@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 - INSPECT LOWER SKIN PANEL INBOARD OF RIB 9 AND AFT

OF REAR SPAR

MODIFICATION No.: None

This page transmits Revision No.08 of Service Bulletin No.A300-57-6029

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No. 08 issued to clarify the information in Tables 1 through 14.

CHANGES

Tables 1 through 14 up issued.

SUMMARY

MODIFICATIONS Minor editorial or document structure change N

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

Minor editorial or document structure change N

GENERAL EVALUATION Minor editorial or document structure change N

MATERIAL PRICE INFORMATION Minor editorial or document structure change N

EFFECTIVITY Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REFERENCES / REPERCUSSIONS Minor editorial or document structure change N

NATURE OF THE WORK Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

APPENDICES Minor editorial or document structure change N

Fig. A-USAAA Minor editorial or document structure change N

Fig. A-USAAA Sheet 01 Minor editorial or document structure change N

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 1

7

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@A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

PLANNING INFORMATION

EFFECTIVITY Minor editorial or document structure change N

Configuration definition Minor editorial or document structure change N

CONF 001 Minor editorial or document structure change N

Material Effectivity Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REASON Minor editorial or document structure change N

History Minor editorial or document structure change N

Objective/Action Minor editorial or document structure change N

Advantages Minor editorial or document structure change N

Operational/Maintenance

Consequences

Minor editorial or document structure change N

DESCRIPTION Minor editorial or document structure change N

COMPLIANCE Minor editorial or document structure change N

Classification Minor editorial or document structure change N

Accomplishment Timescale Minor editorial or document structure change N

APPROVAL Minor editorial or document structure change N

Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

Minor editorial or document structure change N

WEIGHT AND BALANCE Minor editorial or document structure change N

ELECTRICAL LOAD DATA Minor editorial or document structure change N

REFERENCES Minor editorial or document structure change N

Minor editorial or document structure change N

PUBLICATION AFFECTED Minor editorial or document structure change N

INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N

SPARES Minor editorial or document structure change N

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY Minor editorial or document structure change N

INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N

LIST OF COMPONENTS Minor editorial or document structure change N

LIST OF MATERIALS - OPERATOR

SUPPLIED

Minor editorial or document structure change N

PARTS TO BE RE-IDENTIFIED BY

OPERATOR

Minor editorial or document structure change N

TOOLING Minor editorial or document structure change N

ACCOMPLISHMENT INSTRUCTIONS

TASK 576029- 832-895-001-INSPECTION Minor editorial or document structure change N

Task associated data - 001 Minor editorial or document structure change N

Subtask 576029-900-402-001 Minor editorial or document structure change N

Subtask 576029-832-403-002 Minor editorial or document structure change N

Subtask 576029-832-404-002 Minor editorial or document structure change N

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 2

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 576029-250-401-001 Minor editorial or document structure change N

Subtask 576029-260-401-001 Minor editorial or document structure change N

Subtask 576029-832-405-001 Minor editorial or document structure change N

Subtask 576029-832-406-001 Minor editorial or document structure change N

Subtask 576029-832-407-001 Minor editorial or document structure change N

Subtask 576029-832-408-001 Minor editorial or document structure change N

Subtask 576029-832-409-001 Minor editorial or document structure change N

Subtask 576029-832-410-001 Minor editorial or document structure change N

Subtask 576029-832-413-001 Minor editorial or document structure change N

Subtask 576029-832-414-001 Minor editorial or document structure change N

Subtask 576029-832-415-001 Minor editorial or document structure change N

Subtask 576029-832-416-001 Minor editorial or document structure change N

Subtask 576029-832-417-001 Minor editorial or document structure change N

Subtask 576029-832-419-001 Minor editorial or document structure change N

TASK 576029- 833-896-001-REPAIR Minor editorial or document structure change N

Task associated data - 001 Minor editorial or document structure change N

Subtask 576029-900-421-001 Minor editorial or document structure change N

Subtask 576029-833-422-002 Minor editorial or document structure change N

Subtask 576029-833-423-001 Minor editorial or document structure change N

Subtask 576029-833-427-001 Minor editorial or document structure change N

Subtask 576029-833-430-001 Minor editorial or document structure change N

Subtask 576029-833-433-001 Minor editorial or document structure change N

Subtask 576029-833-436-001 Minor editorial or document structure change N

Subtask 576029-833-437-001 Minor editorial or document structure change N

Subtask 576029-833-439-001 Minor editorial or document structure change N

Subtask 576029-833-440-001 Minor editorial or document structure change N

Subtask 576029-833-441-001 Minor editorial or document structure change N

Subtask 576029-833-443-001 Minor editorial or document structure change N

Subtask 576029-833-445-001 Minor editorial or document structure change N

Subtask 576029-833-446-001 Minor editorial or document structure change N

Subtask 576029-833-447-001 Minor editorial or document structure change N

Subtask 576029-833-448-001 Minor editorial or document structure change N

Subtask 576029-833-450-002 Minor editorial or document structure change N

Fig. A-UBAAA Minor editorial or document structure change N

Fig. A-UBAAA Sheet 01 Minor editorial or document structure change N

Fig. A-UBAAA Sheet 02 Minor editorial or document structure change N

Fig. A-UBAAA Sheet 03 Minor editorial or document structure change N

Fig. A-UBAAA Sheet 04 Minor editorial or document structure change N

Fig. A-UBAAA Sheet 05 Minor editorial or document structure change N

Fig. A-UBAAA Sheet 06 Minor editorial or document structure change N

Fig. A-UBAAA Sheet 07 Minor editorial or document structure change N

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 3

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@A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Fig. A-UBAAA Sheet 08 Minor editorial or document structure change N

Fig. A-UBAAA Sheet 09 Minor editorial or document structure change N

Fig. A-UBAAA Sheet 10 Minor editorial or document structure change N

Fig. A-UBAAA Sheet 11 Minor editorial or document structure change N

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

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

HISTORY OF PREVIOUS REVISIONS

NOTE: This is only applicable for Revision No. 08 and subsequent. If information is required for

Revisions issued previous to this, please check your copies of Revision Transmittal

Sheets or contact AIRBUS.

REVISION SEQUENCE

ORIGINAL: Apr 28/93

REVISION No. : 08 - Apr 25/13

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 4

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@A300-600

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - INSPECT LOWER SKIN PANEL INBOARD OF RIB 9 AND AFT

OF REAR SPAR

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During routine maintenance, cracks have been found in the wing bottom skin and in the associated

internal support structure on A300 aircraft aft of the rear spar and inboard of rib 9. Initially, cracks were

found in the skin only, starting from a fastener close to the forward outboard corner of access panel

575FB/675FB. Subsequently, cases have been reported of cracks being found in the skin support strap

and the stiffener.

Cracks in the skin were first found on aircraft that had completed between 15,556 and 24,650 FC.

Cracks in the internal support structure were first found on aircraft that had completed between 22,638

and 24,650 FC.

This Service Bulletin is issued to detail a mandatory inspection for cracks in the lower skin and

associated internal support structure aft of the rear spar and inboard of rib 9. Early detection of cracks

in the lower skin and the associated internal support structure will reduce the possibility of having to

carry out expensive and time consuming repairs.

Service Bulletin A300-57-6030 (modification 08488H5253) was introduced to strengthen the area

concerned. The retrofit solution fitted an external plate with second oversize fasteners in cold expanded

holes. The production solution fitted a thicker skin support bracket and door panel surround and

installed interference fit fasteners in cold expanded holes. This modification was found to be inadequate

since cracks occurred after embodiment of the Service Bulletin.

A second Service Bulletin A300-57-6064 (modification 11178H5410) was introduced which further

strengthened the area concerned by fitting an internal and external plate for both the retrofit and

production solutions. Service Bulletin A300-57-6064 superseded Service Bulletin A300-57-6030.

There have been a number of repairs used on in-service aircraft with cracks as follows:

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 1

7

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@A300-600

SERVICE BULLETIN

SUMMARY

- Repair R57140390 fits a crack stop plug in a cold expanded hole and installs an external

reinforcing plate. It was found to be inadequate and was superseded by Repair R57340148.

- Repair R57340148 fits a crack stop plug in a cold expanded hole and installs an external

reinforcing plate with transition fit fasteners in cold expanded holes. This repair did not strengthen

the support structure and when cracks were detected in this area the repair was replaced with

Repair R57340199.

- Repair R57340199 installs an internal and external plate and replaces some of the support

structure. It is currently considered to be the most appropriate repair solution.

- Repair R57340223 is a replacement repair for R57140390 and R57340148. It is considered to be

of an equivalent standard as Repair R57340199.

- Repair R57340218 is a temporary repair which applies a crack stop hole for cracks longer than

30.0mm.

This Service Bulletin requires mandatory inspections of the lower skin and associated internal support

structure aft of the rear spar and inboard of Rib 9.

Early detection of cracks in the bottom skin and the associated internal support structure will reduce the

possibility of having to carry out expensive and time-consuming repairs.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

No Material

EFFECTIVITY

This Service Bulletin is applicable to this (these) operator(s) :

14S 34Z 77T ABD ABR AHK BCS CES F2I FDX G8E I2L IRA

IRM KAC KAL MNB MON MSR MXU OHY QTR RLB SUD TAR THA

TMA U1T UPS URS UZB

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 2

7

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@A300-600

SERVICE BULLETIN

SUMMARY

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 576029-832-895-001: INSPECTION

TOTAL MANHOURS 26.00

ELAPSED TIME (HOURS) 1.50

Task 576029-833-896-001: REPAIR

TOTAL MANHOURS 0.00

ELAPSED TIME (HOURS) 0.00

APPENDICES

None

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 3

7

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@A300-600

SERVICE BULLETIN

SUMMARY

**CONF ALL

REAR SPAR

D_SB_576029_7_SAAA_01_00

575FB (675FB)

RIB9

LH WING SHOWN

RH WING SIMILAR

Figure A-USAAA - Sheet 01

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 4

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All 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 - INSPECT LOWER SKIN PANEL INBOARD OF RIB 9 AND AFT

OF REAR SPAR

MODIFICATION No.: None

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

B4-603 B4-605R B4-620 B4-622 B4-622R C4-605R/F C4-620 F4-605R

F4-622R

(2) Effectivity by MSN

0284 0294 0301 0307 0312 0321 0336 0344 0348 0351 0358 0361 0365 0380 0388

0401 0405 0408 0411 0414 0417 0462 0464-0465 0477 0479 0505-0506 0509 0514

0516 0518 0521 0525 0529-0530 0532 0536 0540 0543 0546 0553-0561 0563 0566

0569 0572 0575 0577 0579 0581-0582 0584 0602-0605 0607-0611 0613-0614

0617-0618 0621 0623 0625-0633 0635 0637 0641 0643 0657 0659 0662 0664 0666

0668 0670 0673 0677 0679 0681 0683 0685 0688 0692 0694 0696 0699 0701 0703

0705 0707 0709 0711 0713 0715 0717 0719 0721-0746 0748-0750 0752-0764

0766-0775 0777-0794 0797 0799-0841 0845-0878

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 1

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SERVICE BULLETIN

(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the time

of issue in accordance with the information available to AIRBUS. Any future changes

resulting from transfer of an aircraft from one operator to another will not be reflected in

this list unless the Service Bulletin is revised for another reason.

OPERATOR MSN

14S 0609

34Z 0685 0692 0731

77T 0838

ABD 0529 0557

ABR 0683 0770

AHK 0855 0856 0857 0858 0859 0860 0870 0871

BCS 0602 0617 0621 0637 0641 0670 0679 0703 0711 0724 0729 0730

0737 0740 0753 0783

CES 0521 0525 0532 0707 0725 0732 0741 0746 0754 0763

F2I 0284 0294 0301 0307 0312 0321 0336 0348 0351 0518 0610

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 0774

0777 0778 0779 0780 0781 0789 0790 0791 0792 0793 0794 0799

0800 0801 0802 0803 0804 0873 0874 0875 0876 0877 0878

G8E 0462 0465 0506 0509 0514 0516

I2L 0677 0743

IRA 0632 0696 0723 0727

IRM 0380 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701

0750 0762 0773

KAC 0344 0673 0694 0699 0719 0721

KAL 0582 0627 0631 0662

MNB 0734 0739 0755 0756 0758

MON 0540 0556 0604 0605

MSR 0561 0607

MXU 0767 0788 0797 0836 0837

OHY 0584 0603 0744 0749 0764

QTR 0554 0560 0614

RLB 0626 0643

SUD 0666 0775

TAR 0505 0558 0563

THA 0464 0566 0569 0577 0629 0635 0681 0705 0782 0784 0785 0786

0787

TMA 0872

U1T 0628

UPS 0805 0806 0807 0808 0809 0810 0811 0812 0813 0814 0815 0816

0817 0818 0819 0820 0821 0822 0823 0824 0825 0826 0827 0828

0829 0830 0831 0832 0833 0834 0835 0839 0840 0841 0845 0846

0847 0848 0849 0850 0851 0852 0853 0854 0861 0862 0863 0864

0865 0866 0867 0868 0869

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 2

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@A300-600

SERVICE BULLETIN

OPERATOR MSN

URS 0733

UZB 0717 0722

(4) Configuration by MSN

MSN CONFIGURATION

0284 0294 0301 0307 0312 0321 0336 0344 0348 0351 0358

0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0462

0464 0465 0477 0479 0505 0506 0509 0514 0516 0518 0521

0525 0529 0530 0532 0536 0540 0543 0546 0553 0554 0555

0556 0557 0558 0559 0560 0561 0563 0566 0569 0572 0575

0577 0579 0581 0582 0584 0602 0603 0604 0605 0607 0608

0609 0610 0611 0613 0614 0617 0618 0621 0623 0625 0626

0627 0628 0629 0630 0631 0632 0633 0635 0637 0641 0643

0657 0659 0662 0664 0666 0668 0670 0673 0677 0679 0681

0683 0685 0688 0692 0694 0696 0699 0701 0703 0705 0707

0709 0711 0713 0715 0717 0719 0721 0722 0723 0724 0725

0726 0727 0728 0729 0730 0731 0732 0733 0734 0735 0736

0737 0738 0739 0740 0741 0742 0743 0744 0745 0746 0748

0749 0750 0752 0753 0754 0755 0756 0757 0758 0759 0760

0761 0762 0763 0764 0766 0767 0768 0769 0770 0771 0772

0773 0774 0775 0777 0778 0779 0780 0781 0782 0783 0784

0785 0786 0787 0788 0789 0790 0791 0792 0793 0794 0797

0799 0800 0801 0802 0803 0804 0805 0806 0807 0808 0809

0810 0811 0812 0813 0814 0815 0816 0817 0818 0819 0820

0821 0822 0823 0824 0825 0826 0827 0828 0829 0830 0831

0832 0833 0834 0835 0836 0837 0838 0839 0840 0841 0845

0846 0847 0848 0849 0850 0851 0852 0853 0854 0855 0856

0857 0858 0859 0860 0861 0862 0863 0864 0865 0866 0867

0868 0869 0870 0871 0872 0873 0874 0875 0876 0877 0878

001

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a

standard configuration; however, the Service Bulletin information is further split into 14

Configurations based on various Repair Instruction and Modification standards as listed

in the 14 Notes below. Operators must select the appropriate Configuration, from the 14

configurations listed below, that describes their aircraft configuration.

NOTE: Configuration 001 is applicable to aircraft which are Pre Service Bulletin

A300-57-6030 (Modification 08488H5253) and do not have a repair embodied.

NOTE: Configuration 002 is applicable to aircraft which are post production

Modification 08488H5253 and do not have a repair embodied.

NOTE: Configuration 003 is applicable to aircraft which are post Service Bulletin

A300-57-6030 (Modification 08488H5253) and have confirmed to AIRBUS that

there was no damage to the internal support structure.

NOTE: Configuration 004 is applicable to aircraft which are post Service Bulletin

A300-57-6030 (Modification 08488H5253) and have not confirmed, to

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 3

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SERVICE BULLETIN

AIRBUS, that there was no damage to the internal support structure.

NOTE: Configuration 005 is applicable to all aircraft with Temporary Repair

R53740218 that have cracks less than 30mm.

NOTE: Configuration 006 is applicable to aircraft with Temporary Repair R57340218

embodied and cracks greater than 30mm that have been stop drilled.

NOTE: Configuration 007 is applicable to aircraft with Repair Instruction R57340199

(small plate) embodied.

NOTE: Configuration 008 is applicable to all aircraft with Repair Instruction

R57340199 (large plate) embodied.

NOTE: Configuration 009 is applicable to aircraft with Repair Instruction R57140390

embodied.

NOTE: Configuration 010 is applicable to aircraft with Repair Instruction R57340148

embodied.

NOTE: Configuration 011 is applicable to aircraft with Repair Instruction R57340223

(small plate) embodied.

NOTE: Configuration 012 is applicable to aircraft with Repair Instruction R57340223

(large plate) embodied.

NOTE: Configuration 013 is applicable to aircraft with Post Retro Modification

11178H5410 (Service Bulletin A300-57-6064) embodied.

NOTE: Configuration 014 is applicable to aircraft with Post Production Modification

11178H5410 embodied.

(6) Material Effectivity

No Material Set

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During routine maintenance, cracks have been found in the wing bottom skin and in the

associated internal support structure on A300 aircraft aft of the rear spar and inboard of

rib 9. Initially, cracks were found in the skin only, starting from a fastener close to the

forward outboard corner of access panel 575FB/675FB. Subsequently, cases have been

reported of cracks being found in the skin support strap and the stiffener.

Cracks in the skin were first found on aircraft that had completed between 15,556 and

24,650 FC. Cracks in the internal support structure were first found on aircraft that had

completed between 22,638 and 24,650 FC.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 4

7

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@A300-600

SERVICE BULLETIN

This Service Bulletin is issued to detail a mandatory inspection for cracks in the lower

skin and associated internal support structure aft of the rear spar and inboard of rib 9.

Early detection of cracks in the lower skin and the associated internal support structure

will reduce the possibility of having to carry out expensive and time consuming repairs.

Service Bulletin A300-57-6030 (modification 08488H5253) was introduced to strengthen

the area concerned. The retrofit solution fitted an external plate with second oversize

fasteners in cold expanded holes. The production solution fitted a thicker skin support

bracket and door panel surround and installed interference fit fasteners in cold expanded

holes. This modification was found to be inadequate since cracks occurred after

embodiment of the Service Bulletin.

A second Service Bulletin A300-57-6064 (modification 11178H5410) was introduced

which further strengthened the area concerned by fitting an internal and external plate

for both the retrofit and production solutions. Service Bulletin A300-57-6064 superseded

Service Bulletin A300-57-6030.

There have been a number of repairs used on in-service aircraft with cracks as follows:

- Repair R57140390 fits a crack stop plug in a cold expanded hole and installs an

external reinforcing plate. It was found to be inadequate and was superseded by

Repair R57340148.

- Repair R57340148 fits a crack stop plug in a cold expanded hole and installs an

external reinforcing plate with transition fit fasteners in cold expanded holes. This

repair did not strengthen the support structure and when cracks were detected in

this area the repair was replaced with Repair R57340199.

- Repair R57340199 installs an internal and external plate and replaces some of

the support structure. It is currently considered to be the most appropriate repair

solution.

- Repair R57340223 is a replacement repair for R57140390 and R57340148. It is

considered to be of an equivalent standard as Repair R57340199.

- Repair R57340218 is a temporary repair which applies a crack stop hole for cracks

longer than 30.0mm.

(2) Objective/Action

This Service Bulletin requires mandatory inspections of the lower skin and associated

internal support structure aft of the rear spar and inboard of Rib 9.

(3) Advantages

Early detection of cracks in the bottom skin and the associated internal support structure

will reduce the possibility of having to carry out expensive and time-consuming repairs.

(4) Operational/Maintenance Consequences

None

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 5

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@A300-600

SERVICE BULLETIN

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 576029-832-895-001: INSPECTION

(1) INSPECTION CONFIGURATION 001

(2) INSPECTION CONFIGURATION 002

(3) INSPECTION CONFIGURATION 003

(4) INSPECTION CONFIGURATION 004

(5) INSPECTION CONFIGURATION 005

(6) INSPECTION CONFIGURATION 006

(7) INSPECTION CONFIGURATION 007

(8) INSPECTION CONFIGURATION 008

(9) INSPECTION CONFIGURATION 009

(10) INSPECTION CONFIGURATION 010

(11) INSPECTION CONFIGURATION 011

(12) INSPECTION CONFIGURATION 012

(13) INSPECTION CONFIGURATION 013

(14) INSPECTION CONFIGURATION 014

Task 576029-833-896-001: REPAIR

(1) REPAIR - CONFIGURATION 001

(2) REPAIR - CONFIGURATION 002

(3) REPAIR - CONFIGURATION 003

(4) REPAIR - CONFIGURATION 004

(5) REPAIR - CONFIGURATION 005

(6) REPAIR - CONFIGURATION 006

(7) REPAIR - CONFIGURATION 007

(8) REPAIR - CONFIGURATION 008

(9) REPAIR - CONFIGURATION 009

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 6

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@A300-600

SERVICE BULLETIN

(10) REPAIR - CONFIGURATION 010

(11) REPAIR - CONFIGURATION 011

(12) REPAIR - CONFIGURATION 012

(13) REPAIR - CONFIGURATION 013

(14) REPAIR - CONFIGURATION 014

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

NOTE: Throughout the configurations that follow, all crack lengths are taken

from the aft skin edge to the forward tip of the crack, regardless of

whether the crack has propagated to the aft skin edge. All crack lengths

specified are considered to be maximum crack lengths.

NOTE: The tables that follow list all the inspection periods in Flight Cycles (FC)

and Flight Hours (FH). The inspection must be done at whichever occurs

first.

NOTE: The ’A’ tables are for A300F4-600R aircraft with an average flight time

greater than 1.5 hours and the ’B’ tables are for A300F4-600R aircraft

with an average flight time less than 1.5 hours.

NOTE: The ’C’ tables are for A300B4-600(R) and A300C4-600(R) aircraft with

an average flight time greater than 1.5 hours and the ’D’ tables are for

A300B4-600(R) and A300C4-600(R) aircraft with an average flight time

less than 1.5 hours.

NOTE: The inspection threshold figures in the tables that follow are taken from

embodiment of the repair or modification unless otherwise specified.

NOTE: Aircraft already in the inspection programme that have or are close to

exceeding the revised FC or FH figures can conduct the inspection at the

previous planned inspection.

Configuration 001

Pre Service Bulletin A300-57-6030 (Modification 08488H5253) Without Repair.

NOTE: The inspection threshold figures in the tables that follow are taken from

aircraft first flight.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 7

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@A300-600

SERVICE BULLETIN

TABLE 1A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspection thresholds and intervals before embodiment of Service Bulletin

A300-57-6030 (Modification 08488H5253) and without any repair.

Threshold Interval Inspection

Technique

FC FH FC FH

8,000 17,200 2,100 4,500

HFEC

Grace period For aircraft that have exceeded the threshold, inspections

must be done within 2,100 FC or 2,500 FH.

TABLE 1B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspection thresholds and intervals before embodiment of Service Bulletin

A300-57-6030 (Modification 08488H5253) and without any repair.

Threshold Interval Inspection

Technique

FC FH FC FH

8,600 12,900 2,200 3,400

HFEC

Grace period For aircraft that have exceeded the threshold, inspections

must be done within 2,200 FC or 3,100 FH.

TABLE 1C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspection thresholds and intervals before embodiment of

Service Bulletin A300-57-6030 (Modification 08488H5253) and without any repair.

Threshold Interval Inspection

Technique

FC FH FC FH

6,300 13,700 1,600 3,500

HFEC

Grace period For aircraft that have exceeded the threshold, inspections

must be done within 1,600 FC or 3,500 FH.

TABLE 1D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspection thresholds and intervals before embodiment of

Service Bulletin A300-57-6030 (Modification 08488H5253) and without any repair.

Threshold Interval Inspection

Technique

FC FH FC FH

6,800 10,200 1,700 2,700

HFEC

Grace period For aircraft that have exceeded the threshold, inspections

must be done within 1,700 FC or 2,700 FH.

Configuration 002

Post Production Modification 08488H5253 without repair.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 8

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@A300-600

SERVICE BULLETIN

NOTE: The inspection threshold figures in the tables that follow are taken from

aircraft first flight.

TABLE 2A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspection thresholds at intervals for aircraft which are post production modification

08488H5253 and do not have a repair embodied.

Inspection

Technique

Inspection

Requirement

Inspection Threshold Inspection Interval

HFEC Inspect bottom FC FH FC FH

skin for cracks

at the historic

crack initiation

site

DVI Inspect the

local support

structure

10,000 21,600 2,800 6,000

TABLE 2B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspection thresholds at intervals for aircraft which are post production modification

08488H5253 and do not have a repair embodied.

Inspection

Technique

Inspection

Requirement

Inspection Threshold Inspection Interval

HFEC Inspect bottom FC FH FC FH

skin for cracks

at the historic

crack initiation

site

DVI Inspect the

local support

structure

10,800 16,200 3,000 4,500

TABLE 2C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspection thresholds at intervals for aircraft which are post

production modification 08488H5253 and do not have a repair embodied.

Inspection

Technique

Inspection

Requirement

Inspection Threshold Inspection Interval

HFEC Inspect bottom FC FH FC FH

skin for cracks

at the historic

crack initiation

site

DVI Inspect the

local support

structure

7,900 17,200 2,200 4,700

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 9

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@A300-600

SERVICE BULLETIN

TABLE 2D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspection thresholds at intervals for aircraft which are post

production modification 08488H5253 and do not have a repair embodied.

Inspection

Technique

Inspection

Requirement

Inspection Threshold Inspection Interval

HFEC Inspect bottom FC FH FC FH

skin for cracks

at the historic

crack initiation

site

DVI Inspect the

local support

structure

8,600 12,900 2,300 3,500

Configuration 003

Post Service Bulletin A300-57-6030 (Modification 08488H5253) and HAVE CONFIRMED

TO AIRBUS that there was no damage to the internal support sub structure.

TABLE 3A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspection thresholds and intervals after embodiment of Service Bulletin A300-57-6030

(Modification 08488H5253) and HAVE CONFIRMED TO AIRBUS that there was no damage to the

internal support structure.

Inspection Inspection Threshold Inspection Interval

Technique

Inspection

Requirement FC FH FC FH

X-ray Inspect bottom

skin for cracks

at the historic

crack initiation

site

X-ray Inspect bottom

skin for cracks

at the

reinforcing plate

end fasteners

DVI Inspect the

local support

structure

5,400 11,600 380 820

Grace period For aircraft that have exceeded the threshold, inspections must be done within 380

FC or 820 FH.

TABLE 3B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspection thresholds and intervals after embodiment of Service Bulletin A300-57-6030

(Modification 08488H5253) and HAVE CONFIRMED TO AIRBUS that there was no damage to the

internal support structure.

Inspection Inspection Threshold Inspection Interval

Technique

Inspection

Requirement FC FH FC FH

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 10

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@A300-600

SERVICE BULLETIN

TABLE 3B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspection thresholds and intervals after embodiment of Service Bulletin A300-57-6030

(Modification 08488H5253) and HAVE CONFIRMED TO AIRBUS that there was no damage to the

internal support structure.

X-ray Inspect bottom

skin for cracks

at the historic

crack initiation

site

X-ray Inspect bottom

skin for cracks

at the

reinforcing plate

end fasteners

DVI Inspect the

local support

structure

5,800 8,700 410 610

Grace period For aircraft that have exceeded the threshold, inspections must be done within 410

FC or 610 FH.

TABLE 3C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspection thresholds and intervals after embodiment of Service

Bulletin A300-57-6030 (Modification 08488H5253) and HAVE CONFIRMED TO AIRBUS that there

was no damage to the internal support structure.

Inspection Inspection Threshold Inspection Interval

Technique

Inspection

Requirement FC FH FC FH

X-ray Inspect bottom

skin for cracks

at the historic

crack initiation

site

X-ray Inspect bottom

skin for cracks

at the

reinforcing plate

end fasteners

DVI Inspect the

local support

structure

4,300 9,200 300 650

Grace period For aircraft that have exceeded the threshold, inspections must be done within 300

FC or 650 FH.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 11

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@A300-600

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TABLE 3D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspection thresholds and intervals after embodiment of Service

Bulletin A300-57-6030 (Modification 08488H5253) and HAVE CONFIRMED TO AIRBUS that there

was no damage to the internal support structure.

Inspection Inspection Threshold Inspection Interval

Technique

Inspection

Requirement FC FH FC FH

X-ray Inspect bottom

skin for cracks

at the historic

crack initiation

site

X-ray Inspect bottom

skin for cracks

at the

reinforcing plate

end fasteners

DVI Inspect the

local support

structure

4,600 6,900 320 480

Grace period For aircraft that have exceeded the threshold, inspections must be done within 320

FC or 480 FH.

Configuration 004

Post Service Bulletin A300-57-6030 (Modification 08488H5253) and HAVE NOT

CONFIRMED TO AIRBUS that there was no damage to the internal support sub

structure.

TABLE 4A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspection thresholds and intervals after embodiment of Service Bulletin A300-57-6030

(Modification 08488H5253) and HAVE NOT CONFIRMED, TO AIRBUS, that there was no damage to

the internal support structure or that the sub structure is broken.

Inspection

Technique

Inspection

Requirement

Inspection Threshold Inspection Interval

X-ray (See FC FH FC FH

Note)

Inspect bottom

skin for cracks

at the historic

crack initiation

site

X-ray Inspect bottom

skin for cracks

at the

reinforcing plate

end fasteners

DVI Inspect the

local support

structure for

cracks

5,200 11,200 380 820

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 12

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@A300-600

SERVICE BULLETIN

TABLE 4A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspection thresholds and intervals after embodiment of Service Bulletin A300-57-6030

(Modification 08488H5253) and HAVE NOT CONFIRMED, TO AIRBUS, that there was no damage to

the internal support structure or that the sub structure is broken.

Grace period For aircraft that have exceeded the threshold, inspections must be done within 380

FC or 820 FH.

TABLE 4B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspection thresholds and intervals after embodiment of Service Bulletin A300-57-6030

(Modification 08488H5253) and HAVE NOT CONFIRMED, TO AIRBUS, that there was no damage to

the internal support structure or that the sub structure is broken.

Inspection

Technique

Inspection

Requirement

Inspection Threshold Inspection Interval

X-ray (See FC FH FC FH

Note)

Inspect bottom

skin for cracks

at the historic

crack initiation

site

X-ray Inspect bottom

skin for cracks

at the

reinforcing plate

end fasteners

DVI Inspect the

local support

structure for

cracks

5,600 8,400 410 610

Grace period For aircraft that have exceeded the threshold, inspections must be done within 410

FC or 610 FH.

TABLE 4C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspection thresholds and intervals after embodiment of Service

Bulletin A300-57-6030 (Modification 08488H5253) and HAVE NOT CONFIRMED, TO AIRBUS, that

there was no damage to the internal support structure or that the sub structure is broken.

Inspection

Technique

Inspection

Requirement

Inspection Threshold Inspection Interval

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 13

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@A300-600

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TABLE 4C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspection thresholds and intervals after embodiment of Service

Bulletin A300-57-6030 (Modification 08488H5253) and HAVE NOT CONFIRMED, TO AIRBUS, that

there was no damage to the internal support structure or that the sub structure is broken.

X-ray (See FC FH FC FH

Note)

Inspect bottom

skin for cracks

at the historic

crack initiation

site

X-ray Inspect bottom

skin for cracks

at the

reinforcing plate

end fasteners

DVI Inspect the

local support

structure for

cracks

4,100 8,900 300 650

Grace period For aircraft that have exceeded the threshold, inspections must be done within 300

FC or 650 FH.

TABLE 4D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspection thresholds and intervals after embodiment of Service

Bulletin A300-57-6030 (Modification 08488H5253) and HAVE NOT CONFIRMED, TO AIRBUS, that

there was no damage to the internal support structure or that the sub structure is broken.

Inspection

Technique

Inspection

Requirement

Inspection Threshold Inspection Interval

X-ray (See FC FH FC FH

Note)

Inspect bottom

skin for cracks

at the historic

crack initiation

site

X-ray Inspect bottom

skin for cracks

at the

reinforcing plate

end fasteners

DVI Inspect the

local support

structure for

cracks

4,400 6,600 320 480

Grace period For aircraft that have exceeded the threshold, inspections must be done within 320

FC or 480 FH.

Configuration 005

Small cracks running forward which have not cleared the support structure. Crack less

than 30.0mm to grow to 30.0mm before stop drilling.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 14

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@A300-600

SERVICE BULLETIN

NOTE: The inspection figures in the tables that follow are taken from crack

detection.

Temporary Repair R57340218.

TABLE 5A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Small cracks running forward which have not cleared the support structure before stop

drilling to Repair R57340218 (See Note).

Crack length measured from aft Inspection Interval

skin edge FC FH

22.0mm 230 490

24.0mm 150 320

26.0mm 100 210

28.0mm 50 100

NOTE: The inspection frequency should increase as the crack length increase.

After a crack has been found at 22 mm the first re-inspection should

be conducted at 230 FC. If the crack length, after this inspection, has

increased to 26 mm then the next repeat inspection should be conducted

at 100 FC not 230 FC.

TABLE 5B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Small cracks running forward which have not cleared the support structure before stop

drilling to Repair R57340218 (See Note).

Crack length measured from aft Inspection Interval

skin edge FC FH

22.0mm 240 370

24.0mm 160 240

26.0mm 100 160

28.0mm 50 80

NOTE: The inspection frequency should increase as the crack length increase.

After a crack has been found at 22 mm the first re-inspection should

be conducted at 240 FC. If the crack length, after this inspection, has

increased to 26 mm then the next repeat inspection should be conducted

at 100 FC not 240 FC.

TABLE 5C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Small cracks running forward which have not cleared the

support structure before stop drilling to Repair R57340218 (See Note).

Crack length measured from aft Inspection Interval

skin edge FC FH

22.0mm 180 380

24.0mm 110 230

26.0mm 70 150

28.0mm 30 60

NOTE: The inspection frequency should increase as the crack length increase.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 15

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@A300-600

SERVICE BULLETIN

After a crack has been found at 22 mm the first re-inspection should

be conducted at 180 FC. If the crack length, after this inspection, has

increased to 26 mm then the next repeat inspection should be conducted

at 70 FC not 180 FC.

TABLE 5D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Small cracks running forward which have not cleared the

support structure before stop drilling to Repair R57340218 (See Note).

Crack length measured from aft Inspection Interval

skin edge FC FH

22.0mm 190 300

24.0mm 120 190

26.0mm 80 120

28.0mm 40 60

NOTE: The inspection frequency should increase as the crack length increase.

After a crack has been found at 22 mm the first re-inspection should

be conducted at 190 FC. If the crack length, after this inspection, has

increased to 26 mm then the next repeat inspection should be conducted

at 80 FC not 190 FC.

Configuration 006

Aircraft with Temporary Repair R57340218

TABLE 6A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspection intervals after embodiment of Temporary Repair R57340218.

Stopped Drilled Cracks Inspection Threshold Inspection Interval

Crack length measured

from aft skin edge

FC FH FC FH

30.0mm 510 1,100 100 210

32.0mm 440 950 90 190

34.0mm 370 810 70 150

36.0mm 310 670 60 120

38.0mm 250 550 50 100

40.0mm 200 430 50 100

TABLE 6B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspection intervals after embodiment of Temporary Repair R57340218.

Stopped Drilled Cracks Inspection Threshold Inspection Interval

Crack length measured

from aft skin edge

FC FH FC FH

30.0mm 550 890 100 160

32.0mm 470 760 90 140

34.0mm 400 640 70 110

36.0mm 330 530 60 90

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 16

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@A300-600

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TABLE 6B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspection intervals after embodiment of Temporary Repair R57340218.

38.0mm 270 430 50 80

40.0mm 210 340 50 80

TABLE 6C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspection intervals after embodiment of Temporary Repair

R57340218.

Stopped Drilled Cracks Inspection Threshold Inspection Interval

Crack length measured

from aft skin edge

FC FH FC FH

30.0mm 410 880 70 150

32.0mm 350 750 70 150

34.0mm 290 620 50 100

36.0mm 240 510 40 80

38.0mm 200 430 30 60

40.0mm 160 340 30 60

TABLE 6D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspection intervals after embodiment of Temporary Repair

R57340218.

Stopped Drilled Cracks Inspection Threshold Inspection Interval

Crack length measured

from aft skin edge

FC FH FC FH

30.0mm 440 710 70 110

32.0mm 370 590 70 110

34.0mm 310 500 50 80

36.0mm 250 400 40 60

38.0mm 210 340 30 40

40.0mm 170 270 30 40

Configuration 007

Post Repair R57340199 (small plate)

TABLE 7A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340199 (small plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 17

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@A300-600

SERVICE BULLETIN

TABLE 7A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340199 (small plate).

Bottom skin

inspection for

skin cracking

beyond crack

stop plug

X-ray

Bottom skin

inspection for

skin cracks at

reinforcing plate

end bolts

X-ray

Inspect support

structure for

cracks

DVI

35,500 76,600 580 1,200

Grace period For aircraft that have exceeded the threshold, inspections must be done within 580

FC or 1,200 FH

TABLE 7B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340199 (small plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Bottom skin

inspection for

skin cracking

beyond crack

stop plug

X-ray

Bottom skin

inspection for

skin cracks at

reinforcing plate

end bolts

X-ray

Inspect support

structure for

cracks

DVI

38,300 57,500 620 930

Grace period For aircraft that have exceeded the threshold, inspections must be done within 620

FC or 930 FH

TABLE 7C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340199 (small

plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 18

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@A300-600

SERVICE BULLETIN

TABLE 7C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340199 (small

plate).

Bottom skin

inspection for

skin cracking

beyond crack

stop plug

X-ray

Bottom skin

inspection for

skin cracks at

reinforcing plate

end bolts

X-ray

Inspect support

structure for

cracks

DVI

28,200 61,000 460 950

Grace period For aircraft that have exceeded the threshold, inspections must be done within 460

FC or 950 FH

TABLE 7D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340199 (small

plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Bottom skin

inspection for

skin cracking

beyond crack

stop plug

X-ray

Bottom skin

inspection for

skin cracks at

reinforcing plate

end bolts

X-ray

Inspect support

structure for

cracks

DVI

30,500 45,800 490 740

Grace period For aircraft that have exceeded the threshold, inspections must be done within 490

FC or 740 FH

Configuration 008

Post Repair R57340199 (large plate)

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 19

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@A300-600

SERVICE BULLETIN

TABLE 8A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340199 (large plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FH FC FH

Inspection for skin

cracking beyond

crack stop plug

not exceeding

76.0mm

X-ray 6,900 14,900 2,000 4,300

Inspection for skin

cracking beyond

crack stop plug

not exceeding

69.0mm

X-ray 14,200 30,600 2,600 5,600

Inspection for skin

cracking beyond

crack stop plug

not exceeding

60.0mm

X-ray 21,100 45,500 3,300 7,100

Inspection for skin

cracking beyond

crack stop plug

not exceeding

50.0mm

X-ray 27,600 59,600 3,600 7,700

Inspection for skin

cracks at repair

plate end bolts

X-ray 40,000 86,400 810 1,700

Inspect support

structure for

cracks

DVI See NOTE below

Grace period For aircraft that have exceeded the threshold, inspections must be done within 810

FC or 1,700 FH.

NOTE: Inspection to be conducted at the same time as the inspection of the skin

at the crack stop plug.

TABLE 8B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340199 (large plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

76.0mm

X-ray 7,400 11,100 2,100 3,200

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 20

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

TABLE 8B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340199 (large plate).

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

69.0mm

X-ray 15,300 23,000 2,800 4,200

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

60.0mm

X-ray 22,700 34,100 3,500 5,300

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

50.0mm

X-ray 29,800 44,700 3,800 5,800

Inspection for

skin cracks at

repair plate end

bolts

X-ray 43,200 64,800 870 1,300

Inspect support

structure for

cracks

DVI See NOTE below

Grace period For aircraft that have exceeded the threshold, inspections must be done within 870

FC or 1,300 FH.

NOTE: Inspection to be conducted at the same time as the inspection of the skin

at the crack stop plug.

TABLE 8C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340199 (large

plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

76.0mm

X-ray 5,400 11,800 1,600 3,400

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 21

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

TABLE 8C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340199 (large

plate).

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

69.0mm

X-ray 11,300 24,300 2,000 4,400

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

60.0mm

X-ray 16,800 36,200 2,600 5,600

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

50.0mm

X-ray 21,900 47,500 2,800 6,100

Inspection for

skin cracks at

repair plate end

bolts

X-ray 31,800 68,800 640 1,300

Inspect support

structure for

cracks

DVI See NOTE below

Grace period For aircraft that have exceeded the threshold, inspections must be done within 640

FC or 1,300 FH.

NOTE: Inspection to be conducted at the same time as the inspection of the skin

at the crack stop plug.

TABLE 8D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340199 (large

plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

76.0mm

X-ray 5,800 8,800 1,700 2,500

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 22

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

TABLE 8D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340199 (large

plate).

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

69.0mm

X-ray 12,100 18,300 2,200 3,300

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

60.0mm

X-ray 18,000 27,100 2,700 4,200

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

50.0mm

X-ray 23,700 35,600 3,000 4,600

Inspection for

skin cracks at

repair plate end

bolts

X-ray 34,400 51,600 690 1,000

Inspect support

structure for

cracks

DVI See NOTE below

Grace period For aircraft that have exceeded the threshold, inspections must be done within 690

FC or 1,000 FH.

NOTE: Inspection to be conducted at the same time as the inspection of the skin

at the crack stop plug.

Configuration 009

Post Repair R57340390

NOTE: This repair must be removed and replaced by repair R57340223 at the

earliest opportunity.

TABLE 9A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspections after embodiment of repair R57140390

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 23

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

TABLE 9A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspections after embodiment of repair R57140390

Bottom skin

inspection for

skin cracking

beyond crack

stop hole

X-Ray

Bottom skin

inspection for

skin cracks at

reinforcing plate

end bolts

X-Ray

Inspect support

structure for

cracks

DVI

4,600 9,900 870 1,800

Grace period For aircraft that have exceeded the threshold, the repair instruction R57340223 must

be installed within 870 FC or 1,800 FH

TABLE 9B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspections after embodiment of repair R57140390

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Bottom skin

inspection for

skin cracking

beyond crack

stop hole

X-Ray

Bottom skin

inspection for

skin cracks at

reinforcing plate

end bolts

X-Ray

Inspect support

structure for

cracks

DVI

4,900 7,400 960 1,400

Grace period For aircraft that have exceeded the threshold, the repair instruction R57340223 must

be installed within 960 FC or 1,400 FH

TABLE 9C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of repair R57140390

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 24

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

TABLE 9C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of repair R57140390

Bottom skin

inspection for

skin cracking

beyond crack

stop hole

X-Ray

Bottom skin

inspection for

skin cracks at

reinforcing plate

end bolts

X-Ray

Inspect support

structure for

cracks

DVI

3,600 7,900 690 1,400

Grace period For aircraft that have exceeded the threshold, the repair instruction R57340223 must

be installed within 690 FC or 1,400 FH

TABLE 9D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of repair R57140390

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Bottom skin

inspection for

skin cracking

beyond crack

stop hole

X-Ray

Bottom skin

inspection for

skin cracks at

reinforcing plate

end bolts

X-Ray

Inspect support

structure for

cracks

DVI

3,900 5,800 760 1,100

Grace period For aircraft that have exceeded the threshold, the repair instruction R57340223 must

be installed within 760 FC or 1,100 FH

Configuration 010

Post Repair R57340148

TABLE 10A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340148.

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 25

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

TABLE 10A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340148.

Inspection for skin

cracking beyond

crack stop plug

not exceeding

85.0mm

X-ray 2,400 5,100 450 970

Inspection for skin

cracking beyond

crack stop plug

not exceeding

80.0mm

X-ray 2,400 5,100 1,000 2,200

Inspection for skin

cracking beyond

crack stop plug

not exceeding

70.0mm

X-ray 2,400 5,100 2,100 4,600

Inspection for skin

cracking beyond

crack stop plug

not exceeding

60.0mm

X-ray 4,500 9,700 2,700 5,800

Inspection for skin

cracking beyond

crack stop plug

not exceeding

50.0mm

X-ray 8,900 19,200 2,800 6,100

Inspection for skin

cracking beyond

crack stop plug

not exceeding

40.0mm

X-ray 10,200 22,000 2,900 6,300

Inspection for skin

cracking beyond

crack stop plug

not exceeding

30.0mm

X-ray 13,300 28,700 3,000 6,400

Inspection for skin

cracking beyond

crack stop plug

not exceeding

24.0mm

X-ray 17,000 36,700 3,000 6,500

Inspection for skin

cracking beyond

crack stop plug

not exceeding

20.0mm

X-ray 21,000 45,300 3,000 6,600

Inspection for skin

cracks at repair

plate end bolts

X-ray 7,500 16,200 690 1,400

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 26

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

TABLE 10A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340148.

Inspect support

structure for

cracks

DVI See NOTE below

Grace period For aircraft that have exceeded the threshold, inspections must be done within 450

FC or 970 FH.

NOTE: Inspection to be conducted at the same time as the inspection of the skin

at the crack stop plug.

TABLE 10B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340148.

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

85.0mm

X-ray 2,500 3,800 480 720

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

80.0mm

X-ray 2,500 3,800 1,100 1,700

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

70.0mm

X-ray 2,500 3,800 2,300 3,500

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

60.0mm

X-ray 4,800 7,200 2,900 4,400

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

50.0mm

X-ray 9,600 14,400 3,000 4,600

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 27

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

TABLE 10B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340148.

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

40.0mm

X-ray 11,000 16,500 3,100 4,700

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

30.0mm

X-ray 14,300 21,500 3,200 4,800

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

24.0mm

X-ray 18,300 27,500 3,200 4,900

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

20.0mm

X-ray 22,600 34,000 3,300 5,000

Inspection for

skin cracks at

repair plate end

bolts

X-ray 8,100 12,100 700 1,100

Inspect support

structure for

cracks

DVI See NOTE below

Grace period For aircraft that have exceeded the threshold, inspections must be done within 480

FC or 720 FH.

NOTE: Inspection to be conducted at the same time as the inspection of the skin

at the crack stop plug.

TABLE 10C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340148.

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

85.0mm

X-ray 1,900 4,000 350 770

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 28

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

TABLE 10C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340148.

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

80.0mm

X-ray 1,900 4,000 830 1,700

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

70.0mm

X-ray 1,900 4,000 1,700 3,600

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

60.0mm

X-ray 3,500 7,700 2,100 4,600

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

50.0mm

X-ray 7,000 15,300 2,200 4,800

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

40.0mm

X-ray 8,100 17,500 2,300 5,000

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

30.0mm

X-ray 10,600 22,800 2,300 5,100

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

24.0mm

X-ray 13,500 29,200 2,400 5,100

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

20.0mm

X-ray 16,700 36,100 2,400 5,200

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 29

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

TABLE 10C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340148.

Inspection for

skin cracks at

repair plate end

bolts

X-ray 5,900 12,900 500 1,100

Inspect support

structure for

cracks

DVI See NOTE below

Grace period For aircraft that have exceeded the threshold, inspections must be done within 350

FC or 770 FH.

NOTE: Inspection to be conducted at the same time as the inspection of the skin

at the crack stop plug.

TABLE 10D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340148.

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

85.0mm

X-ray 2,000 3,000 380 570

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

80.0mm

X-ray 2,000 3,000 870 1,300

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

70.0mm

X-ray 2,000 3,000 1,800 2,700

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

60.0mm

X-ray 3,800 5,800 2,300 3,500

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

50.0mm

X-ray 7,600 11,400 2,300 3,600

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 30

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

TABLE 10D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340148.

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

40.0mm

X-ray 8,700 13,100 2,400 3,700

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

30.0mm

X-ray 11,400 17,100 2,500 3,800

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

24.0mm

X-ray 14,600 21,900 2,500 3,900

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

20.0mm

X-ray 18,000 27,100 2,600 3,900

Inspection for

skin cracks at

repair plate end

bolts

X-ray 6,400 9,600 500 800

Inspect support

structure for

cracks

DVI See NOTE below

Grace period For aircraft that have exceeded the threshold, inspections must be done within 380

FC or 570 FH.

NOTE: Inspection to be conducted at the same time as the inspection of the skin

at the crack stop plug.

Configuration 011

Post Repair R57340223 (small plate)

TABLE 11A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340223 (small plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 31

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

Inspection for

skin cracking

beyond crack

stop plug

X-ray

Inspection for

skin cracks at

reinforcing plate

end bolts

X-ray

Inspect support

structure for

cracks

DVI

35,500 76,600 580 1,200

Grace period For aircraft that have exceeded the threshold, inspections must be done within 580

FC or 1,200 FH.

TABLE 11B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340223 (small plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking

beyond crack

stop plug

X-ray

Inspection for

skin cracks at

reinforcing plate

end bolts

X-ray

Inspect support

structure for

cracks

DVI

38,300 57,500 620 930

Grace period For aircraft that have exceeded the threshold, inspections must be done within 620

FC or 930 FH.

TABLE 11C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340223 (small

plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 32

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

Inspection for

skin cracking

beyond crack

stop plug

X-ray

Inspection for

skin cracks at

reinforcing plate

end bolts

X-ray

Inspect support

structure for

cracks

DVI

28,200 61,000 460 900

Grace period For aircraft that have exceeded the threshold, inspections must be done within 460

FC or 900 FH.

TABLE 11D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340223 (small

plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking

beyond crack

stop plug

X-ray

Inspection for

skin cracks at

reinforcing plate

end bolts

X-ray

Inspect support

structure for

cracks

DVI

30,500 45,800 490 740

Grace period For aircraft that have exceeded the threshold, inspections must be done within 490

FC or 740 FH.

Configuration 012

Post Repair R57340223 (large plate)

TABLE 12A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340223 (large plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

91.0mm

X-ray 3,000 6,400 900 1,900

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 33

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

TABLE 12A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340223 (large plate).

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

80.0mm

X-ray 11,900 25,700 2,100 4,500

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

70.0mm

X-ray 32,800 70,800 2,900 6,200

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

60.0mm

X-ray 45,700 98,700 3,500 7,500

Inspection for

skin cracks at

repair plate end

bolts

X-ray 36,800 79,400 870 1,800

Inspect support

structure for

cracks

DVI See NOTE below

Grace period For aircraft that have exceeded the threshold, inspections must be done within 870

FC or 1,800 FH.

NOTE: Inspection to be conducted at the same time as the inspection of the skin

at the crack stop plug.

TABLE 12B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340223 (large plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

91.0mm

X-ray 3,200 4,800 970 1,400

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

80.0mm

X-ray 12,800 19,200 2,200 3,400

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 34

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@A300-600

SERVICE BULLETIN

TABLE 12B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspections after embodiment of Repair R57340223 (large plate).

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

70.0mm

X-ray 35,400 53,100 3,100 4,600

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

60.0mm

X-ray 49,300 74,000 3,700 5,600

Inspection for

skin cracks at

repair plate end

bolts

X-ray 39,700 59,600 930 1,400

Inspect support

structure for

cracks

DVI See NOTE below

Grace period For aircraft that have exceeded the threshold, inspections must be done within 930

FC or 1,400 FH.

NOTE: Inspection to be conducted at the same time as the inspection of the skin

at the crack stop plug.

TABLE 12C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340223 (large

plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

91.0mm

X-ray 2,300 5,100 710 1,500

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

80.0mm

X-ray 9,400 20,400 1,600 3,500

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 35

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@A300-600

SERVICE BULLETIN

TABLE 12C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340223 (large

plate).

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

70.0mm

X-ray 26,100 56,400 2,300 4,900

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

60.0mm

X-ray 36,400 78,600 2,700 5,900

Inspection for

skin cracks at

repair plate end

bolts

X-ray 29,300 63,200 690 1,400

Inspect support

structure for

cracks

DVI See NOTE below

Grace period For aircraft that have exceeded the threshold, inspections must be done within 690

FC or 1,400 FH.

NOTE: Inspection to be conducted at the same time as the inspection of the skin

at the crack stop plug.

TABLE 12D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340223 (large

plate).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

91.0mm

X-ray 2,500 3,800 770 1,100

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

80.0mm

X-ray 10,200 15,300 1,700 2,700

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 36

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@A300-600

SERVICE BULLETIN

TABLE 12D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections after embodiment of Repair R57340223 (large

plate).

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

70.0mm

X-ray 28,200 42,300 2,400 3,600

Inspection for

skin cracking

beyond crack

stop plug not

exceeding

60.0mm

X-ray 39,200 58,900 2,900 4,400

Inspection for

skin cracks at

repair plate end

bolts

X-ray 31,600 47,500 740 1,100

Inspect support

structure for

cracks

DVI See NOTE below

Grace period For aircraft that have exceeded the threshold, inspections must be done within 740

FC or 1,100 FH.

NOTE: Inspection to be conducted at the same time as the inspection of the skin

at the crack stop plug.

Configuration 013

Inspection programme for Post Retro-fit Modification 11178H5410 (Service Bulletin

A300-57-6064)

TABLE 13A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspections for aircraft which are post retro-fit modification 11178H5410 (Service

Bulletin A300-57-6064).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking at

historic crack

location

X-ray 41,400 89,400 580 1,200

Inspection for

skin cracks at

repair end bolt

X-ray 41,400 89,400 580 1,200

Inspect support

structure for

cracks

DVI 41,400 89,400 580 1,200

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 37

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@A300-600

SERVICE BULLETIN

TABLE 13A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspections for aircraft which are post retro-fit modification 11178H5410 (Service

Bulletin A300-57-6064).

Grace period For aircraft that have exceeded the threshold, inspections must be done within 580

FC or 1,200 FH.

TABLE 13B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspections for aircraft which are post retro-fit modification 11178H5410 (Service

Bulletin A300-57-6064).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking at

historic crack

location

X-ray

Inspection for

skin cracks at

repair end bolt

X-ray

Inspect support

structure for

cracks

DVI

44,700 67,000 620 930

Grace period For aircraft that have exceeded the threshold, inspections must be done within 620

FC or 930 FH.

TABLE 13C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections for aircraft which are post retro-fit modification

11178H5410 (Service Bulletin A300-57-6064).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking at

historic crack

location

X-ray

Inspection for

skin cracks at

repair end bolt

X-ray

Inspect support

structure for

cracks

DVI

32,900 71,200 460 950

Grace period For aircraft that have exceeded the threshold, inspections must be done within 460

FC or 950 FH.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 38

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@A300-600

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TABLE 13D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections for aircraft which are post retro-fit modification

11178H5410 (Service Bulletin A300-57-6064).

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracking at

historic crack

location

X-ray

Inspection for

skin cracks at

repair end bolt

X-ray

Inspect support

structure for

cracks

DVI

35,500 53,200 490 740

Grace period For aircraft that have exceeded the threshold, inspections must be done within 490

FC or 740 FH.

Configuration 014

Inspection programme for Post Production Modification 11178H5410

TABLE 14A - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300F4-600R - Inspections for aircraft which are post production modification 11178H5410

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracks at

repair end bolt

X-ray

Inspect support

structure for

cracks

DVI

42,200 91,100 580 1,200

Grace period For aircraft that have exceeded the threshold, inspections must be done within 580

FC or 1,200 FH.

TABLE 14B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspections for aircraft which are post production modification 11178H5410

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracks at

repair end bolt

X-ray

Inspect support

structure for

cracks

DVI

45,500 68,300 620 930

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 39

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@A300-600

SERVICE BULLETIN

TABLE 14B - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300F4-600R - Inspections for aircraft which are post production modification 11178H5410

Grace period For aircraft that have exceeded the threshold, inspections must be done within 620

FC or 930 FH.

TABLE 14C - NORMAL RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME EQUAL

OR > 1.5 FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections for aircraft which are post production modification

11178H5410

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracks at

repair end bolt

X-ray

Inspect support

structure for

cracks

DVI

33,600 72,600 460 950

Grace period For aircraft that have exceeded the threshold, inspections must be done within 460

FC or 950 FH.

TABLE 14D - SHORT RANGE - FOR A/C OPERATION WITH AN AVERAGE FLIGHT TIME < 1.5

FLIGHT HOURS

A300B4-600(R) and A300C4-600(R) - Inspections for aircraft which are post production modification

11178H5410

Inspection Inspection Threshold Inspection Interval

Requirement

Inspection

Technique FC FH FC FH

Inspection for

skin cracks at

repair end bolt

X-ray

Inspect support

structure for

cracks

DVI

36,200 54,400 490 740

Grace period For aircraft that have exceeded the threshold, inspections must be done within 490

FC or 740 FH.

F. APPROVAL

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

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 40

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@A300-600

SERVICE BULLETIN

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

Task 576029-832-895-001: INSPECTION

Get Access 0.50

On Aircraft

INSPECTION CONFIGURATION 001 1.50

INSPECTION CONFIGURATION 002 1.50

INSPECTION CONFIGURATION 003 2.00

INSPECTION CONFIGURATION 004 2.00

INSPECTION CONFIGURATION 005 1.50

INSPECTION CONFIGURATION 006 1.50

INSPECTION CONFIGURATION 007 2.00

INSPECTION CONFIGURATION 008 2.00

INSPECTION CONFIGURATION 009 2.00

INSPECTION CONFIGURATION 010 2.00

INSPECTION CONFIGURATION 011 2.00

INSPECTION CONFIGURATION 012 2.00

INSPECTION CONFIGURATION 013 2.00

INSPECTION CONFIGURATION 014 1.00

Close-Up 0.50

TOTAL MANHOURS 26.00

ELAPSED TIME (HOURS) 1.50

NOTE: Total Manhours is for all Configurations - Manhours for individual

configurations are less as stated above.

Task 576029-833-896-001: REPAIR

On Aircraft

REPAIR - CONFIGURATION 001 0

REPAIR - CONFIGURATION 002 0

REPAIR - CONFIGURATION 003 0

REPAIR - CONFIGURATION 004 0

REPAIR - CONFIGURATION 005 0

REPAIR - CONFIGURATION 006 0

REPAIR - CONFIGURATION 007 0

REPAIR - CONFIGURATION 008 0

REPAIR - CONFIGURATION 009 0

REPAIR - CONFIGURATION 010 0

REPAIR - CONFIGURATION 011 0

REPAIR - CONFIGURATION 012 0

REPAIR - CONFIGURATION 013 0

REPAIR - CONFIGURATION 014 0

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 41

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@A300-600

SERVICE BULLETIN

Task 576029-833-896-001: REPAIR

TOTAL MANHOURS 0.00

ELAPSED TIME (HOURS) 0.00

NOTE: Manhours for Repairs are not included in this Service Bulletin.

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01 51-10-08 57-20-12

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 42

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@A300-600

SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

None

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 43

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This Page Intentionally Left Blank

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 44

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 576029-832-895-001 - INSPECTION

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER

CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

NOTE: These instructions are applicable to the left and right hand wings.

Task Associated Data

Manpower

TOTAL MANHOURS 26.00

ELAPSED TIME (HOURS) 1.50

A. GENERAL

(1) Subtask 576029-900-402-001 - DOCUMENTATION

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

B. PREPARATION

(1) Subtask 576029-832-403-002 - PREPARATION

Manpower Resources

Skills AIRFRAME

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 45

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@A300-600

SERVICE BULLETIN

References

Fig. A-UBAAA Sheet 01 - Area to be Inspected

(Configurations 001 thru 014)

Sheet 02 - Areas to be Inspected Before

Repair (Configurations 001, 005 and 006)

Sheet 03 - Area to be Inspected After

Repair R57340199 and R57340223, Large

Plate Option (Configurations 008 and 012)

Sheet 04 - Area to be Inspected for Repair

R57340148 (Configuration 010)

Sheet 05 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

Sheet 06 - Area to be Inspected Post

Production Modification 08488H5253

(Configuration 002)

Sheet 07 - Area to be Inspected for Repair

R57140390 (Configuration 009)

Sheet 08 - Area to be Inspected After

Production Modification 11178H5410

(Configuration 014)

Sheet 09 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

Sheet 10 - Area to be Inspected After

Repair R57340199 and R57340223, Small

Plate Option (Configurations 007 and 011)

Sheet 11 - View from Underside of Wing

Showing Typical Crack (Configurations 001,

005 and 006)

Refer to Figure Fig. A-UBAAA Sheet 01.

(a) Get access to the wing bottom skin immediately inboard of rib 9 and aft of the rear

spar.

(b) Open access panels 575FB / 675FB.

(c) Locate the fasteners and the associated internal support structure to be inspected.

C. PROCEDURE

(1) Subtask 576029-832-404-002 - INSPECTION CONFIGURATION 001

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills AIRFRAME

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 46

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@A300-600

SERVICE BULLETIN

References

Non Destructive Test Manual (NTM) 51-10-08 Part 6

Fig. A-UBAAA Sheet 01 - Area to be Inspected

(Configurations 001 thru 014)

Sheet 02 - Areas to be Inspected Before

Repair (Configurations 001, 005 and 006)

Sheet 03 - Area to be Inspected After

Repair R57340199 and R57340223, Large

Plate Option (Configurations 008 and 012)

Sheet 04 - Area to be Inspected for Repair

R57340148 (Configuration 010)

Sheet 05 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

Sheet 06 - Area to be Inspected Post

Production Modification 08488H5253

(Configuration 002)

Sheet 07 - Area to be Inspected for Repair

R57140390 (Configuration 009)

Sheet 08 - Area to be Inspected After

Production Modification 11178H5410

(Configuration 014)

Sheet 09 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

Sheet 10 - Area to be Inspected After

Repair R57340199 and R57340223, Small

Plate Option (Configurations 007 and 011)

Sheet 11 - View from Underside of Wing

Showing Typical Crack (Configurations 001,

005 and 006)

NOTE: The steps that follow are for the LH and RH wings.

Configuration 001 - For pre Service Bulletin A300-57-6030 (modification 08488H5253)

aircraft that have not been repaired previously, do the steps that follow:

Refer to Figure Fig. A-UBAAA Sheet 02 and Fig. A-UBAAA Sheet 11.

(a) Do an HFEC inspection of the bottom skin panel around the fasteners indicated

(Refer to NTM 51-10-08 Part 6).

(b) Do a DVI of the skin support flange, particularly at the joggled section and

immediately outboard of the stiffener and stiffener flange at the skin fastener holes

forward of the false rear spar.

(c) If no cracks are found it is recommended to embody Service Bulletin A300-57-6064

(modification 11178H5410).

(d) If Service Bulletin A300-57-6064 is not embodied, repeat the inspections.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 47

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SERVICE BULLETIN

(e) If cracks are found, repair in accordance with TASK 576029-833-896 001 REPAIR ,

before the next flight.

(2) Subtask 576029-250-401-001 - INSPECTION CONFIGURATION 002

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-08 Part 6

Fig. A-UBAAA Sheet 01 - Area to be Inspected

(Configurations 001 thru 014)

Sheet 02 - Areas to be Inspected Before

Repair (Configurations 001, 005 and 006)

Sheet 03 - Area to be Inspected After

Repair R57340199 and R57340223, Large

Plate Option (Configurations 008 and 012)

Sheet 04 - Area to be Inspected for Repair

R57340148 (Configuration 010)

Sheet 05 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

Sheet 06 - Area to be Inspected Post

Production Modification 08488H5253

(Configuration 002)

Sheet 07 - Area to be Inspected for Repair

R57140390 (Configuration 009)

Sheet 08 - Area to be Inspected After

Production Modification 11178H5410

(Configuration 014)

Sheet 09 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

Sheet 10 - Area to be Inspected After

Repair R57340199 and R57340223, Small

Plate Option (Configurations 007 and 011)

Sheet 11 - View from Underside of Wing

Showing Typical Crack (Configurations 001,

005 and 006)

NOTE: The steps that follow are for the LH and RH wings.

Configuration 002 - For post production modification 08488H5253 aircraft, do the steps

which follow:

Refer to Figure Fig. A-UBAAA Sheet 06.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 48

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SERVICE BULLETIN

(a) Do a HFEC inspection of the bottom skin panel at the historic crack initiation site

(Refer to NTM 51-10-08 Part 6).

(b) Do a DVI of the local support structure for cracks.

(c) If no cracks are found, it is recommended to embody Service Bulletin

A300-57-6064 (modification 11178H5410).

(d) If Service Bulletin A300-57-6064 is not embodied, repeat the inspections.

(e) If cracks are found, repair in accordance with TASK 576029-833-896 001 REPAIR ,

before the next flight.

(3) Subtask 576029-260-401-001 - INSPECTION CONFIGURATION 003

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 57-20-12 Part 2

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 49

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SERVICE BULLETIN

References

Fig. A-UBAAA Sheet 01 - Area to be Inspected

(Configurations 001 thru 014)

Sheet 02 - Areas to be Inspected Before

Repair (Configurations 001, 005 and 006)

Sheet 03 - Area to be Inspected After

Repair R57340199 and R57340223, Large

Plate Option (Configurations 008 and 012)

Sheet 04 - Area to be Inspected for Repair

R57340148 (Configuration 010)

Sheet 05 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

Sheet 06 - Area to be Inspected Post

Production Modification 08488H5253

(Configuration 002)

Sheet 07 - Area to be Inspected for Repair

R57140390 (Configuration 009)

Sheet 08 - Area to be Inspected After

Production Modification 11178H5410

(Configuration 014)

Sheet 09 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

Sheet 10 - Area to be Inspected After

Repair R57340199 and R57340223, Small

Plate Option (Configurations 007 and 011)

Sheet 11 - View from Underside of Wing

Showing Typical Crack (Configurations 001,

005 and 006)

NOTE: The steps that follow are for the LH and RH wings.

Configuration 003 - For post-Service Bulletin A300-57-6030 (modification 08488H5253)

aircraft and it was confirmed that there was no damage to the internal support structure,

do the steps that follow:

Refer to Figure Fig. A-UBAAA Sheet 09.

(a) Carry out an X-ray inspection of the bottom skin panel at the historic crack initiation

site (Refer to ).

(b) Carry out an X-ray inspection at the reinforcing plate end bolts indicated. Inspect for

skin cracks at the reinforcing plate end bolts. (Refer to NTM 57-20-12 Part 2).

(c) Do a DVI of the local support structure for cracks.

(d) If no cracks are found, it is recommended to remove Service Bulletin A300-57-6030

(modification 08488H5253) and embody Service Bulletin A300-57-6064

(modification 11178H5410).

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 50

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

(e) If Service Bulletin A300-57-6064 is not embodied, repeat the inspections.

(f) If cracks are found, repair in accordance with TASK 576029-833-896 001 REPAIR ,

before the next flight.

(4) Subtask 576029-832-405-001 - INSPECTION CONFIGURATION 004

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 57-20-12 Part 2

Fig. A-UBAAA Sheet 01 - Area to be Inspected

(Configurations 001 thru 014)

Sheet 02 - Areas to be Inspected Before

Repair (Configurations 001, 005 and 006)

Sheet 03 - Area to be Inspected After

Repair R57340199 and R57340223, Large

Plate Option (Configurations 008 and 012)

Sheet 04 - Area to be Inspected for Repair

R57340148 (Configuration 010)

Sheet 05 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

Sheet 06 - Area to be Inspected Post

Production Modification 08488H5253

(Configuration 002)

Sheet 07 - Area to be Inspected for Repair

R57140390 (Configuration 009)

Sheet 08 - Area to be Inspected After

Production Modification 11178H5410

(Configuration 014)

Sheet 09 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

Sheet 10 - Area to be Inspected After

Repair R57340199 and R57340223, Small

Plate Option (Configurations 007 and 011)

Sheet 11 - View from Underside of Wing

Showing Typical Crack (Configurations 001,

005 and 006)

NOTE: The steps that follow are for the LH and RH wings.

Configuration 004 - For post-Service Bulletin A300-57-6030 (modification 08488H5253)

aircraft and it was not confirmed that there was no damage to the internal support

structure, do the steps that follow:

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 51

7

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@A300-600

SERVICE BULLETIN

Refer to Figure Fig. A-UBAAA Sheet 09.

(a) Carry out an X-ray inspection of the bottom skin panel at the historic crack initiation

site (Refer to NTM 57-20-12 Part 2).

(b) Carry out an X-ray inspection at the reinforcing plate end bolts indicated. Inspect for

skin cracks at the reinforcing plate end bolts (Refer to NTM 57-20-12 Part 2).

(c) Do a DVI of the local support structure for cracks.

(d) If no cracks are found, remove Service Bulletin A300-57-6030 (modification

08488H5253) and embody Service Bulletin A300-57-6064 (modification

11178H5410).

(e) If cracks are found, repair in accordance with TASK 576029-833-896 001 REPAIR ,

before the next flight.

(5) Subtask 576029-832-406-001 - INSPECTION CONFIGURATION 005

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills AIRFRAME

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 52

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

References

Fig. A-UBAAA Sheet 01 - Area to be Inspected

(Configurations 001 thru 014)

Sheet 02 - Areas to be Inspected Before

Repair (Configurations 001, 005 and 006)

Sheet 03 - Area to be Inspected After

Repair R57340199 and R57340223, Large

Plate Option (Configurations 008 and 012)

Sheet 04 - Area to be Inspected for Repair

R57340148 (Configuration 010)

Sheet 05 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

Sheet 06 - Area to be Inspected Post

Production Modification 08488H5253

(Configuration 002)

Sheet 07 - Area to be Inspected for Repair

R57140390 (Configuration 009)

Sheet 08 - Area to be Inspected After

Production Modification 11178H5410

(Configuration 014)

Sheet 09 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

Sheet 10 - Area to be Inspected After

Repair R57340199 and R57340223, Small

Plate Option (Configurations 007 and 011)

Sheet 11 - View from Underside of Wing

Showing Typical Crack (Configurations 001,

005 and 006)

NOTE: The steps that follow are for the LH and RH wings.

Configuration 005 - Aircraft on which there are cracks in the bottom skin running forward

which have not cleared the edge of the internal support structure, do the steps that

follow:

Refer to Figure Fig. A-UBAAA Sheet 02 and Fig. A-UBAAA Sheet 11.

(a) Do a DVI of the bottom skin panel around the fasteners to check for additional

cracks. A crack cannot be stop drilled if it is below 30.0mm (1.18in). Crack lengths

are measured from the aft edge of the skin line.

(b) Repeat inspections must be carried out to monitor the crack until it becomes

sufficiently long to clear the support structure. If the crack is clear of the support

structure or if an additional crack is detected Do a repair in accordance with TASK

576029-833-896 001 REPAIR , before the next flight.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 53

7

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@A300-600

SERVICE BULLETIN

(6) Subtask 576029-832-407-001 - INSPECTION CONFIGURATION 006

Manpower Resources

Manhours 1.50

Minimum number of person 1

Subtask elapsed time 1.50

Skills AIRFRAME

References

Fig. A-UBAAA Sheet 01 - Area to be Inspected

(Configurations 001 thru 014)

Sheet 02 - Areas to be Inspected Before

Repair (Configurations 001, 005 and 006)

Sheet 03 - Area to be Inspected After

Repair R57340199 and R57340223, Large

Plate Option (Configurations 008 and 012)

Sheet 04 - Area to be Inspected for Repair

R57340148 (Configuration 010)

Sheet 05 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

Sheet 06 - Area to be Inspected Post

Production Modification 08488H5253

(Configuration 002)

Sheet 07 - Area to be Inspected for Repair

R57140390 (Configuration 009)

Sheet 08 - Area to be Inspected After

Production Modification 11178H5410

(Configuration 014)

Sheet 09 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

Sheet 10 - Area to be Inspected After

Repair R57340199 and R57340223, Small

Plate Option (Configurations 007 and 011)

Sheet 11 - View from Underside of Wing

Showing Typical Crack (Configurations 001,

005 and 006)

NOTE: The steps that follow are for the LH and RH wings.

Configuration 006 - For aircraft on which temporary repair R57340218 has been

incorporated, do the the steps that follow until a permanent repair in accordance with

Repair Instruction R57340199 is accomplished:

Refer to Figure Fig. A-UBAAA Sheet 02 and Fig. A-UBAAA Sheet 11.

(a) Do a DVI at the crack stop hole location.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 54

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

(b) Do a DVI of the skin support flange, particularly at the joggled section and

immediately outboard of the stiffener and the stiffener flange at the skin fastener

holes forward of the false rear spar for cracks.

(c) If additional cracks are found or if the existing crack length has increased, repair in

accordance with TASK 576029-833-896 001 REPAIR , before the next flight.

(d) If there are no new cracks or new crack propagation do repeat inspections.

(7) Subtask 576029-832-408-001 - INSPECTION CONFIGURATION 007

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 57-20-12 Part 2

Fig. A-UBAAA Sheet 01 - Area to be Inspected

(Configurations 001 thru 014)

Sheet 02 - Areas to be Inspected Before

Repair (Configurations 001, 005 and 006)

Sheet 03 - Area to be Inspected After

Repair R57340199 and R57340223, Large

Plate Option (Configurations 008 and 012)

Sheet 04 - Area to be Inspected for Repair

R57340148 (Configuration 010)

Sheet 05 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

Sheet 06 - Area to be Inspected Post

Production Modification 08488H5253

(Configuration 002)

Sheet 07 - Area to be Inspected for Repair

R57140390 (Configuration 009)

Sheet 08 - Area to be Inspected After

Production Modification 11178H5410

(Configuration 014)

Sheet 09 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

Sheet 10 - Area to be Inspected After

Repair R57340199 and R57340223, Small

Plate Option (Configurations 007 and 011)

Sheet 11 - View from Underside of Wing

Showing Typical Crack (Configurations 001,

005 and 006)

NOTE: The steps that follow are for the LH and RH wings.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 55

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

Configuration 007 - For aircraft on which a permanent repair has been incorporated in

accordance with Repair Instruction R57340199 (small plate repair), do the steps that

follow:

Refer to Figure Fig. A-UBAAA Sheet 10.

(a) Do an X-ray inspection of the bottom skin at all the crack stop plug locations.

Inspect for skin cracking beyond the crack stop plug (Refer to NTM 57-20-12 Part

2).

(b) Do an X-ray inspection at the repair plate end bolts indicated (Refer to NTM

57-20-12 Part 2).

(c) Do a DVI of the skin support flange immediately outboard of the stiffener and the

stiffener flange at the skin fastener holes forward of the false rear spar for cracks.

(d) If there are no new cracks or new crack propagation do repeat inspections.

(e) If additional cracks are found or if the existing crack length has increased, contact

AIRBUS before the next flight.

(8) Subtask 576029-832-409-001 - INSPECTION CONFIGURATION 008

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 57-20-12 Part 2

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 56

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

References

Fig. A-UBAAA Sheet 01 - Area to be Inspected

(Configurations 001 thru 014)

Sheet 02 - Areas to be Inspected Before

Repair (Configurations 001, 005 and 006)

Sheet 03 - Area to be Inspected After

Repair R57340199 and R57340223, Large

Plate Option (Configurations 008 and 012)

Sheet 04 - Area to be Inspected for Repair

R57340148 (Configuration 010)

Sheet 05 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

Sheet 06 - Area to be Inspected Post

Production Modification 08488H5253

(Configuration 002)

Sheet 07 - Area to be Inspected for Repair

R57140390 (Configuration 009)

Sheet 08 - Area to be Inspected After

Production Modification 11178H5410

(Configuration 014)

Sheet 09 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

Sheet 10 - Area to be Inspected After

Repair R57340199 and R57340223, Small

Plate Option (Configurations 007 and 011)

Sheet 11 - View from Underside of Wing

Showing Typical Crack (Configurations 001,

005 and 006)

NOTE: The steps that follow are for the LH and RH wings.

Configuration 008 - For aircraft on which a permanent repair has been incorporated in

accordance with Repair Instruction R57340199 (large plate repair), do the the steps that

follow:

Refer to Figure Fig. A-UBAAA Sheet 03.

(a) Do an X-ray inspection of the bottom skin at all the crack stop plug locations.

Inspect for skin cracking beyond the crack stop plug (Refer to NTM 57-20-12 Part

2).

(b) Do an X-ray inspection at the reinforcing plate end bolts indicated (Refer to NTM

57-20-12 Part 2).

(c) Do a DVI of the skin support flange immediately outboard of the stiffener and the

stiffener flange at the skin fastener holes forward of the false rear spar for cracks.

(d) If there are no new cracks or new crack propagation do repeat inspections.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 57

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

(e) If additional cracks are found or if the existing crack length has increased, contact

AIRBUS before the next flight.

(9) Subtask 576029-832-410-001 - INSPECTION CONFIGURATION 009

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6, Procedure A

Fig. A-UBAAA Sheet 01 - Area to be Inspected

(Configurations 001 thru 014)

Sheet 02 - Areas to be Inspected Before

Repair (Configurations 001, 005 and 006)

Sheet 03 - Area to be Inspected After

Repair R57340199 and R57340223, Large

Plate Option (Configurations 008 and 012)

Sheet 04 - Area to be Inspected for Repair

R57340148 (Configuration 010)

Sheet 05 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

Sheet 06 - Area to be Inspected Post

Production Modification 08488H5253

(Configuration 002)

Sheet 07 - Area to be Inspected for Repair

R57140390 (Configuration 009)

Sheet 08 - Area to be Inspected After

Production Modification 11178H5410

(Configuration 014)

Sheet 09 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

Sheet 10 - Area to be Inspected After

Repair R57340199 and R57340223, Small

Plate Option (Configurations 007 and 011)

Sheet 11 - View from Underside of Wing

Showing Typical Crack (Configurations 001,

005 and 006)

NOTE: The steps that follow are for the LH and RH wings.

Configuration 009 - For aircraft on which repair R57140390 has been incorporated, do

the steps that follow:

Refer to Figure Fig. A-UBAAA Sheet 07.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 58

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@A300-600

SERVICE BULLETIN

(a) Remove the repair R57140390.

(b) Do an HFEC inspection of the reinforcing plate end bolts indicated (Refer to NTM

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

(c) Remove the crack stop plug and prepare the hole as detailed in repair R57340223.

Do a HFEC inspection of the crack stop hole (Refer to NTM 51-10-01 Part 6,

Procedure A).

(d) Do a DVI of the local support structure for cracks.

(e) If additional cracks are found or if the existing crack length has increased, repair in

accordance with Para C REPAIR before the next flight.

(f) If there are no additional cracks or if the existing crack length has not increased, it

is also necessary to change the repair in accordance with TASK 576029-833-896

001 REPAIR .

(10) Subtask 576029-832-413-001 - INSPECTION CONFIGURATION 010

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 57-20-12 Part 2

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 59

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

References

Fig. A-UBAAA Sheet 01 - Area to be Inspected

(Configurations 001 thru 014)

Sheet 02 - Areas to be Inspected Before

Repair (Configurations 001, 005 and 006)

Sheet 03 - Area to be Inspected After

Repair R57340199 and R57340223, Large

Plate Option (Configurations 008 and 012)

Sheet 04 - Area to be Inspected for Repair

R57340148 (Configuration 010)

Sheet 05 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

Sheet 06 - Area to be Inspected Post

Production Modification 08488H5253

(Configuration 002)

Sheet 07 - Area to be Inspected for Repair

R57140390 (Configuration 009)

Sheet 08 - Area to be Inspected After

Production Modification 11178H5410

(Configuration 014)

Sheet 09 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

Sheet 10 - Area to be Inspected After

Repair R57340199 and R57340223, Small

Plate Option (Configurations 007 and 011)

Sheet 11 - View from Underside of Wing

Showing Typical Crack (Configurations 001,

005 and 006)

NOTE: The steps that follow are for the LH and RH wings.

Configuration 10 - For aircraft on which repair R57340148 has been incorporated, do the

steps that follow:

Refer to Figure Fig. A-UBAAA Sheet 04.

(a) Do an X-ray inspection of the bottom skin at all the crack stop plug locations.

Inspect skin cracking beyond the crack stop plug (Refer to NTM 57-20-12 Part 2).

(b) Do an X-ray inspection at the reinforcing plate end bolts indicated (Refer to NTM

57-20-12 Part 2).

(c) Do a DVI of the local support structure for cracks.

(d) If there are no new cracks or new crack propagation do repeat inspections or

remove the repair or remove the repair R57340148 and embody repair R57340223.

(e) If additional cracks are found or if the existing crack length has increased, repair in

accordance with TASK 576029-833-896 001 REPAIR , before the next flight.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 60

7

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@A300-600

SERVICE BULLETIN

(11) Subtask 576029-832-414-001 - INSPECTION CONFIGURATION 011

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 57-20-12 Part 2

Fig. A-UBAAA Sheet 01 - Area to be Inspected

(Configurations 001 thru 014)

Sheet 02 - Areas to be Inspected Before

Repair (Configurations 001, 005 and 006)

Sheet 03 - Area to be Inspected After

Repair R57340199 and R57340223, Large

Plate Option (Configurations 008 and 012)

Sheet 04 - Area to be Inspected for Repair

R57340148 (Configuration 010)

Sheet 05 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

Sheet 06 - Area to be Inspected Post

Production Modification 08488H5253

(Configuration 002)

Sheet 07 - Area to be Inspected for Repair

R57140390 (Configuration 009)

Sheet 08 - Area to be Inspected After

Production Modification 11178H5410

(Configuration 014)

Sheet 09 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

Sheet 10 - Area to be Inspected After

Repair R57340199 and R57340223, Small

Plate Option (Configurations 007 and 011)

Sheet 11 - View from Underside of Wing

Showing Typical Crack (Configurations 001,

005 and 006)

NOTE: The steps that follow are for the LH and RH wings.

Configuration 011 - For aircraft on which repair R57340223 (small plate) has been

incorporated, do the steps that follow:

Refer to Figure Fig. A-UBAAA Sheet 10.

(a) Carry out an X-ray inspection of the bottom skin at all the crack stop plug locations.

Inspect skin cracking beyond the crack stop plug (Refer to NTM 57-20-12 Part 2).

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 61

7

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@A300-600

SERVICE BULLETIN

(b) Carry out an X-ray inspection at the reinforcing plate end bolts indicated (Refer to

NTM 57-20-12 Part 2).

(c) Do a DVI of the local support structure for cracks.

(d) If there are no new cracks or new crack propagation do repeat inspections.

(e) If additional cracks are found or if the existing crack length has increased, contact

AIRBUS before the next flight.

(12) Subtask 576029-832-415-001 - INSPECTION CONFIGURATION 012

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 57-20-12 Part 2

Fig. A-UBAAA Sheet 01 - Area to be Inspected

(Configurations 001 thru 014)

Sheet 02 - Areas to be Inspected Before

Repair (Configurations 001, 005 and 006)

Sheet 03 - Area to be Inspected After

Repair R57340199 and R57340223, Large

Plate Option (Configurations 008 and 012)

Sheet 04 - Area to be Inspected for Repair

R57340148 (Configuration 010)

Sheet 05 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

Sheet 06 - Area to be Inspected Post

Production Modification 08488H5253

(Configuration 002)

Sheet 07 - Area to be Inspected for Repair

R57140390 (Configuration 009)

Sheet 08 - Area to be Inspected After

Production Modification 11178H5410

(Configuration 014)

Sheet 09 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

Sheet 10 - Area to be Inspected After

Repair R57340199 and R57340223, Small

Plate Option (Configurations 007 and 011)

Sheet 11 - View from Underside of Wing

Showing Typical Crack (Configurations 001,

005 and 006)

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 62

7

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@A300-600

SERVICE BULLETIN

NOTE: The steps that follow are for the LH and RH wings.

Configuration 012

For aircraft on which repair R57340223 (large plate) has been incorporated, do the steps

that follow:

Refer to Figure Fig. A-UBAAA Sheet 03.

(a) Do an X-ray inspection of the bottom skin at all the crack stop plug locations.

Inspect skin cracking beyond the crack stop plug (Refer to NTM 57-20-12 Part 2).

(b) Do an X-ray inspection at the reinforcing plate end bolts indicated (Refer to NTM

57-20-12 Part 2).

(c) Do a DVI of the local support structure for cracks.

(d) If additional cracks are found or if the existing crack length has increased, contact

AIRBUS before the next flight.

(e) If there are no new cracks or new crack propagation do repeat inspections.

(13) Subtask 576029-832-416-001 - INSPECTION CONFIGURATION 013

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 57-20-12 Part 2

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 63

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A300-600

SERVICE BULLETIN

References

Fig. A-UBAAA Sheet 01 - Area to be Inspected

(Configurations 001 thru 014)

Sheet 02 - Areas to be Inspected Before

Repair (Configurations 001, 005 and 006)

Sheet 03 - Area to be Inspected After

Repair R57340199 and R57340223, Large

Plate Option (Configurations 008 and 012)

Sheet 04 - Area to be Inspected for Repair

R57340148 (Configuration 010)

Sheet 05 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

Sheet 06 - Area to be Inspected Post

Production Modification 08488H5253

(Configuration 002)

Sheet 07 - Area to be Inspected for Repair

R57140390 (Configuration 009)

Sheet 08 - Area to be Inspected After

Production Modification 11178H5410

(Configuration 014)

Sheet 09 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

Sheet 10 - Area to be Inspected After

Repair R57340199 and R57340223, Small

Plate Option (Configurations 007 and 011)

Sheet 11 - View from Underside of Wing

Showing Typical Crack (Configurations 001,

005 and 006)

NOTE: The steps that follow are for the LH and RH wings.

Configuration 013 - For aircraft on which retro-fit modification 11178H5410 (Service

Bulletin A300-57-6064) has been incorporated, do the steps that follow:

Refer to Figure

(a) Do an X-ray inspection of the bottom skin at the historic crack location (Refer to

NTM 57-20-12 Part 2).

(b) Do an X-ray inspection at the repair plate end bolts indicated (Refer to NTM

57-20-12 Part 2).

(c) Do a DVI of the local support structure for cracks.

(d) If there are no new cracks or new crack propagation do repeat inspections.

(e) If additional cracks are found or if the existing crack length has increased, contact

AIRBUS before the next flight.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 64

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@A300-600

SERVICE BULLETIN

(14) Subtask 576029-832-417-001 - INSPECTION CONFIGURATION 014

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 57-20-12 Part 2

Fig. A-UBAAA Sheet 01 - Area to be Inspected

(Configurations 001 thru 014)

Sheet 02 - Areas to be Inspected Before

Repair (Configurations 001, 005 and 006)

Sheet 03 - Area to be Inspected After

Repair R57340199 and R57340223, Large

Plate Option (Configurations 008 and 012)

Sheet 04 - Area to be Inspected for Repair

R57340148 (Configuration 010)

Sheet 05 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

Sheet 06 - Area to be Inspected Post

Production Modification 08488H5253

(Configuration 002)

Sheet 07 - Area to be Inspected for Repair

R57140390 (Configuration 009)

Sheet 08 - Area to be Inspected After

Production Modification 11178H5410

(Configuration 014)

Sheet 09 - Area to be Inspected After

Embodiment of Service Bulletin

A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

Sheet 10 - Area to be Inspected After

Repair R57340199 and R57340223, Small

Plate Option (Configurations 007 and 011)

Sheet 11 - View from Underside of Wing

Showing Typical Crack (Configurations 001,

005 and 006)

NOTE: The steps that follow are for the LH and RH wings.

Configuration 14 - For aircraft on which post production modification 11178H5410 has

been carried out, do the steps that follow:

Refer to Figure Fig. A-UBAAA Sheet 08.

(a) Do an X-ray inspection of the repair plate end bolts indicated (Refer to NTM

57-20-12 Part 2).

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 65

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@A300-600

SERVICE BULLETIN

(b) Do a DVI of the local support structure for cracks.

(c) If additional cracks are found or if the existing crack length has increased, contact

AIRBUS before the next flight.

(d) If no cracks are found, do repeat inspections.

D. TEST

None

E. CLOSE-UP

(1) Subtask 576029-832-419-001

Manpower Resources

Skills AIRFRAME

(a) Make certain that the work areas are clean and clear of tools and other items of

equipment.

(b) Close access panels 575FB/675FB.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 66

7

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@A300-600

SERVICE BULLETIN

Task 576029-833-896-001 - REPAIR

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER

CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

NOTE: These instructions are applicable to the left and right hand wings.

Task Associated Data

Manpower

TOTAL MANHOURS 0.00

ELAPSED TIME (HOURS) 0.00

A. GENERAL

(1) Subtask 576029-900-421-001 - DOCUMENTATION

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

B. PREPARATION

(1) Subtask 576029-833-422-002 - PREPARATION

Manpower Resources

Skills AIRFRAME

Refer to Figure

(a) Get access to the wing bottom skin immediately inboard of rib 9 and aft of the rear

spar.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 67

7

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@A300-600

SERVICE BULLETIN

(b) Open access panels 575FB / 675FB.

(c) Locate the fasteners and the associated internal support structure to be inspected.

C. PROCEDURE

(1) Subtask 576029-833-423-001 - REPAIR - CONFIGURATION 001

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills AIRFRAME

(a) If cracks are found in the internal support structure only and all the cracks

would be removed by embodiment of Service Bulletin A300-57-6064 (Modification

11178H5410) then embody Service Bulletin A300-57-6064 (modification

11178H5410) before the next flight.

(b) For cracks in the bottom skin less than or equal to 76mm (3.0in) in length or cracks

in the skin support flange or cracks in the stiffener, Do a permanent repair in

accordance with Repair Instruction R57340199.

NOTE: The small repair plate (Repair Instruction R57340199) can only be

applied to the cracks in the skin less than or equal to 40mm (1.6in)

in the length and only to the one bolt position shown on the Repair

Instruction.

(c) For the cracks in the bottom skin only, a temporary repair may be carried out in

accordance with Repair Instruction R57340218.

(d) For cracks in the skin greater than 76mm (3.0in) contact AIRBUS for details of an

approved repair.

(2) Subtask 576029-833-427-001 - REPAIR - CONFIGURATION 002

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills AIRFRAME

(a) If cracks are found in the internal support structure only and all the cracks

would be removed by embodiment of Service Bulletin A300-57-6064 (modification

11178H5410) then embody Service Bulletin A300-57-6064 (modification

11178H5410) before the next flight.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 68

7

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@A300-600

SERVICE BULLETIN

(b) If cracks are found that would not be removed by embodiment of Service Bulletin

A300-57-6064 (modification 11178H5410), check the Repair Instruction R57340199.

If the cracks are within the limits of the instruction then repair in accordance with

Repair Instruction R57340199 before next flight.

NOTE: The small repair plate (Repair Instruction R57340199) can only be

applied to the cracks in the skin less than or equal to 40mm (1.6in)

in the length and only to the one bolt position shown on the Repair

Instruction.

(c) If cracks are found that would not be removed by embodiment of R57340199, Do a

repair in accordance with instructions obtained from AIRBUS before the next flight.

(3) Subtask 576029-833-430-001 - REPAIR - CONFIGURATION 003

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills AIRFRAME

(a) If cracks are found in the internal support structure only and all the cracks

would be removed by embodiment of Service Bulletin A300-57-6064 (modification

11178H5410) then embody Service Bulletin A300-57-6064 (modification

11178H5410) before the next flight.

(b) If cracks are found that would not be removed by embodiment of Service Bulletin

A300-57-6064 (modification 11178H5410), check the Repair Instruction R57340199.

If the cracks are within the limits of the instruction then repair in accordance with

Repair Instruction R57340199 before next flight.

NOTE: The small repair plate (Repair Instruction R57340199) can only be

applied to the cracks in the skin less than or equal to 40mm (1.6in)

in the length and only to the one bolt position shown on the Repair

Instruction.

(c) If cracks are found that would not be removed by embodiment of R57340199, Do a

repair in accordance with instructions obtained from AIRBUS before the next flight.

(4) Subtask 576029-833-433-001 - REPAIR - CONFIGURATION 004

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills AIRFRAME

(a) If cracks are found in the internal support structure only and all the cracks

would be removed by embodiment of Service Bulletin A300-57-6064 (modification

11178H5410) then embody Service Bulletin A300-57-6064 (modification

11178H5410) before the next flight.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 69

7

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@A300-600

SERVICE BULLETIN

(b) If cracks are found that would not be removed by embodiment of Service Bulletin

A300-57-6064 (modification 11178H5410), check the Repair Instruction R57340199.

If the cracks are within the limits of the instruction then repair in accordance with

Repair Instruction R57340199 before next flight.

NOTE: The small repair plate (Repair Instruction R57340199) can only be

applied to the cracks in the skin less than or equal to 40mm (1.6in)

in the length and only to the one bolt position shown on the Repair

Instruction.

(c) If cracks are found that would not be removed by embodiment of R57340199, Do a

repair in accordance with instructions obtained from AIRBUS before the next flight.

(5) Subtask 576029-833-436-001 - REPAIR - CONFIGURATION 005

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills AIRFRAME

(a) The temporary repair R57340218 or the permanent repair R57340199 can be

embodied once the crack has cleared the underlying support structure.

(6) Subtask 576029-833-437-001 - REPAIR - CONFIGURATION 006

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills AIRFRAME

(a) For cracks in the bottom skin less than or equal to 76.0mm (3.0in) in length or

cracks in the skin support flange or cracks in the stiffener, Do a permanent repair in

accordance with (Repair Instruction R57340199).

1 For cracks in the skin between 30.0mm (1.18in) and 40.0mm (1.6in) in length

the small plate option must be embodied.

2 For cracks in the skin between 40.0mm (1.6in) and 76.0mm (3.0in) in length

the large plate option must be embodied.

(b) For cracks in the skin greater than 76.0mm (3.0in) contact AIRBUS for details of an

approved repair before the next flight.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 70

7

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@A300-600

SERVICE BULLETIN

(7) Subtask 576029-833-439-001 - REPAIR - CONFIGURATION 007

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills AIRFRAME

(a) For aircraft which have had repair R57340199 (small plate option) and new cracks

have been found, contact AIRBUS for details of an approved repair before the next

flight.

(8) Subtask 576029-833-440-001 - REPAIR - CONFIGURATION 008

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills AIRFRAME

(a) For aircraft which have had repair R57340199 (large plate option) and cracks have

been found, contact AIRBUS for details of an approved repair before the next flight.

(9) Subtask 576029-833-441-001 - REPAIR - CONFIGURATION 009

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills AIRFRAME

(a) For cracks in the bottom skin less than or equal to 76.0mm (3.0in) in length or

cracks in the skin support flange or cracks in the stiffener, Do a permanent repair in

accordance with Repair Instruction R57340223.

1 For cracks in the skin between 30.0mm (1.18in) and 40.0mm (1.6in) in length

the small plate option must be embodied.

2 For cracks in the skin between 40.0mm (1.6in) and 76.0mm (3.0in) in length

the large plate option must be embodied.

(b) For cracks in the skin greater than 76.0mm (3.0in) contact AIRBUS for details of an

approved repair before the next flight.

(10) Subtask 576029-833-443-001 - REPAIR - CONFIGURATION 010

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills AIRFRAME

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 71

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@A300-600

SERVICE BULLETIN

(a) For cracks in the bottom skin less than or equal to 85.0mm (3.35in) in length or

cracks in the skin support flange or cracks in the stiffener, do a permanent repair in

accordance with Repair Instruction R57340223.

1 For cracks in the skin between 30.0mm (1.18in) and 40.0mm (1.6in) in length

the small plate option must be embodied.

2 For cracks in the skin between 40.0mm (1.6in) and 85.0mm (3.35in) in length

the large plate option must be embodied.

(b) For cracks in the skin greater than 85.0mm (3.35in) contact AIRBUS for details of

an approved repair before the next flight.

(11) Subtask 576029-833-445-001 - REPAIR - CONFIGURATION 011

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills AIRFRAME

(a) For aircraft which have had repair R57340223 (small plate option) and cracks have

been found, contact AIRBUS for details of an approved repair before the next flight.

(12) Subtask 576029-833-446-001 - REPAIR - CONFIGURATION 012

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills AIRFRAME

(a) For aircraft which have had repair R57340223 (large plate option) and cracks have

been found, contact AIRBUS for details of an approved repair before the next flight.

(13) Subtask 576029-833-447-001 - REPAIR - CONFIGURATION 013

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills AIRFRAME

(a) For aircraft which have had retro-fit modification 11178H5410 (Service Bulletin

A300-57-6064) and cracks have been found, contact AIRBUS for details of an

approved repair before the next flight.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 72

7

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@A300-600

SERVICE BULLETIN

(14) Subtask 576029-833-448-001 - REPAIR - CONFIGURATION 014

Manpower Resources

Manhours 0

Minimum number of person 0

Subtask elapsed time 0

Skills AIRFRAME

(a) For aircraft which have had repair modification 11178H5410 and cracks have been

found, contact AIRBUS for details of an approved repair before the next flight.

D. TEST

None

E. CLOSE-UP

(1) Subtask 576029-833-450-002 - CLOSE-UP

Manpower Resources

Skills AIRFRAME

(a) Make certain that the work areas are clean and clear of tools and other items of

equipment.

(b) Close access panels 575FB/675FB.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 73

7

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@A300-600

SERVICE BULLETIN

**CONF ALL

LH WING SHOWN

RH WING SIMILAR

D_SB_576029_7_BAAA_01_00

REAR SPAR

575FB (675FB)

RIB9

A B C D E F G H J K

Figure A-UBAAA - Sheet 01

- Area to be Inspected (Configurations 001 thru 014)

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 74

7

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@A300-600

SERVICE BULLETIN

**CONF ALL

HINGE

FALSE

REAR SPAR

REAR SPAR

DATUM

SKIN SUPPORT

FLANGE

STIFFENER

FLANGE

JOGGLED

SECTION

D_SB_576029_7_BAAA_02_00

NOTE:

FASTENER HOLES TO BE INSPECTED

F

W

D

A INBD

BEFORE

REPAIR

575FB (675FB)

Figure A-UBAAA - Sheet 02

- Areas to be Inspected Before Repair (Configurations 001, 005 and 006)

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 75

7

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@A300-600

SERVICE BULLETIN

**CONF ALL

HINGE

FALSE

REAR SPAR

REAR SPAR

DATUM

SKIN SUPPORT

FLANGE STIFFENER

D_SB_576029_7_BAAA_03_00

F

W

D

INBD

AFTER REPAIR

R57340199 AND R57340223

(LARGE PLATE OPTION)

X−RAY INSPECTION AREAS

CRACK STOP PLUG

NOTE:

REPAIR PLATE END FASTENERS

B

575FB (675FB)

Figure A-UBAAA - Sheet 03

- Area to be Inspected After Repair R57340199 and R57340223, Large Plate Option (Configurations

008 and 012)

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 76

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@A300-600

SERVICE BULLETIN

**CONF ALL

FALSE REAR

SPAR DATUM

 REPAIR

 PLATE

TYPICAL CRACK

STOP HOLE

 REAR SPAR

 DATUM

D_SB_576029_7_BAAA_04_00

AFTER REPAIR

R57340148

C

X−RAY INSPECTION AREAS

REPAIR PLATE END BOLTS

NOTE:

Figure A-UBAAA - Sheet 04

- Area to be Inspected for Repair R57340148 (Configuration 010)

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 77

7

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@A300-600

SERVICE BULLETIN

**CONF ALL

F

W

D

INBD

AFTER REPAIR

SB A300−57−6064

D

D_SB_576029_7_BAAA_05_00

X−RAY INSPECTION AREAS

NOTE:

MOD PLATE END FASTENERS

FALSE

REAR SPAR

REAR SPAR

DATUM

SKIN SUPPORT

FLANGE STIFFENER

575FB (675FB)

HINGE

Figure A-UBAAA - Sheet 05

- Area to be Inspected After Embodiment of Service Bulletin A300-57-6064 (Retro-Modification

11178H5410) (Configuration 013)

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 78

7

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@A300-600

SERVICE BULLETIN

**CONF ALL

HISTORIC CRACK

INITIATION SITE

FALSE

REAR SPAR

REAR SPAR

DATUM

SUPPORT

STRUCTURE SUPPORT

STRUCTURE

F

W

D

INBD

AFTER MODIFICATION

08488H5253

D_SB_576029_7_BAAA_06_00

E

HFEC INSPECTION AREA

NOTE:

Figure A-UBAAA - Sheet 06

- Area to be Inspected Post Production Modification 08488H5253 (Configuration 002)

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 79

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@A300-600

SERVICE BULLETIN

**CONF ALL

REAR SPAR

DATUM

FALSE REAR

SPAR DATUM

TYPICAL CRACK

STOP HOLE

D_SB_576029_7_BAAA_07_00

NOTE:

HOLES TO BE INSPECTED

AFTER REPAIR

R57140390

F

Figure A-UBAAA - Sheet 07

- Area to be Inspected for Repair R57140390 (Configuration 009)

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 80

7

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@A300-600

SERVICE BULLETIN

**CONF ALL

FALSE

REAR SPAR

REAR SPAR

DATUM

INTERNAL PLATE

SKIN SUPPORT

FLANGE STIFFENER

D_SB_576029_7_BAAA_08_00

F

W

D

INBD

AFTER MODIFICATION

11178H5410

G

EXTERNAL PLATE

X−RAY INSPECTION AREAS

NOTE:

MOD PLATE END FASTENERS

Figure A-UBAAA - Sheet 08

- Area to be Inspected After Production Modification 11178H5410 (Configuration 014)

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 81

7

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@A300-600

SERVICE BULLETIN

**CONF ALL

HISTORIC CRACK

INITIATION SITE

FALSE

REAR SPAR

REAR SPAR

DATUM

SUPPORT

STRUCTURE

SUPPORT

STRUCTURE

REINFORCING

PLATE

D_SB_576029_7_BAAA_09_00

F

W

D

INBD

AFTER SB A300−57−6030

H

X−RAY INSPECTION AREAS

NOTE:

REINFORCING PLATE END FASTENERS

Figure A-UBAAA - Sheet 09

- Area to be Inspected After Embodiment of Service Bulletin A300-57-6030 (Retro-Modification

08488H5253) (Configurations 003 and 004)

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 82

7

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@A300-600

SERVICE BULLETIN

**CONF ALL

HINGE

FALSE

REAR SPAR

REAR SPAR

DATUM

SKIN SUPPORT

FLANGE STIFFENER

D_SB_576029_7_BAAA_10_00

F

W

D

INBD

AFTER REPAIR

R57340199 AND R57340223

(SMALL PLATE OPTION)

575FB (675FB)

J

X−RAY INSPECTION AREAS

CRACK STOP PLUG

NOTE:

REPAIR PLATE END FASTENERS

Figure A-UBAAA - Sheet 10

- Area to be Inspected After Repair R57340199 and R57340223, Small Plate Option (Configurations

007 and 011)

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 83

7

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@A300-600

SERVICE BULLETIN

**CONF ALL

HINGE

FALSE

REAR SPAR

REAR SPAR

DATUM

INTERNAL STRUCTURE CRACK ORIGINATING

FROM FASTENER HOLE

CRACK ORIGINATING

FROM EDGE OF SKIN

CRACK LENGTH

MEASURED FROM

EDGE OF SKIN

EDGE OF

SKIN

CRACK

STOP

HOLES

PANEL

PANEL

PANEL

CRACK WHICH HAS

NOT CLEARED THE

SUPPORT STRUCTURE

D_SB_576029_7_BAAA_11_00

F

W

D

INBD

TYPICAL CRACK VIEW

NOTE:

CRACK STOP PLUG

K

Figure A-UBAAA - Sheet 11

- View from Underside of Wing Showing Typical Crack (Configurations 001, 005 and 006)

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 84

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@A300-600

SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - INSPECT LOWER SKIN PANEL INBOARD OF RIB 9 AND AFT

OF REAR SPAR

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:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 1

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@A300-600

SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Apr 28/93 SERVICE BULLETIN No.: A300-57-6029

REVISION No.: 08 - Apr 25/13 Page: 1

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