01 0 o 0

O

Oo Q o 0 o

o©

OUT

o

ER REAR INNER REAR

SPAR n SPAR A

FOR WARD

INBOARD A'

HOLE Y

A,.-l--HOLE Z

Figure 2 Sheet 1

Holes To Be Inspected - Rear Spar Bottom Boom

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

I REVISION No. : 04 Feb 24/11 Page : 17

Printed in France ©Airbus Industrie 1994, All rights reserved
N

D

,O

ti

FR(

Sr

CEN'

TAI

VEI

S A300-600

SERVICE BULLETIN

FUEL RIB 10

RTR Q FEED

Figure 3 Sheet 1

RemovaL of the RefueL/Defuel Pipes for Access

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

I

REVISION No. : 04 Feb 24/11 Page : 18

Printed in France © Arrbus Industrie 1994, AJI rights reserved
DB7 57 6037 AG AA C

A300 SB No.

A/C MSN

FLIGHT CYCLES

FLIGHT HOURS

FINDINGS :

A300-57-6037

YES ❑ NO ❑

INSPECTION REPORT

DATE OF INSPECTION

INSPECTION METHOD : VISUAL

NDT

(SPECIFY METHOD)

IF YES, CRACK CONFIRMED BY

(SPECIFY METHOD)

ILLUSTRATION WHICH DEFINES THE PARAMETER TABLE TO INSERT RECORDS OF REQUIRED

TO BE RECORDED (E.G_ CRACK LENGTH, CRACK PARAMETERS (E.G. HOLE No., CRACK LENGTH,

DEPTH, EDGE MARGIN ETC.). REPAIR BY OVERSIZE ETC.).

PLEASE LIST OTHER FINDINGS, EXCLUDING CRACK. AREA REPAIRED IN ACCORDANCE WITH,

SB ❑ SRM AIB INSTRUCTION

D

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7

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S4o.1(-
SA300 -boo

SERVICE BULLETIN

CAL

Li

Figure 5 Sheet 1

RefueL / DefueL System - Leak Test

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

REVISION No. : 04 Feb 24/11 PAGE: 20

Printed in France
© 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 BE embodied . . . . . . . . . . . . . .YES/NO (if NO pLease comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates

(month/year) of embodiment : . . . . . . . . . . . . . . . . . . . . . . . . . .

B - SB HAS BEEN embodied on aircraft:

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

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

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

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

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

FromAirline . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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 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 1 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.

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

I REVISION No. : 04 Feb 24/11 Page : 1 of 1

Printed in France©Airbus Industrie 1994, At rights reserved
A3

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

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

or via your Resident Customer Support Office.

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

I

REVISION No. : 04 Feb 24/11 Page : 1 of 1

Printed in France ©Airbus Industrie 1994, AJI rights reserved