A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Tel : (33) 5 61-93-33-33

TeLex: AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 57

TITLE: WINGS - INSPECTION OF TOP SKIN AT CENTER SPAR JOINT BETWEEN RIBS 1 AND 7

MODIFICATION No. : None

This page transmits revision No. 04 of Service BuLLetin A300-57-6044.

ADDITIONAL WORK

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

previous revision.

REASON/ACTION

This Service BuLLetin is issued at revision 04 to inform Operators that the inspection is

reinstated for post mod. 10089H5315 aircraft. ALso new inspection threshoLds, repeat

intervaLs and grace periods with FLight Hour (FH) conversion figures have been added to

the AccompLishment TimescaLe to enabLe aircraft to operate to the Extended Service GoaL 2

(ESG2).

CHANGES

SUMMARY:

. AIRBUS address has been amended.

- REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Revision 04 statement has been added.

• Text has been amended and tables have been added to show new

inspection threshoLds, repeat intervaLs and grace periods with FH

conversions.

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 1

Printed in France
A300 -boo

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- EFFECTIVITY

Effectivity has been updated.

- REFERENCES/REPERCUSSIONS

. TFU has been added.

- MANPOWER

. Minor Layout changes.

SERVICE BULLETIN:

• AIRBUS address has been amended.

• Copyright statement has been moved.

- PLANNING INFORMATION

- EFFECTIVITY

- Para. (1) Effectivity has been updated.

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

- Para. (2)(b) Effectivity by operator has been added.

- Para. (2)(c) Effectivity by MSN and kit/configuration has been added-

- REASON

- Para. (1) Revision 04 statement added.

Para. (5) Text amended and Tables added to show inspection thresholds,

repeat intervaLs and grace periods with FLight Hour (FH)

conversions.

- DESCRIPTION

- Para. (2) updated.

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 2

Printed in France
A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- APPROVAL

Approval statement has been amended.

MANPOWER

. Minor Layout changes.

. Minor Layout changes. ALI 57-21-48 added.

- ACCOMPLISHMENT INSTRUCTIONS

Para. A.(2) Reference to repair amended.

Minor Layout changes.

AI/SE-A becomes AIRBUS.

- REPAIR

. AI/SE-A becomes AIRBUS.

- DOCUMENTATION

AI/SE-A becomes AIRBUS.

- APPENDIX

Minor Layout changes.

ACCEPTANCE/REJECTION SHEET:

. Minor Layout changes.

. AIRBUS address has been amended.

DATE: MAR 01/93 SERVICE BULLETIN No. A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 3

Printed in France
A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

FILING INSTRUCTIONS

1. Remove and destroy pages 1 thru 4 of the Summary and pages 1 thru 11 of the

Service BuLLetin. Remove and destroy pages 1 thru 7 of the Appendix 1.

2. Insert pages 1 thru 6 of the Summary and pages 1 thru 18 of the Service

BuLLetin. Insert pages 1 thru 7 of the Appendix 1.

3. RepLace Acceptance/Rejection Letter

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

HISTORY OF PREVIOUS REVISIONS

Revision No. 01 was issued to update the effectivity and change post Modification

visual inspections to LFEC inspections.

Revision No. 02 was issued to revise pre Modification inspections to HFEC and to

make the Service BuLLetin Mandatory.

Revision No. 03 was issued to add crack findings for hole 1A and Repair

Instructions references for hoLes 1, 1A and 2.

REVISION SEQUENCE

ORIGINAL : MAR 01/93

REVISION No. : 01 - NOV 25/94

REVISION No. : 02 - SEP 06/95

REVISION No. : 03 - APR 07/99

REVISION No. : 04 - Aug 19/11

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 4

Printed in France
-IA300-600

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice BeLLonte

31707 BLAGNAC CEDEX FRANCE

Tel : (33) 5 61-93-33-33

TeLex: AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only

and is not approved for modification of the aircraft

MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 57

TITLE : WINGS - INSPECTION OF TOP SKIN AT CENTER SPAR JOINT BETWEEN RIBS 1 AND 7

MODIFICATION No. : None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During full-scale fatigue testing, cracks were found on the top skin of the wing at the

center spar joint between ribs 1 and 7 after approximately 33,000 to 49,000 simulated

f Lights.

There is a possibility of simiLar cracks appearing in service which would need Lengthy,

expensive repairs.

Modification No_ 10089H5315 (Service BuLLetin A300-57.6041) instaLLs an external

reinforcing plate between ribs 1 and 7 at the center spar. This modification may be

embodied at any future time as operators decide_

Modification No. 10160H5328 is the production equivalent of Modification No. 10089H5315

and has been embodied on MSN 723 and subsequent aircraft. For post-mod 10160 modified

aircraft, inspection is adequately covered by Airworthiness Limitation Items (ALI)

57-21-48. Therefore no specific additionaL inspections are required in ISB 57-6044 for

post-MOD 10160 aircraft flying to ESG2.

Revised FC/FH Limits for inspections to temporary repairs are given in TabLe 3.

A permanent repair must be conducted within 250 FC / 550 FH from the embodiment of the

temporary repair.

DATE: MAR 01/93 SERVICE BULLETIN No. : A300 -57 -6044

REVISION No. : 04 Aug 19/11 PAGE : 1
SA300-600

SERVICE BULLETIN

SUMMARY

During the inspection of the fastener hoLes at embodiment of Modification No. 10089H5315,

there have been three reports of cracks found at the fastener hole position 1A. Possible

cracks couLd aLso occur at the adjacent hoLes 1 and 2. Repair Instruction R573 40277 has

been introduced to repair any cracked fastener hoLes in this area. Refer to TabLe 3 for

repeat visuaL inspection requirements for temporary repairs.

On pre Modification No. 10089H5315 aircraft either a DetaiLed VisuaL Inspection (DVI) or

SpeciaL DetaiLed Inspection (SDI) by High Frequency Eddy Current (HFEC) inspection for

cracks in the wing top skin, in the area shown in figure 1, is to be done in accordance

with TabLe 1 or 2 (depending on range) of this Service BuLLetin.

On post Modification No. 10089H5315 aircraft a SpeciaL DetaiLed Inspection (SDI) by Low

Frequency Eddy Current (LFEC) inspection for cracks in the wing top skin, propagating

from under the inboard and rear edges of the reinforcing pLate is required. This

inspection is to be done in accordance with TabLe 1 or 2 (depending on range) of this

Service BuLLetin.

In aLL cases FH Limits are aLso introduced and the inspections are justified to ESG2, see

TabLe 1 or 2 (depending on range).

AccompLishment of this Service BuLLetin is expected to be rendered mandatory by the issue

of an Airworthiness Directive (AD) published by the European Aviation Safety Agency

(EASA). It is anticipated that the AD will confirm the thresholds and/or intervaLs given

beLow but reference should be made to the AD for confirmation of the mandated

accompLishment timescaLe.

NormaL Range Operation

Inspection

Threshold Inspection Interval Inspection Grace Period

Method

FC FH FC FH FC FH

PreMod DVI 14,000 30,300 3,900 8,400 1,500 3,200

10089

PreMod HFEC 14,000 30,300 7,400 16,000 1,500 3,200

10089

PostMod LFEC 17,100 37,100 8,500 18,500 1,500 3,200

10089

TabLe 1: SB A300-57-6044 Inspection Programme for A300B4-600(R) and A30004-600(R)

(NormaL range)

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

I REVISION No. : 04 Aug 19/11 PAGE : 2

Printed in France
ZA300 600

SERVICE BULLETIN

SUMMARY

Short Range Operation (Average FLight Time < 1.5h)

Inspection ThreshoLd Inspection Interval Inspection Grace Period

Method

FC FH FC FH FC FH

PreMod DVI 15,100 22,700 4,200 6,300 1,600 2,500

10089

PreMod HFEC 15,100 22,700 8,000 11,900 1,600 2,500

10089

Post -

Mod LFEC 18,500 27,800 9,200 13,700 1,600 2,500

10089

TabLe 2: SB A300-57-6044 Inspection Programme for A300B4.600(R) and A300C4-600(R)

(Short Range) (SR)

Inspection

Method

ALL Variants

FC FH

DVI 50 110

TabLe 3: Repeat VisuaL Inspections for Temporary Repairs

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

I REVISION No. : 04 Aug 19/11 PAGE : 3

Printed in France
SA300-600

SERVICE BULLETIN

SUMMARY

EFFECTIVITY

This Service BuLLetin is appLicabLe to these Customers:

83V, AAL, AAW, ABD, AMU, CES, DLH, F2I, FOX, GBE, IRA, IRM, JAL, KAC, KAL, LAA,

MNB, MON, MSR, NMB, OHY, QTR, SUD, TAR, THA, UZB

SERVICE BULLETIN TO BE ACCOMPLISHED

PREVIOUSLY OR SIMULTANEOUSLY

None

REFERENCES/REPERCUSSIONS

TFU : 573311002

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

COMPLIANCE

Mandatory

MANPOWER

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 4

Printed in France
S-IA300-600

SERVICE BULLETIN

SUMMARY

I

Aircraft - VisuaL

TOTAL MANHOURS

ELAPSED TIME (HOURS)

Aircraft - HFEC

TOTAL MANHOURS

ELAPSED TIME (HOURS)

Aircraft - LFEC

TOTAL MANHOURS

ELAPSED TIME (HOURS)

MATERIAL INFORMATION

AIRCRAFT DATA

None

EQUIPMENT DATA

Non e

APPENDICES

Appendix 1 - Stop driLLing and pLugging of cracks in the top skin at the center

spar between ribs 1 and 7.

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 5

2.0

1.0

I,4 1

3.0

3.0

Printed in France
A300-600

SERVICE BULLETIN

SUMMARY

STGR 9

STGR 11

STGR 13

STGR 15

TYPICAL SKIN CENTER SPAR

CRACKS AT CENTER BOOM

STRAP

OUTBOARD AFT

DATE : MAR 01/93 SERVICE BULLETIN No. ; A300 -57-6044

I

REVISION No. : 04 Aug 19/11 PAGE 6

Printed in France
WA3O0-600

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

I

TITLE : WINGS - INSPECTION OF TOP SKIN AT CENTER SPAR JOINT BETWEEN RIBS 1 AND 7

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 INFORMATI©N

A.EFFECTIVITY

(1) Aircraft ModeLs

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

(2) Aircraft

(a) Effectivity by MSN

The Service BuLLetin is applicable to aircraft MSN:

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

0361 0365 0368 0380 0388 0398 0401 0405 0408 0411 0414 0417 0423

0459 0460 0461 0462 0463 0464 0465 0466 0469 0470 0474 0477 0479

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 1

Printed in France
A300-600

SERVICE BULLETIN

0505 0506 0507 0508 0509 0510 0511 0512 0513 0514 0515 0516 0517

0518 0521 0525 0529 0530 0532 0536 0540 0543 0546 0553 0554 0555

0556 0557 0558 0559 0560 0561 0563 0566 0569 0572 0575 0577 0579

0581 0582 0584 0601 0602 0603 0604 0605 0606 0607 0608 0609 0610

0611 0612 0613 0614 0615 0616 0617 0618 0619 0621 0623 0625 0626

0627 0628 0629 0630 0631 0632 0633 0635 0637 0639 0641 0643 0645

0657 0659 0662 0664 0666 0668 0670 0673 0675 0677 0679 0681 0683

0685 0688 0692 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713

0715 0717 0719 0721 0722 0755 0758

(b) 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 further 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

83V 0423 0459 0510 0511 0512 0615 0619

AAL 0461 0463 0466 0469 0470 0474 0506

0507 0508 0509 0513 0514 0515 0516

0517 0606 0610 0612 0626 0639 0643

0645 0675

AAW D354

ABD 0529 0557

AMU 0677

CES 0521 0525 0532 0707

DLH 0401 0405

F2I 0284 0294 0301 0307 0312 0317 0321

0336 0341 0348 0351

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 2

Printed in France
JA300-600

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 0726 0728 0735 0736 0738 0742

0745 0748 0752 0757 0759 0760 0761

0766 0768 0769 0771 0772

G8E 0462 0465

IRA 0632 0696

IRM 0380 0408 0411 0414 0532 0546 0608

0618 0623 0701

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

MNB 0758

MON 0540 0556 0604 0605

MSR 0561 0607

NMB 0755

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

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 3

Printed in France
A300-600

SERVICE BULLETIN

OPERATOR MSN

UZB 0717 0722

Modification No.10160H05328 is the production equivalent of Modification

No.10089HO5315 and has been embodied on MSN 723 and subsequent aircraft.

(c) Effectivity by MSN and Kit/Configuration

None

(3) Spares

None

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

I REVISION No. : 04 Aug 19/11 PAGE : 4

Printed in France
SA300-600

SERVICE BULLETIN

B. REASON

(1) History

During fuLL scaLe fatigue testing cracks were found on the top skin

I

of the wing at the center spare joint between ribs 1 and 7 after

approximately 33,000 to 49,000 simuLated fLights.

There is a possibiLity of similar cracks appearing in service which

would need Lengthy, expensive repairs.

Modification No. 10089HG5315 (Service bulletin A300-57-6041)

installs an externaL reinforcing pLate between ribs 1 and 7 at the

center spar. This modification may be embodied at any future time

as operators decide.

Subsequent to the introduction of the modifications there have been

three reports of cracks in the top skin at fastener hoLe 1A. This

hoLe is on the center spar, inboard of rib 1 and immediateLy

adjacent to the inboard edge of the modification externaL pLate.

The investigation of these cracks has shown that the adjacent holes

1 and 2 could aLso become cracked. Because these hoLes are near to

the modification externaL pLate, any cracks need to be found earLy

so that they can be removed by oversizing the hoLes. Repair

Instruction R573 40277 has been issued to give repair details for

these cracked hoLes prior to the embodiment of the modification.

(2) Objectives/Action

(a) Mandatory DetaiLed VisuaL Inspections (DVI) or SpeciaL

Detailed Inspections (SDI) by High Frequency Eddy Current

(HFEC) inspections are required to find cracks in the wing

top skins at the center spare between ribs 1 and 7 on

aircraft that are pre Modification No 10089H05315.

I (b) Mandatory SpeciaL DetaiLed Inspections (SDI) by Low Frequency

Eddy Current (LFEC) inspections are required to find cracks

on aircraft that are post Modification No. 10089H005315.

(3) Advantages

If cracks are found when small this wiLL prevent the need for

expensive repairs.

(4) OperationaL/Maintenance Consequences

None

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

I REVISION No. : 04 Aug 19/11 PAGE - 5

Printed 9n France
A300-600

SERVICE BULLETIN

(5) Accomplishment TimescaLe

(a) Accomplishment of this Service Bulletin is expected to be

rendered mandatory by the issue of an Airworthiness Directive

(AD) published by the European Aviation Safety Agency (EASA).

It is anticipated that the AD wiLL confirm the thresholds

and/or intervaLs given beLow but reference should be made to

the AD for confirmation of the mandated accomplishment

timescaLe.

(b) On pre Modification No. 100891105315 aircraft the initial

threshoLd inspection and repeat inspections are mandatory as

defined in Table 1 or 2 (dependant on range) of this Service

Bulletin.

(c) On post Modification No. 10089HO5315 aircraft the initial

threshoLd LFEC inspection and repeat inspections are

mandatory as defined in Table 1 or 2 (dependant on range)

of this Service Bulletin. I (d) Table 3 of this Service Bulletin gives repeat visual

inspection requirements for any temporary repairs.

Normal Range Operation

Threshold Interval Inspection Grace Period

Inspection Inspection

Method

FC FH FC FH FC FH

PreMod DVI 14,000 30,300 3,900 8,400 1,500 3,200

10089

PreMod HFEC 14,000 30,300 7,400 16,000 1,500 3,200

10089

PostMod LFEC 17,100 37,100 8,500 18,500 1,500 3,200

10089

TabLe 1: SB A300-57-6044 Inspection Programme for A300B4-600(R) and A300C4-600(R)

(Normal range)

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

I

REVISION No. : 04 Aug 19/11 PAGE : 6

Printed in France
A300 -boo

SERVICE BULLETIN

Short Range Operation (Average FLight Time < 1-5h)

Threshold Interval Inspection Grace Period

Inspection Inspection

Method

FC FH FC FH EC FH

PreMod DVI 15,100 22,700 4,200 6,300 1,600 2,500

10089

PreMod HFEC 15,100 22,700 8,000 11,900 1,600 2,500

10089

PostMod LFEC 18,500 27,800 9,200 13,700 1,600 2,500

10089

TabLe 2: SB A300-57-6044 Inspection Programme for A300B4-600(R) and A300C4-600(R)

(Short Range) (SR)

Inspection

Method

ALL Variants

FC FH

DVI 50 110

TabLe 3: Repeat VisuaL Inspections for Temporary Repairs

C.

DESCRIPTION

To accompLish this Service Bulletin it is necessary to:

(1) Identify the area to be inspected and do one of the inspections that

foLLows:

(2) Do one of the following inspections:

(a) If an external reinforcing pLate has not been fitted carry

out a DVI of the reLevant area. If cracking is suspected,

confirm by carrying out a SDI by HFEC inspection.

NOTE : It is recommended that the fastener hoLes 1A, 1 and 2,

outboard of Rib 1 between stringer 11 and the center

spar are inspection by HFEC.

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57.6044

I REVISION No. : 04 Aug 19/11 PAGE : 7

Printed in France
A300-600

SERVICE BULLETIN

(b) If an externaL reinforcing pLate has not been fitted, carry

out a SDI by HFEC inspection.

Cc) If an externaL reinforcing pLate has been fitted, carry out a SDI

by LFEC inspection on the reLevant area.

(3) Repair as necessary.

D. APPROVAL

Approved under EASA Design Organisation Approval No. EASA.21J.031.

If an aircraft Listed in the effectivity has a modification or repair that is

not of AIRBUS origin, and which effects 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.

E MANPOWER

This Service Bulletin is written for an aircraft in a maintenance status. The

manhours/eLapsed time estimates do not include the time to prepare for the

inspection, non-productive elapsed time or administration.

Detailed/General VisuaL Inspection

Get access 0.0

Inspection 2.0

CLose-up 0.0

TOTAL MANHOURS 2.0

ELAPSED TIME (HOURS) 1.0

HFEC/LFEC Inspection

Get access 0.0

Inspection 3.0

CLose-up 0.0

TOTAL MANHOURS 3.0

ELAPSED TIME (HOURS) 3.0

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 8

Printed in France
A300 -boa

SERVICE BULLETIN

F. MATERIAL — COST AND AVAILABILITY

None

G. TOOLING — PRICE AND AVAILABILITY

None

H. WEIGHT AND BALANCE

Not changedI. REFERENCES

Airworthiness Limitation Items

Nondestructive Testing ManuaL (NTM)

Repair Drawings Instructions

Service BuLLetin (SB)

Structural Repair ManuaL (SRM)

J.

PUBLICATIONS AFFECTED

None

57-21-48

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

Part 6, 57-21-58, Part 6.

R571 40141, R573 40277

A300-57.6041

51-10-43

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 9

Printed in France
A300-600

SERVICE BULLETIN

THIS PAGE IS INTENTIONALLY LEFT BLANK

DATE: MAR 01/93 SERVICE BULLETIN No. A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 10

Printed in France
^A300-600

SERVICE BULLETIN

2. ACCOMPLISHMENT INSTRUCTIONS

A.

GENERAL

(1) Preparation

Refer to Figure 1 of this Service Bulletin and get access to the

wing top skin in the area shown.

(2) Standard Practices

For identification of the fastener hole positions at the top skin

center-spar, refer to: Bolt Location Drawings R571 40141 Sheet

Nos. 4 and 5.

B. INSPECTION

Refer Figures 1 and 2.

The procedures that follow are applicable to the LH and RH wings.

(1) On pre Modification 10089HO5313 aircraft you must do steps

(a) and (b) or step (c) as foLLows:

(a) Refer to Figure 1 and do a Detailed Visual Inspection of the

wing top skins and center spar, between ribs 1 and 7.

NOTE : It is recommended that fastener holes 1A, 1 and 2

outboard of Rib 1 between stringer 11 and the center

spare are inspected by SDI by HFEC procedure, refer to

NTM Part 6: 51.10-08. This will make sure that cracks

are detected earLy and the hoLes can be repaired by

oversizing. failure to detect and remove cracks from

these hoLes at an earLy stage can Lead to expensive and

time consuming repairs.

(b) Where you find cracks, or you suspect there are cracks, refer

to NTM Part 6: 51-10-08 and do a SDI and examine the cracks

by HFEC surface inspection and check the size of the cracks.

Use the procedures detailed in SRM: 51-10-13 and report the

findings to AIRBUS.

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 11

Printed in France
A300-600

SERVICE BULLETIN

1 If you find cracks refer to para. C. REPAIR and do the

appLicabLe repair.

2 If you do not find cracks, Close-up the work area.

(c) Do a SDI by HFEC inspection of the wing top skin at the

center spar, between ribs 1 and 7, refer to NTM, Part 6:

51-10.08 and check the size of the cracks. Use the procedures

detailed in SRM: 51-10-13 and report the findings to AIRBUS.

1 If you find cracks refer to para. C. REPAIR and do the

appLicabLe repair.

2 If you do not find cracks, CLose-up the work area.

(2) On post Modification 10089HO5315 aircraft:

(a) Refer to NTM Part 6: 57-21-58 and Refer to Figure 1. Do a SDI

by LFEC inspection at the inboard and rear edges of the top

skin reinforcing pLate. If you find cracks send the detaiLs

of the cracks to AIRBUS for an approved repair.

C.REPAIR

(1) On pre Modification 10089HO5315 aircraft:

(a) If cracks Lengths are not more than the maximum aLLowabLe

crack Length of 75mm per rib bay, as detailed in Figure 2,

then you must do temporary repairs, cracks must be stop

driLLed and plugged, as detaiLed in Appendix 1.

NOTE : Cracks with a visible Length of Less than 6mm do not

need to be stopped driLLed, but they must have repeat

visuaL inspections as given in paragraph 2. C.(l)(b).

I

(b) Repeat visuaL inspections of aLL cracks that have had a

temporary repair, refer to TabLe 3, not exceeding

250FC/550FH, when a permanent repair must be embodied.

(c) If crack Lengths are more than 75mm per rib bay, as shown in

Figure 2, a repair must be done, before the next fLight, by

embodiment of Modification No. 10089H03515 (Service BuLLetin

A300.57-6041).

DATE: MAR 01/93 SERVICE BULLETIN No. : A300.57.6044

I REVISION No. : 04 Aug 19/11 PAGE : 12
JA300-600

SERVICE BULLETIN

(d) If you find cracks at fastener hoLes 1A, 1 and 2 then do the

repair as detailed in: Repair Instruction R573 40277.

(2) On post Modification 10089HO5315 aircraft:

(a) If you find cracks during the inspections in accordance with

ACCOMPLISHMENT INSTRUCTIONS paragraph B.(2)(a), send details

of the cracks to AIRBUS for an approved repair before next

f Light.

D-TEST

None

E. CLOSE-UP

(1) Make sure that the work areas are clean and clear of tools and

other items of equipment.

F. DOCUMENTATION

Use the Inspection Report Form provided in APPENDIX 1 and send the

results of the inspections, incLuding no findings, immediately to AIRBUS.

Refer also to SRM: 51-10-13.

Write in the appLicabLe aircraft records that you have done aLL the work

given in this Service BuLLetin.

DATE: MAR 01/93 SERVICE BULLETIN No : A300-57-6044

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-'g300-600

SERVICE BULLETIN

THIS PAGE IS INTENTIONALLY LEFT BLANK

DATE: MAR 01/93 SERVICE BULLETIN No. : A300.57.6044

REVISION No. : 04 Aug 19/11 PAGE : 14

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SERVICE BULLETIN

STGR 9

^STGR 11

_STGR 13

_-STGR 15

nION

4

TYPICAL SKIN CENTER SPAR

CRACKS AT CENTER B00M

STRAP

OUTBOARD AFT

Typical Skin Cracks at the Center Spar Attachment

Figure 1

DATE : MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04Aug 19/11 PAGE :15

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A300-600

SERVICE BULLETIN

CENT E R SPA R

DIAGRAM DEFINES THE MAXIMUM

ALLOWABLE LENGTH OF A SINGLE

CRACK.

75mm +

(2.9in.)

CENTER SPA R

DIAGRAM DEFINES THE MAXIMUM

ALLOWABLE LENGTH OF A MULTIPLE

CRACK.

75mm

CEN TE R SPA R C ENTER SP AR

75mm

75mm }

Ii (2.9în.)

-\

(2.9în.)

2

<40mm A B

(<1 .61n.)

A+B <40mm (1.61n.)

DIAGRAMS DEFINE THE MAXIMUM

ALLOWABLE CRACK LENGTHS WHEN

ADJACENT HOLES ARE CRACKED.

Definition of Allowable Crack Length

Figure 2

DATE : MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 16

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SERVICE BULLETIN

3. MATERIAL INFORMATION

None

DATE : MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. . 04 Aug 19/11 PAGE : 17

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SERVICE BULLETIN

THIS PAGE IS INTENTIONALLY LEFT BLANK

DATE: MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

I

REVISION No. : 04 Aug 19/11 PAGE : 18

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© A300-600

SERVICE BULLETIN

APPENDIX 01

STOP DRILLING AND PLUGGING OF CRACKS IN THE TOP SKIN AT THE CENTER SPAR BETWEEN

RIBS 1 AND 7

(1) GENERAL.

(a) A crack from a fastener must have a minimum visibLe Length of 6mm

before it can be stop drilled. Also, the distance from the edge of the

crack stop hole to the edge of any other fastener countersink must be

a minimum of 6mm.

(b) Where a crack is too cLose to another fastener to do crack stop repair

the crack details must be reported to AIRBUS and an approved repair

must be done before the next flight.

(c) A crack that has run into unsupported skin must be stop drilled and

pLugged with a blind plug, Refer to Figure 1 .

(d) The stop drill hole and plug can overlap the buttstrap edge if the

crack stops near the edge of the buttstrap. In this case a blind pLug

must be used.

(e) When a crack is stop plugged the total Length that shouLd be recorded

for the inspection records is the length of the crack pLus the

diameter of the plug.

NOT E : UsuaLLy the direction of the cracks will be chordwise.

(2) REPAIR INSTRUCTION

(a) Make sure that the crack stop hoLe is in line with the direction of

the crack.

(b) Make sure that the crack stop hoLe is positioned at the Local

thickness 'T' ahead of the end of the crack (Refer to Figure 1 and

Refer to Figure 2 ).

Cc) Refer to Figure 3 , Operation 1, and drill and de—burr the crack stop

hole.

(d) Do a crack detection in accordance with NTM Part 6: 51-10-01 to make

sure that the crack does not extend beyond the crack stop hole.

(e) Refer to Figure 3 , Operation 2, and end miLL the crack stop hole to

the correct dimensions.

(f) Refer to Figure 3 , Operation 3, and ream the crack stop hole to the

correct dimensions. Make sure that the crack stop hoLe is reamed over

its fuLL depth with a surface finish of 1.6 microns (63 micro inches).

De—burr the crack stop hole.

(g) Refer to Figure 4 and make a pLug to the correct dimensions, with a

surface finish of 1.6 microns (63 micro inches)

(h) Apply a Layer of (Lubricant (Mat. No. 06-005)) to the crack stop plug.

(i) InstaLL the crack stop plug and make sure that it engages the crack

stop hole over its full depth.

(j) If necessary, grind the end of the crack stop plug so that it is in

Line with the surface of the wing skin.

7 DATE : MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

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REVISION No. : 04 Aug 19/11 PAGE : 1 of 7

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SERVICE BULLETIN

APPENDIX 01

(k) Refer to SRM: 51.75-10, P. Block 201 and apply protective treatment

to the crack stop pLug and the surrounding area of the wing skin as

necessary.

DATE : MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

I

REVISION No. : 04 Aug 19111 PAGE : 2

Printed in France
© A300-600

SERVICE BULLETIN

APPENDIX 01

CSK.100°x 0.89/1.D2mm

(0.035/0.04în.)

EXTREMITY OF VISIBLE CRACK

T SKIN

LOCAL THICKNESS T

6.210/6.261mm DIA.

I (0.2445/0.2465in.)

BU TT STRAP

C/L OF PLUG HOLE

(SEE APPENDIX 1 FIGURE 4 FOR DETAILS OF PLUG.)

Crack in Unsupported Skin

Figure 1

DATE : MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 3

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Q A300-600

SERVICE BULLETIN

APPENDIX 01

EXTREMITY OF VISIBLE CRACK

T

// SKIN

L04

BUTTSTRAP

CIL OF PLUG HOLE

(SEE APPENDIX I FIGURE 3 FOR DETAILS OF STOP PLUG HOLE)

(SEE APPENDIX 1 FIGURE 4 FOR DETAILS OF PLUG)

Crack in the Skin

Figure 2

DATE . MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 4

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SERVICE BULLETIN

APPENDIX 01

DRILL 4.762mm (0.1875in.) DIA.

0.6410.89mm

(0.025/0.035in.)

*—ENDMILL5.951mm (0.2343în.) DIA.

0.76/1.02mm (0.03/0.04in.) RAD. (0.040/0.045in.)

6.210/6.261mm r

-REAM (0,2445/0.2465in.) DIA.

CSK.100 ° x 0 89/1.D2m

(0.035/0.04i

0.76/1.02mm (0.03/0.041n.) RAD. !(0.045/0.050în.)

Details of the Plug Stop HoLe

Figure 3

DATE : MAR 01/93 SERVICE BULLETIN No. : A300 -57-6044

REVISION No. : 04 Aug 19/11 PAGE 5

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© A300-600

SERVICE BULLETIN

APPENDIX 01

LENGTH AS SKIN THICKNESS

0.13mm(O.QDSin.)

Ÿ'

0.76mm(0.030in.)

0.89/1.02mm

(0.035/0.040in.)

(IF THE PLUG IS TO BE FITTED IN

UNSUPPORTED SKIN, DO NOT DRILL

THIS HOLE)

DETAIL OF PLUG

MAKE FROM BOLT No. HL803PN-8

OR HLT950PN-8

SKIN SKIN

BUTTSTRAP

Detail of the PLug

Figure 4

DATE : MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

I

REVISION No. : 04 Aug 19111 PAGE : 6

Printed in France
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A300 SB NO: INSPECTION REPORT FORM

A/C MSN DATE OF INSPECTION:

FLIGHT CYCLES INSPECTION METHOD: E VISUAL

FLIGHT HOURS . F N.D.T.

FINDING YES L NO El IF YES, CRACK CONFIRMED BY,

(SPECIFY NDT METHOD USED TO CONFIRM CRACK)

USE A SKETCH TO SHOW PARAMETER TO BE USE A TABLE TO SHOW RECORDS OF

RECORDED (FOR EXAMPLE; CRACK LENGTH, DEPTH, REQUIRED PARAMETERS

EDGE MARGIN) (HOLE NUMBER, CRACK LENGTH, REPAIR BY OVERSIZE)

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

ElSB. ElS.R.M.El AIB INSTRUCTIONS

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A300-600

SERVICE BULLETIN

ACCEPTANCE/REJECTION SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice BELLONTE

31707 BLAGNAC CEDEX FRANCE

Tel: (33) 5 61-93-33-33

Telex: AIRBU 530526 F

TITLE : WINGS —INSPECTION OF TOP SKIN AT CENTER SPAR JOINT BETWEEN RIBS 1 AND 7

MODIFICATION No. : NONE ATA SYSTEM : 57

IS BEING HEREWITH SUBMITTED TO YOU FOR REVIEW

PLease fill : .._REJECTED

._.WILL BE EMBODIED

...EFFECTIVITY

This SB can only be incorporated in your "customized"

documentation within the agreed time scheduLe in so far as this

sheet returned to us on purchase date and signed by a duly

authorized and empowered officer or representative.

FROM : PLease return to

AIRLINE : AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

NAME : 31707 BLAGNAC CEDEX FRANCE

• Attn : AI/SE—D32 Technical Data

DATE : and Documentation Services

FAX : (+33) 5 61 93 28 06

7 DATE : MAR 01/93 SERVICE BULLETIN No. : A300-57-6044

REVISION No. : 04 Aug 19/11 PAGE : 1 of 1

Printed in France