# @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



# MANDATORYMANDATORYMANDATORY

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 TASK576029- 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 7

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# @A300-600
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 TASK576029- 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 7

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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 7

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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. 

# MANDATORYMANDATORYMANDATORY

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

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# @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



# MANDATORYMANDATORYMANDATORY

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 7

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# @A300-600
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 7

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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 7

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# @A300-600
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 7

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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 7

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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 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 7

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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
FC FH FC FH HFEC Inspect bottom 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
FC FH FC FH HFEC Inspect bottom 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
FC FH FC FH HFEC Inspect bottom 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 7

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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
FC FH FC FH HFEC Inspect bottom 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 Threshold Inspection Interval Inspection 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 Threshold Inspection Interval Inspection 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 7

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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 Threshold Inspection Interval Inspection 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 7

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# @A300-600
SERVICE BULLETIN

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 Threshold Inspection Interval Inspection 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
FC FH FC FH X-ray (See 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 7

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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
FC FH FC FH X-ray (See 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 7

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# @A300-600
SERVICE BULLETIN

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. FC FH FC FH X-ray (See 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
FC FH FC FH X-ray (See 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 7

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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). Inspection Interval Crack length measured from aft 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). Inspection Interval Crack length measured from aft 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). Inspection Interval Crack length measured from aft 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 7

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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). Inspection Interval Crack length measured from aft 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 7

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# @A300-600
SERVICE BULLETIN

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 Threshold Inspection Interval Inspection 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 7

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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 Threshold Inspection Interval Inspection 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 Threshold Inspection Interval Inspection 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 7

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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 Threshold Inspection Interval Inspection 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 7

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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 Threshold Inspection Interval Inspection 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 Threshold Inspection Interval Inspection 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

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# @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 Threshold Inspection Interval Inspection 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

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# @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 Threshold Inspection Interval Inspection 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

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# @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 Threshold Inspection Interval Inspection 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

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# @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 Threshold Inspection Interval Inspection 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 Threshold Inspection Interval Inspection 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

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# @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 Threshold Inspection Interval Inspection 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 Threshold Inspection Interval Inspection 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

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# @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

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# @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 Threshold Inspection Interval Inspection 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

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# @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 Threshold Inspection Interval Inspection 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

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# @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

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# @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 Threshold Inspection Interval Inspection 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

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# @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 Threshold Inspection Interval Inspection 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

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# @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 Threshold Inspection Interval Inspection 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 Threshold Inspection Interval Inspection 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

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# @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 Threshold Inspection Interval Inspection 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 Threshold Inspection Interval Inspection 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

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# @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 Threshold Inspection Interval Inspection 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 7

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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 Threshold Inspection Interval Inspection 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 7

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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 Threshold Inspection Interval Inspection 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 7

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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 Threshold Inspection Interval Inspection 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 7

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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 Threshold Inspection Interval Inspection 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 Threshold Inspection Interval Inspection 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 7

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# @A300-600
SERVICE BULLETIN

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 Threshold Inspection Interval Inspection 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 Threshold Inspection Interval Inspection 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 Threshold Inspection Interval Inspection 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 7

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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 Threshold Inspection Interval Inspection 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 Threshold Inspection Interval Inspection 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 7

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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 7

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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 7

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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 7

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SERVICE BULLETIN

This Page Intentionally Left Blank

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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 7

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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 7

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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 7

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(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 7

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(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 7

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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

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(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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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

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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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(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

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(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

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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

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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.

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(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

.
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(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

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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) 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

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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) 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 7

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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 7

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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
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(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 7

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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 INBD**  

## A
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 7

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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 7

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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

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @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

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @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 7

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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 7

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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 7

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.