# @A300 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: 54 

### TITLE: NACELLES/PYLON - INSPECT PYLON LOWER SPAR BETWEEN RIBS 6 AND 7 MODIFICATION No.: None This page transmits Revision No.03 of Service Bulletin No.A300-54-0073 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 03 issued to update the threshold and intervals analysis improvement and in-service crack findings consistency. CHANGES 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 Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N 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
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 1 5

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# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
MANPOWER Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N APPENDICES Minor editorial or document structure change N Fig. A-FSAAA Minor editorial or document structure change N Fig. A-FSAAA Sheet 01 Minor editorial or document structure change N 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 CONF 002 Minor editorial or document structure change N CONF 003 Minor editorial or document structure change N CONF 004 Minor editorial or document structure change N CONF 005 Minor editorial or document structure change N CONF 006 Minor editorial or document structure change N CONF 007 Minor editorial or document structure change N Material Effectivity Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N 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 Accomplishment Timescale Minor editorial or document structure change N Accomplishment Timescale Minor editorial or document structure change N Accomplishment Timescale Minor editorial or document structure change N Accomplishment Timescale Minor editorial or document structure change N Accomplishment Timescale Minor editorial or document structure change N Accomplishment Timescale Minor editorial or document structure change N
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 2 5

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

# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
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 Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N WEIGHT AND BALANCE Minor editorial or document structure change N 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 Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N PUBLICATION AFFECTED Minor editorial or document structure change N 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 Procurement Addresses Minor editorial or document structure change N 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 Kit 540073A01R03 Minor editorial or document structure change N Kit 540073A02R02 Minor editorial or document structure change N Kit 540073A03R00 Minor editorial or document structure change N LIST OF MATERIALS - OPERATOR SUPPLIED Minor editorial or document structure change N Consumable Materials Minor editorial or document structure change N Consumable CMLA01 Minor editorial or document structure change N Components Minor editorial or document structure change N Equipment Minor editorial or document structure change N

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 3 5

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# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
PARTS TO BE RE-IDENTIFIED BY OPERATOR Minor editorial or document structure change N TOOLING Minor editorial or document structure change N Tooling - Price and Availability Minor editorial or document structure change N Tools Minor editorial or document structure change N Special Tools Minor editorial or document structure change N ACCOMPLISHMENT INSTRUCTIONS TASK 540073- 832-801-001-Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 Minor editorial or document structure change N
Task associated data - 001 Minor editorial or document structure change N Task associated data - 002 Minor editorial or document structure change N Task associated data - 003 Minor editorial or document structure change N Task associated data - 004 Minor editorial or document structure change N Task associated data - 005 Minor editorial or document structure change N Task associated data - 006 Minor editorial or document structure change N Task associated data - 007 Minor editorial or document structure change N Subtask 540073-910-001-001 Minor editorial or document structure change N Subtask 540073-839-001-001 Minor editorial or document structure change N Subtask 540073-910-001-001 Minor editorial or document structure change N Subtask 540073-839-001-001 Minor editorial or document structure change N Subtask 540073-910-001-001 Minor editorial or document structure change N Subtask 540073-839-001-001 Minor editorial or document structure change N Subtask 540073-910-001-001 Minor editorial or document structure change N Subtask 540073-839-001-001 Minor editorial or document structure change N Subtask 540073-910-001-001 Minor editorial or document structure change N Subtask 540073-839-001-001 Minor editorial or document structure change N Subtask 540073-910-001-001 Minor editorial or document structure change N Subtask 540073-839-001-001 Minor editorial or document structure change N Subtask 540073-910-001-001 Minor editorial or document structure change N Subtask 540073-839-001-001 Minor editorial or document structure change N Subtask 540073-941-001-001 Minor editorial or document structure change N Subtask 540073-010-001-001 Minor editorial or document structure change N Subtask 540073-941-001-001 Minor editorial or document structure change N Subtask 540073-010-001-001 Minor editorial or document structure change N Subtask 540073-941-001-001 Minor editorial or document structure change N Subtask 540073-010-001-001 Minor editorial or document structure change N Subtask 540073-941-001-001 Minor editorial or document structure change N Subtask 540073-010-001-002 Minor editorial or document structure change N Subtask 540073-941-001-001 Minor editorial or document structure change N Subtask 540073-010-001-002 Minor editorial or document structure change N Subtask 540073-941-001-001 Minor editorial or document structure change N
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 4 5

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

# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 540073-010-001-002 Minor editorial or document structure change N Subtask 540073-941-001-001 Minor editorial or document structure change N Subtask 540073-010-001-002 Minor editorial or document structure change N Subtask 540073-832-001-001 Minor editorial or document structure change N Subtask 540073-832-005-001 Minor editorial or document structure change N Subtask 540073-832-001-001 Minor editorial or document structure change N Subtask 540073-832-005-001 Minor editorial or document structure change N Subtask 540073-832-001-001 Minor editorial or document structure change N Subtask 540073-832-005-001 Minor editorial or document structure change N Subtask 540073-832-001-001 Minor editorial or document structure change N Subtask 540073-832-005-002 Minor editorial or document structure change N Subtask 540073-832-001-001 Minor editorial or document structure change N Subtask 540073-832-005-002 Minor editorial or document structure change N Subtask 540073-832-001-001 Minor editorial or document structure change N Subtask 540073-832-005-002 Minor editorial or document structure change N Subtask 540073-832-001-003 Minor editorial or document structure change N Subtask 540073-832-005-003 Minor editorial or document structure change N Subtask 540073-700-002-001 Minor editorial or document structure change N Subtask 540073-700-002-001 Minor editorial or document structure change N Subtask 540073-700-002-001 Minor editorial or document structure change N Subtask 540073-700-002-001 Minor editorial or document structure change N Subtask 540073-700-002-001 Minor editorial or document structure change N Subtask 540073-700-002-001 Minor editorial or document structure change N Subtask 540073-700-002-001 Minor editorial or document structure change N Subtask 540073-410-001-001 Minor editorial or document structure change N Subtask 540073-942-002-001 Minor editorial or document structure change N Subtask 540073-410-001-001 Minor editorial or document structure change N Subtask 540073-942-002-001 Minor editorial or document structure change N Subtask 540073-410-001-001 Minor editorial or document structure change N Subtask 540073-942-002-001 Minor editorial or document structure change N Subtask 540073-410-001-002 Minor editorial or document structure change N Subtask 540073-942-002-001 Minor editorial or document structure change N Subtask 540073-410-001-002 Minor editorial or document structure change N Subtask 540073-942-002-001 Minor editorial or document structure change N Subtask 540073-410-001-002 Minor editorial or document structure change N Subtask 540073-942-002-001 Minor editorial or document structure change N Subtask 540073-410-001-002 Minor editorial or document structure change N Subtask 540073-942-002-001 Minor editorial or document structure change N TASK 540073- 832-804-001-Inspection Post Repair Minor editorial or document structure change N Task associated data - 001 Minor editorial or document structure change N
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 5 5

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

# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Task associated data - 002 Minor editorial or document structure change N Task associated data - 003 Minor editorial or document structure change N Task associated data - 004 Minor editorial or document structure change N Task associated data - 005 Minor editorial or document structure change N Task associated data - 006 Minor editorial or document structure change N Task associated data - 007 Minor editorial or document structure change N Subtask 540073-910-003-001 Minor editorial or document structure change N Subtask 540073-839-003-001 Minor editorial or document structure change N Subtask 540073-910-003-001 Minor editorial or document structure change N Subtask 540073-839-003-001 Minor editorial or document structure change N Subtask 540073-910-003-001 Minor editorial or document structure change N Subtask 540073-839-003-001 Minor editorial or document structure change N Subtask 540073-910-003-001 Minor editorial or document structure change N Subtask 540073-839-003-001 Minor editorial or document structure change N Subtask 540073-910-003-001 Minor editorial or document structure change N Subtask 540073-839-003-001 Minor editorial or document structure change N Subtask 540073-910-003-001 Minor editorial or document structure change N Subtask 540073-839-003-001 Minor editorial or document structure change N Subtask 540073-910-003-001 Minor editorial or document structure change N Subtask 540073-839-003-001 Minor editorial or document structure change N Subtask 540073-941-002-001 Minor editorial or document structure change N Subtask 540073-010-005-001 Minor editorial or document structure change N Subtask 540073-941-002-001 Minor editorial or document structure change N Subtask 540073-010-005-001 Minor editorial or document structure change N Subtask 540073-941-002-001 Minor editorial or document structure change N Subtask 540073-010-005-001 Minor editorial or document structure change N Subtask 540073-941-002-001 Minor editorial or document structure change N Subtask 540073-010-005-002 Minor editorial or document structure change N Subtask 540073-941-002-001 Minor editorial or document structure change N Subtask 540073-010-005-002 Minor editorial or document structure change N Subtask 540073-941-002-001 Minor editorial or document structure change N Subtask 540073-010-005-002 Minor editorial or document structure change N Subtask 540073-941-002-001 Minor editorial or document structure change N Subtask 540073-010-005-002 Minor editorial or document structure change N Subtask 540073-832-008-001 Minor editorial or document structure change N Subtask 540073-832-008-001 Minor editorial or document structure change N Subtask 540073-832-008-001 Minor editorial or document structure change N Subtask 540073-832-008-001 Minor editorial or document structure change N Subtask 540073-832-008-001 Minor editorial or document structure change N Subtask 540073-832-008-001 Minor editorial or document structure change N Subtask 540073-832-008-002 Minor editorial or document structure change N
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 6 5

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

# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 540073-700-003-001 Minor editorial or document structure change N Subtask 540073-700-003-001 Minor editorial or document structure change N Subtask 540073-700-003-001 Minor editorial or document structure change N Subtask 540073-700-003-001 Minor editorial or document structure change N Subtask 540073-700-003-001 Minor editorial or document structure change N Subtask 540073-700-003-001 Minor editorial or document structure change N Subtask 540073-700-003-001 Minor editorial or document structure change N Subtask 540073-410-003-001 Minor editorial or document structure change N Subtask 540073-942-004-001 Minor editorial or document structure change N Subtask 540073-410-003-001 Minor editorial or document structure change N Subtask 540073-942-004-001 Minor editorial or document structure change N Subtask 540073-410-003-001 Minor editorial or document structure change N Subtask 540073-942-004-001 Minor editorial or document structure change N Subtask 540073-410-003-002 Minor editorial or document structure change N Subtask 540073-942-004-001 Minor editorial or document structure change N Subtask 540073-410-003-002 Minor editorial or document structure change N Subtask 540073-942-004-001 Minor editorial or document structure change N Subtask 540073-410-003-002 Minor editorial or document structure change N Subtask 540073-942-004-001 Minor editorial or document structure change N Subtask 540073-410-003-002 Minor editorial or document structure change N Subtask 540073-942-004-001 Minor editorial or document structure change N TASK 540073- 832-805-001-Inspection Post Service Bulletin No.A300-54-0080 Minor editorial or document structure change N Task associated data - 001 Minor editorial or document structure change N Task associated data - 002 Minor editorial or document structure change N Task associated data - 003 Minor editorial or document structure change N Task associated data - 004 Minor editorial or document structure change N Task associated data - 005 Minor editorial or document structure change N Task associated data - 006 Minor editorial or document structure change N Task associated data - 007 Minor editorial or document structure change N Subtask 540073-910-004-001 Minor editorial or document structure change N Subtask 540073-839-004-001 Minor editorial or document structure change N Subtask 540073-910-004-001 Minor editorial or document structure change N Subtask 540073-839-004-001 Minor editorial or document structure change N Subtask 540073-910-004-001 Minor editorial or document structure change N Subtask 540073-839-004-001 Minor editorial or document structure change N Subtask 540073-910-004-001 Minor editorial or document structure change N Subtask 540073-839-004-001 Minor editorial or document structure change N Subtask 540073-910-004-001 Minor editorial or document structure change N Subtask 540073-839-004-001 Minor editorial or document structure change N Subtask 540073-910-004-001 Minor editorial or document structure change N
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 7 5

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

# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 540073-839-004-001 Minor editorial or document structure change N Subtask 540073-910-004-001 Minor editorial or document structure change N Subtask 540073-839-004-001 Minor editorial or document structure change N Subtask 540073-941-003-001 Minor editorial or document structure change N Subtask 540073-010-006-001 Minor editorial or document structure change N Subtask 540073-941-003-001 Minor editorial or document structure change N Subtask 540073-010-006-001 Minor editorial or document structure change N Subtask 540073-941-003-001 Minor editorial or document structure change N Subtask 540073-010-006-001 Minor editorial or document structure change N Subtask 540073-941-003-001 Minor editorial or document structure change N Subtask 540073-010-006-002 Minor editorial or document structure change N Subtask 540073-941-003-001 Minor editorial or document structure change N Subtask 540073-010-006-002 Minor editorial or document structure change N Subtask 540073-941-003-001 Minor editorial or document structure change N Subtask 540073-010-006-002 Minor editorial or document structure change N Subtask 540073-941-003-001 Minor editorial or document structure change N Subtask 540073-010-006-002 Minor editorial or document structure change N Subtask 540073-832-009-001 Minor editorial or document structure change N Subtask 540073-832-009-001 Minor editorial or document structure change N Subtask 540073-832-009-001 Minor editorial or document structure change N Subtask 540073-832-009-001 Minor editorial or document structure change N Subtask 540073-832-009-001 Minor editorial or document structure change N Subtask 540073-832-009-001 Minor editorial or document structure change N Subtask 540073-832-009-003 Minor editorial or document structure change N Subtask 540073-700-004-001 Minor editorial or document structure change N Subtask 540073-700-004-001 Minor editorial or document structure change N Subtask 540073-700-004-001 Minor editorial or document structure change N Subtask 540073-700-004-001 Minor editorial or document structure change N Subtask 540073-700-004-001 Minor editorial or document structure change N Subtask 540073-700-004-001 Minor editorial or document structure change N Subtask 540073-700-004-001 Minor editorial or document structure change N Subtask 540073-410-004-001 Minor editorial or document structure change N Subtask 540073-942-005-001 Minor editorial or document structure change N Subtask 540073-410-004-001 Minor editorial or document structure change N Subtask 540073-942-005-001 Minor editorial or document structure change N Subtask 540073-410-004-001 Minor editorial or document structure change N Subtask 540073-942-005-001 Minor editorial or document structure change N Subtask 540073-410-004-002 Minor editorial or document structure change N Subtask 540073-942-005-001 Minor editorial or document structure change N Subtask 540073-410-004-002 Minor editorial or document structure change N Subtask 540073-942-005-001 Minor editorial or document structure change N
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 8 5

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# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 540073-410-004-002 Minor editorial or document structure change N Subtask 540073-942-005-001 Minor editorial or document structure change N Subtask 540073-410-004-002 Minor editorial or document structure change N Subtask 540073-942-005-001 Minor editorial or document structure change N TASK 540073- 833-801-001-Repair Minor editorial or document structure change N Task associated data - 001 Minor editorial or document structure change N Task associated data - 002 Minor editorial or document structure change N Task associated data - 003 Minor editorial or document structure change N Task associated data - 004 Minor editorial or document structure change N Task associated data - 005 Minor editorial or document structure change N Task associated data - 006 Minor editorial or document structure change N Task associated data - 007 Minor editorial or document structure change N Subtask 540073-910-002-001 Minor editorial or document structure change N Subtask 540073-839-002-001 Minor editorial or document structure change N Subtask 540073-910-002-001 Minor editorial or document structure change N Subtask 540073-839-002-001 Minor editorial or document structure change N Subtask 540073-910-002-001 Minor editorial or document structure change N Subtask 540073-839-002-001 Minor editorial or document structure change N Subtask 540073-910-002-001 Minor editorial or document structure change N Subtask 540073-839-002-001 Minor editorial or document structure change N Subtask 540073-910-002-001 Minor editorial or document structure change N Subtask 540073-839-002-001 Minor editorial or document structure change N Subtask 540073-910-002-001 Minor editorial or document structure change N Subtask 540073-839-002-001 Minor editorial or document structure change N Subtask 540073-910-002-001 Minor editorial or document structure change N Subtask 540073-839-002-001 Minor editorial or document structure change N Subtask 540073-010-003-001 Minor editorial or document structure change N Subtask 540073-010-004-001 Minor editorial or document structure change N Subtask 540073-010-003-001 Minor editorial or document structure change N Subtask 540073-010-004-001 Minor editorial or document structure change N Subtask 540073-010-003-001 Minor editorial or document structure change N Subtask 540073-010-004-001 Minor editorial or document structure change N Subtask 540073-010-003-001 Minor editorial or document structure change N Subtask 540073-010-004-001 Minor editorial or document structure change N Subtask 540073-010-003-001 Minor editorial or document structure change N Subtask 540073-010-004-001 Minor editorial or document structure change N Subtask 540073-010-003-001 Minor editorial or document structure change N Subtask 540073-010-004-001 Minor editorial or document structure change N Subtask 540073-010-003-001 Minor editorial or document structure change N Subtask 540073-010-004-001 Minor editorial or document structure change N Subtask 540073-833-001-001 Minor editorial or document structure change N
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 9 5

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# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 540073-833-002-001 Minor editorial or document structure change N Subtask 540073-833-001-001 Minor editorial or document structure change N Subtask 540073-833-002-001 Minor editorial or document structure change N Subtask 540073-833-001-001 Minor editorial or document structure change N Subtask 540073-833-002-001 Minor editorial or document structure change N Subtask 540073-833-001-003 Minor editorial or document structure change N Subtask 540073-833-002-002 Minor editorial or document structure change N Subtask 540073-833-001-003 Minor editorial or document structure change N Subtask 540073-833-002-002 Minor editorial or document structure change N Subtask 540073-833-001-003 Minor editorial or document structure change N Subtask 540073-833-002-002 Minor editorial or document structure change N Subtask 540073-833-001-002 Minor editorial or document structure change N Subtask 540073-833-002-003 Minor editorial or document structure change N Subtask 540073-700-001-001 Minor editorial or document structure change N Subtask 540073-700-001-001 Minor editorial or document structure change N Subtask 540073-700-001-001 Minor editorial or document structure change N Subtask 540073-700-001-001 Minor editorial or document structure change N Subtask 540073-700-001-001 Minor editorial or document structure change N Subtask 540073-700-001-001 Minor editorial or document structure change N Subtask 540073-700-001-001 Minor editorial or document structure change N Subtask 540073-942-001-001 Minor editorial or document structure change N Subtask 540073-942-003-001 Minor editorial or document structure change N Subtask 540073-942-001-001 Minor editorial or document structure change N Subtask 540073-942-003-001 Minor editorial or document structure change N Subtask 540073-942-001-001 Minor editorial or document structure change N Subtask 540073-942-003-001 Minor editorial or document structure change N Subtask 540073-942-001-001 Minor editorial or document structure change N Subtask 540073-942-003-001 Minor editorial or document structure change N Subtask 540073-942-001-001 Minor editorial or document structure change N Subtask 540073-942-003-001 Minor editorial or document structure change N Subtask 540073-942-001-001 Minor editorial or document structure change N Subtask 540073-942-003-001 Minor editorial or document structure change N Subtask 540073-942-001-001 Minor editorial or document structure change N Subtask 540073-942-003-001 Minor editorial or document structure change N Fig. A-FBAAA Minor editorial or document structure change N Fig. A-FBAAA Sheet 01 Minor editorial or document structure change N Fig. A-FBCAA Minor editorial or document structure change N Fig. A-FBCAA Sheet 01 Minor editorial or document structure change N Fig. A-FBBAA Minor editorial or document structure change N Fig. A-FBBAA Sheet 01 Minor editorial or document structure change N Fig. A-FBDAA Minor editorial or document structure change N
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 10 5

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# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Fig. A-FBDAA Sheet 01 Minor editorial or document structure change N Fig. A-FBFAA Minor editorial or document structure change N Fig. A-FBFAA Sheet 01 Minor editorial or document structure change N Fig. A-FBEAA Minor editorial or document structure change N Fig. A-FBEAA Sheet 01 Minor editorial or document structure change N Fig. A-FFAAA Minor editorial or document structure change N Fig. A-FFAAA Sheet 01 Minor editorial or document structure change N Fig. A-FFBAA Minor editorial or document structure change N Fig. A-FFBAA Sheet 01 Minor editorial or document structure change N Fig. A-FBGAA Minor editorial or document structure change N Fig. A-FBGAA Sheet 01 Minor editorial or document structure change N Fig. A-FBGAA Sheet 02 Minor editorial or document structure change N Fig. A-FBHAA Minor editorial or document structure change N Fig. A-FBHAA Sheet 01 Minor editorial or document structure change N Fig. A-FBHAA Sheet 02 Minor editorial or document structure change N Appendix 01- Inspection Report APPENDIX CONTENT Minor editorial or document structure change N Fig. A-FRAAA Minor editorial or document structure change N Fig. A-FRAAA Sheet 01 Minor editorial or document structure change N Fig. A-FRAAA Sheet 02 Minor editorial or document structure change N Fig. A-FRAAA Sheet 03 Minor editorial or document structure change N Fig. A-FRBAA Minor editorial or document structure change N Fig. A-FRBAA Sheet 01 Minor editorial or document structure change N Fig. A-FRBAA Sheet 02 Minor editorial or document structure change N Fig. A-FRBAA Sheet 03 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 Revision No. 01 issued to inform the operators of Airworthiness Directive (AD) number. Revision No. 02 issued to add a liquid penetrant Inspection as an alternative to the eddy current Inspection, and to update the effectivity. REVISION SEQUENCE ORIGINAL: Oct 15/93 REVISION No.: 01 - Mar 28/94
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 11 5

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# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET REVISION No.: 02 - Jul 09/02 REVISION No. : 03 - Oct 11/12

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 12 5

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

# @A300 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: 54 

### TITLE: NACELLES/PYLON - INSPECT PYLON LOWER SPAR BETWEEN RIBS 6 AND 7 **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES On A/C fitted with GE pylon and PW, crack has been reported on pylon lower spar. The crack is running between ribs 6 and 7 and is starting on the center stiffener after the flat area. Some cracks have been reported re-initiating even after Service Bulletin embodiment. Hence a deeper investigation has been performed in order to propose the best solution possible to the operators. The aim of this Service Bulletin is to call for Eddy Current Inspection or Liquid Penetrant Inspection of the pylon lower spar in order to detect any crack. This inspection will make it possible to detect crack propagation at an early stage, thus avoiding a significant repair and reduction of the structural capacity. New FC/FH figures of Thresholds and Intervals, due to improvement of analyses and also consistent with in-service crack findings, were acknowledged by Airworthiness Authorities. 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.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 1 5

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# @A300 SERVICE BULLETIN SUMMARY MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 540073A01R03 2 2,880.00 Doubler **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 540073A01R03 2 2,880.00 Doubler **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 540073A01R03 2 2,880.00 Doubler **CONF 004 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 540073A03R00 2 2,880.00 Doubler **CONF 005 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 540073A03R00 2 2,880.00 Doubler **CONF 006 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 540073A03R00 2 2,880.00 Doubler

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 2 5

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# @A300 SERVICE BULLETIN SUMMARY **CONF 007 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 540073A02R02 2 2,840.00 Doubler EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

001 50W 69X 72U ABR AFG C2A DHL F2I FLM GST IAW IRA IRM KYE KZU MIX MNB MNG MSR NTR P2A RUN SOP TNO TSY CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 54.51.41.002 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 **CONF 001 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 Task 540073-832-804-001: Inspection Post Repair TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 3 5

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# @A300 SERVICE BULLETIN SUMMARY Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 Task 540073-833-801-001: Repair TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 **CONF 002 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 Task 540073-832-804-001: Inspection Post Repair TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 Task 540073-833-801-001: Repair TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 **CONF 003 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 Task 540073-832-804-001: Inspection Post Repair TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 Task 540073-833-801-001: Repair TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 4 5

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# @A300 SERVICE BULLETIN SUMMARY **CONF 004 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 Task 540073-832-804-001: Inspection Post Repair TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 Task 540073-833-801-001: Repair TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 **CONF 005 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 Task 540073-832-804-001: Inspection Post Repair TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 Task 540073-833-801-001: Repair TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 **CONF 006 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 Task 540073-832-804-001: Inspection Post Repair TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 5 5

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# @A300 SERVICE BULLETIN SUMMARY Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 Task 540073-833-801-001: Repair TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 **CONF 007 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 Task 540073-832-804-001: Inspection Post Repair TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 Task 540073-833-801-001: Repair TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 APPENDICES **CONF ALL Appendix 01- Inspection Report

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 6 5

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# @A300 SERVICE BULLETIN SUMMARY

**CONF ALL

LOWER SPAR
LOOKING OUTBOARD RIB1 RIB6 RIB7 RIB10

**FWD**

A_SB_540073_5_SAAA_01_00 

### B



## A

**B A** 

AREAS TO BE INSPECTED **NOTE:**

Figure A-FSAAA - Sheet 01

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 7 5

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# @A300 SERVICE BULLETIN SUMMARY

This Page Intentionally Left Blank

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# @A300 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: 54 

### TITLE: NACELLES/PYLON - INSPECT PYLON LOWER SPAR BETWEEN RIBS 6 AND 7 MODIFICATION No.: None This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or 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 NOTE: This Service Bulletin is only applicable to aircraft on which Mod. No. 10149S20315 is not embodied. (1) Models B2-1C B2-203 B2K-3C B4-103 B4-120 B4-203 B4-2C C4-203 F4-203 (2) Effectivity by MSN 0003 0041 0045 0047 0053 0055 0075 0079-0080 0082-0085 0090 0094-0095 0101 0105 0107 0116-0117 0123-0126 0128-0129 0133 0135-0137 0139 0141 0147 0149-0152 0154-0157 0160 0170 0173 0175-0176 0180 0183-0185 0187 0189 0199-0200 0203-0204 0210-0212 0218-0220 0226-0227 0234-0236 0239 0243-0244 0247 0249-0250 0255-0256 0259 0261 0265 0274 0277 0289 0292 0299 0302 0304

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 1 5

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# @A300 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 001 0125 50W 0003 69X 0095 72U 0079 ABR 0152 0184 0189 0199 0219 0220 0234 0236 0250 0259 0274 0289 AFG 0180 C2A 0261 DHL 0084 0085 0141 0149 0249 0265 F2I 0083 0094 0128 0133 0135 0136 0137 0156 0170 0235 0243 FLM 0082 0176 GST 0277 0292 IAW 0239 IRA 0080 0139 0151 0173 0185 0187 0226 0256 0299 0302 IRM 0055 0090 0160 0175 0204 0244 KYE 0053 0211 KZU 0041 0101 0117 MIX 0157 0203 0218 MNB 0123 0212 0304 MNG 0047 MSR 0200 0255 NTR 0124 0155 P2A 0116 0150 RUN 0075 0105 0107 0147 0154 0183 SOP 0126 TNO 0045 0210 0227 0247 TSY 0129 (4) Configuration by MSN MSN CONFIGURATION 0003 0160 0176 0185 0187 0226 0244 004 0041 0045 0047 0055 0084 0085 0105 0124 0151 002 0053 0075 0083 0095 0101 0107 0116 0117 0123 0126 0129 0137 0139 0141 0147 0149 0150 0152 003 0079 0094 0128 0133 0135 0136 0156 0170 007 0080 0082 0090 001 0125 0184 0189 0239 0256 005 0154 0155 0157 0173 0175 0180 0183 0199 0200 0203 0204 0210 0211 0212 0218 0219 0220 0227 0234 0235 0236 0243 0247 0249 0250 0255 0259 0261 0265 0274 0277 0289 0292 0299 0302 0304 006

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 2 5

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# @A300 SERVICE BULLETIN (5) Configuration definition **CONF 001 Config. 001 is valid for the models A300 B2-1C, B2-203 and B2K-3C equipped with the Basic Pylon and GE CF6-50 pylons. **CONF 002 Config. 002 is valid for the models A300 B4-2C, B4-103 and B4-120 equipped with the Basic Pylon and GE CF6-50 pylons. **CONF 003 Config. 003 is valid for the models A300 B4-203, B4-220, C4-203 and F4-203 equipped with the Basic Pylon and GE CF6-50 pylons. **CONF 004 Config. 004 is valid for the models A300 B2-1C, B2-203 and B2K-3C equipped with the General Electric engine and the Polyvalent Pylon. **CONF 005 Config. 005 is valid for the models A300 B4-2C, B4-103 and B4-120 equipped with the General Electric engine and the Polyvalent Pylon. **CONF 006 Config. 006 is valid for the models A300 B4-203, B4-220, C4-203 and F4-203 equipped with the General Electric engine and the Polyvalent Pylon. **CONF 007 Config. 007 is valid for the models A300 B4-2C, B4-103 and B4-120 equipped with the Pratt and Witney engine and the Polyvalent Pylon. (6) Material Effectivity **CONF 001 thru 003 MATERIAL QTY PER A/C SEE NOTES Kit 540073A01R03 2 Consumable CMLA01 1 NOTE: The kit No. 540073A01 is valid for one pylon. **CONF 004 thru 006 MATERIAL QTY PER A/C SEE NOTES Kit 540073A03R00 2 Consumable CMLA01 1 NOTE: The kit No. 540073A02 is valid for one pylon. **CONF 007 MATERIAL QTY PER A/C SEE NOTES Kit 540073A02R02 2 Consumable CMLA01 1 DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 3 5

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# @A300 SERVICE BULLETIN
NOTE: The kit No. 540073A03 is valid for one pylon. **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON (1) History On A/C fitted with GE pylon and PW, crack has been reported on pylon lower spar. The crack is running between ribs 6 and 7 and is starting on the center stiffener after the flat area. Some cracks have been reported re-initiating even after Service Bulletin embodiment. Hence a deeper investigation has been performed in order to propose the best solution possible to the operators. (2) Objective/Action The aim of this Service Bulletin is to call for Eddy Current Inspection or Liquid Penetrant Inspection of the pylon lower spar in order to detect any crack. (3) Advantages This inspection will make it possible to detect crack propagation at an early stage, thus avoiding a significant repair and reduction of the structural capacity. New FC/FH figures of Thresholds and Intervals, due to improvement of analyses and also consistent with in-service crack findings, were acknowledged by Airworthiness Authorities. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. (2) Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 4 5

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# @A300 SERVICE BULLETIN Task 540073-832-804-001: Inspection Post Repair (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. Task 540073-833-801-001: Repair (1) Install the doubler on the LH Pylon (2) Install the doubler on the RH Pylon **CONF 002 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. (2) Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. Task 540073-832-804-001: Inspection Post Repair (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. Task 540073-833-801-001: Repair (1) Install the doubler on the LH Pylon (2) Install the doubler on the RH Pylon **CONF 003 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. (2) Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. Task 540073-832-804-001: Inspection Post Repair (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 5 5

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# @A300 SERVICE BULLETIN Task 540073-833-801-001: Repair (1) Install the doubler on the LH Pylon (2) Install the doubler on the RH Pylon **CONF 004 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. (2) Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. Task 540073-832-804-001: Inspection Post Repair (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. Task 540073-833-801-001: Repair (1) Install the doubler on the LH Pylon (2) Install the doubler on the RH Pylon **CONF 005 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. (2) Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. Task 540073-832-804-001: Inspection Post Repair (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. Task 540073-833-801-001: Repair (1) Install the doubler on the LH Pylon (2) Install the doubler on the RH Pylon

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 6 5

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# @A300 SERVICE BULLETIN
**CONF 006 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. (2) Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. Task 540073-832-804-001: Inspection Post Repair (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. Task 540073-833-801-001: Repair (1) Install the doubler on the LH Pylon (2) Install the doubler on the RH Pylon **CONF 007 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. (2) Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. Task 540073-832-804-001: Inspection Post Repair (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 (1) Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. Task 540073-833-801-001: Repair (1) Install the doubler on the LH Pylon (2) Install the doubler on the RH Pylon **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 7 5

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# @A300 SERVICE BULLETIN (2) Accomplishment Timescale **CONF 001 This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. Compliance Time Condition Action Threshold Grace period Repetitive Interval Config . 001 Do a Special Detailed Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 10,900 FC None None

Do Re-Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 None None 6,700 FC

Or Apply the SB 54-0080 Before next flight None None And No crack found

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 (Task 540073-832-805-001) Refer to table 2

Crack found Do a special Detailed Inspection of the LH/RH Engine Pylon without the aluminium spray protection Refer to Subtask 540073-832-005-001 Before next flight None None

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 8 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Do Re-Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 None None 6,700 FC

Or Apply the SB 54-0080 Before next flight None None And No crack found (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 (Task 540073-832-805-001) Refer to table 2

Install the doubler on the LH and/or RH Pylon Refer to Subtask 540073-833-001-001 and/or Refer to Subtask 540073-833-002-001 (Task 540073-833-801-001) 500 FC None None

And Crack found =< 20 mm (0.787in.) (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001 (Task 540073-832-804-001) Refer to table 3

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 9 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Install the doubler on the LH and/or RH Pylon Refer to Subtask 540073-833-001-001 and/or Refer to Subtask 540073-833-002-001 (Task 540073-833-801-001) 250 FC None None

And Crack found between 20 mm (0.787in.) and 25 mm (0.984in.) (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001 (Task 540073-832-804-001) Refer to table 3

Crack found > 25 mm (0.984in.) (After embodiement of Subtask 540073-832-005-001) Contact AIRBUS Before next flight None None

Table 1, Special Detailed Inspection between RIB6 and RIB7 Pre-repair and Pre-SB 54-0080. Compliance Time Condition Action Threshold (FC or FH whichever occurs first) Grace period (FC or FH whichever occurs first) Repetitive Interval (FC or FH whichever occurs first) Conf . 001 SB 54-0080 is accomplished. Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 12,000 FC / 13,500 FH 500 FC see note (1) 1,000 FC see note (2) None

Crack found. Contact AIRBUS Before next flight None None No crack found Do Re-Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 None 500 FC see note (1) 1,000 FC see note (2) 7,600 FC / 8,600 FH

Table 2, Special Detailed Inspection between RIB6 and RIB7 Post SB 54-0080.

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# @A300 SERVICE BULLETIN

Compliance Time Condition Action Threshold (FC or FH whichever occurs first) Grace period (FC or FH whichever occurs first) Repetitive Interval (FC or FH whichever occurs first) Conf . 001 The Installation of the doubler on the LH / RH Pylon is accomplished. Do a Special Detailed Inspection of the LH /RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001. 5.200 FC / 5,900FH 500 FC see note (1) 1,000 FC see note (2) None

Crack found Contact AIRBUS Before next flight None None No crack found Do Re-Inspection of the LH /RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001. None 500 FC see note (1) 1,000 FC see note (2) 2,200 FC / 2,500 FH

Table 3, Special Detailed Inspection between RIB6 and RIB7 Post repair.
NOTE (1): For A300 GE basic pylon post SB 54-0080 with more than 31.700 FC from first flight: For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 500 FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this ISB. NOTE (2): Other Configurations of A300 GE basic pylon post SB 54-0080 or post repair: For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 1000 FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this ISB. **CONF 002 This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. Compliance Time Condition Action Threshold Grace period Repetitive Interval Config . 002 Do a Special Detailed Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 10,900 FC None None

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 11 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Do Re-Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 None None 6,700 FC

Or Apply the SB 54-0080 Before next flight None None And No crack found

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 (Task 540073-832-805-001) Refer to table 2

Crack found Do a special Detailed Inspection of the LH/RH Engine Pylon without the aluminium spray protection Refer to Subtask 540073-832-005-001 Before next flight None None

Do Re-Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 None None 6,700 FC

Or Apply the SB 54-0080 Before next flight None None And No crack found (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 (Task 540073-832-805-001) Refer to table 2

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 12 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Install the doubler on the LH and/or RH Pylon Refer to Subtask 540073-833-001-001 and/or Refer to Subtask 540073-833-002-001 (Task 540073-833-801-001) 500 FC None None

And Crack found =< 20 mm (0.787in.) (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001 (Task 540073-832-804-001) Refer to table 3

Install the doubler on the LH and/or RH Pylon Refer to Subtask 540073-833-001-001 and/or Refer to Subtask 540073-833-002-001 (Task 540073-833-801-001) 250 FC None None

And Crack found between 20 mm (0.787in.) and 25 mm (0.984in.) (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001 (Task 540073-832-804-001) Refer to table 3

Crack found > 25 mm (0.984in.) (After embodiement of Subtask 540073-832-005-001) Contact AIRBUS Before next flight None None

Table 1, Special Detailed Inspection between RIB6 and RIB7 Pre-repair and Pre-SB 54-0080.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 13 5

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# @A300 SERVICE BULLETIN

Compliance Time Condition Action Threshold (FC or FH whichever occurs first) Grace period (FC or FH whichever occurs first) Repetitive Interval (FC or FH whichever occurs first) Conf . 002 SB 54-0080 is accomplished. Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 12,000 FC / 16,300 FH 500 FC see note (1) 1,000 FC see note (2) None

Crack found. Contact AIRBUS Before next flight None None No crack found Do Re-Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 None 500 FC see note (1) 1,000 FC see note (2) 7,600 FC / 10,400 FH

Table 2, Special Detailed Inspection between RIB6 and RIB7 Post SB 54-0080. Compliance Time Condition Action Threshold (FC or FH whichever occurs first) Grace period (FC or FH whichever occurs first) Repetitive Interval (FC or FH whichever occurs first) Conf . 002 The Installation of the doubler on the LH / RH Pylon is accomplished. Do a Special Detailed Inspection of the LH /RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001 5,200 FC / 7,100 FH 500 FC see note (1) 1,000 FC see note (2) None

Crack found Contact AIRBUS Before next flight None None No crack found Do Re-Inspection of the LH /RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001 None 500 FC see note (1) 1,000 FC see note (2) 2,200 FC / 3.100 FH

Table 3, Special Detailed Inspection between RIB6 and RIB7 Post repair.
NOTE (1): For A300 GE basic pylon post SB 54-0080 with more than 31.700 FC from first flight: For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 500 FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this ISB. NOTE (2): Other Configurations of A300 GE basic pylon post SB 54-0080 or post repair:

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 14 5

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# @A300 SERVICE BULLETIN For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 1000 FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this ISB. **CONF 003 This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. Compliance Time Condition Action Threshold Grace period Repetitive Interval Config . 003 Do a Special Detailed Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 10,900 FC None None

Do Re-Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 None None 6,700 FC

Or Apply the SB 54-0080 Before next flight None None And No crack found

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 (Task 540073-832-805-001) Refer to table 2

Crack found Do a special Detailed Inspection of the LH/RH Engine Pylon without the aluminium spray protection Refer to Subtask 540073-832-005-001 Before next flight None None

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 15 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Do Re-Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 None None 6,700 FC

Or Apply the SB 54-0080 Before next flight None None And No crack found (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 (Task 540073-832-805-001) Refer to table 2

Install the doubler on the LH and/or RH Pylon Refer to Subtask 540073-833-001-001 and/or Refer to Subtask 540073-833-002-001 (Task 540073-833-801-001). 500 FC None None

And Crack found =< 20 mm (0.787in.) (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001 (Task 540073-832-805-001) Refer to table 3

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 16 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Install the doubler on the LH and/or RH Pylon Refer to Subtask 540073-833-001-001 and/or Refer to Subtask 540073-833-002-001 (Task 540073-833-801-001) 250 FC None None

And Crack found between 20 mm (0.787in.) and 25 mm (0.984in.) (After embodiement of Subtask 540073-832-005-001)

Do a Special Inspection of the LH/RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001 (Task 540073-832-805-001). Refer to table 3

Crack found > 25 mm (0.984in.) (After embodiement of Subtask 540073-832-005-001) Contact AIRBUS Before next flight None None

Table 1, Special Detailed Inspection between RIB6 and RIB7 Pre-repair and Pre-SB 54-0080. Compliance Time Condition Action Threshold (FC or FH whichever occurs first) Grace period (FC or FH whichever occurs first) Repetitive Interval (FC or FH whichever occurs first) SR: 12,000 FC / 26,500 FH Conf . 003 SB 54-0080 is accomplished. Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001. LR: 13,200 FC / 19,200 FH 500 FC see note (1) 1,000 FC see note (2) None

Crack found. Contact AIRBUS Before next flight None None SR: 7,600 FC / 16,900 FH No crack found Do Re-Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001. None 500 FC see note (1) 1,000 FC see note (2) LR: 8,400 FC / 12,200 FH Table 2, Special Detailed Inspection between RIB6 and RIB7 Post SB 54-0080.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 17 5

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# @A300 SERVICE BULLETIN

Compliance Time Condition Action Threshold (FC or FH whichever occurs first) Grace period (FC or FH whichever occurs first) Repetitive Interval (FC or FH whichever occurs first) SR: 5,200 FC / 11,600FH Conf . 003 The Installation of the doubler on the LH / RH Pylon is accomplished. Do a Special Detailed Inspection of the LH /RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001. LR: 5,800 FC / 8,400 FH 500 FC see note (1) 1,000 FC see note (2) None

Crack found Contact AIRBUS Before next flight None None SR: 2,200 FC / 5,000 FH No crack found Do Re-Inspection of the LH /RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001. None 500 FC see note (1) 1,000 FC see note (2) LR: 2,500 FC / 3,600 FH Table 3, Special Detailed Inspection between RIB6 and RIB7 Post repair.
NOTE: For Average Flight Time (AFT - limit between Short Range (SR) and Long Range (LR)) configuration refer to Airworthiness Limitation Item Documentation Section B. NOTE (1): For A300 GE basic pylon post SB 54-0080 with more than 31.700 FC from first flight: For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 500 FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this ISB. NOTE (2): Other Configurations of A300 GE basic pylon post SB 54-0080 or post repair: For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 1000 FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this ISB. **CONF 004 This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 18 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Config . 004 Do a Special Detailed Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 10,900 FC None None

Do Re-Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 None None 6,700 FC

Or Apply the SB 54-0080 Before next flight None None And No crack found

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 (Task 540073-832-805-001) Refer to table 2

Crack found Do a special Detailed Inspection of the LH/RH Engine Pylon without the aluminium spray protection Refer to Subtask 540073-832-005-001. Before next flight None None

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 19 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Do Re-Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 None None 6,700 FC

Or Apply the SB 54-0080 Before next flight None None And No crack found (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 (Task 540073-832-805-001) Refer to table 2

Install the doubler on the LH and/or RH Pylon Refer to Subtask 540073-833-001-001 and/or Refer to Subtask 540073-833-002-001 (Task 540073-833-801-001) 500 FC None None

And Crack found =< 30 mm (1.181in.) (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001 (Task 540073-832-804-001) Refer to table 3

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 20 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Install the doubler on the LH and/or RH Pylon Refer to Subtask 540073-833-001-001 and/or Refer to Subtask 540073-833-002-001 (Task 540073-833-801-001) 250 FC None None

And Crack found between 30 mm (1.181in.) and 35 mm (1.378in.) (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001 (Task 540073-832-804-001) Refer to table 3

Crack found > 35 mm (1.378in.) (After embodiement of Subtask 540073-832-005-001) Contact AIRBUS Before next flight None None

Table 1, Special Detailed Inspection between RIB6 and RIB7 Pre-repair and Pre-SB 54-0080. Compliance Time Condition Action Threshold (FC or FH whichever occurs first) Grace period (FC or FH whichever occurs first) Repetitive Interval (FC or FH whichever occurs first) Conf . 004 SB 54-0080 is accomplished. Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001. 12,200 FC / 13,800 FH 500 FC see note (1) 1,000 FC see note (2) None

Crack found. Contact AIRBUS Before next flight None None No crack found Do Re-Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001. None 500 FC see note (1) 1,000 FC see note (2) 7,200 FC / 8,200 FH

Table 2, Special Detailed Inspection between RIB6 and RIB7 Post SB 54-0080.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 21 5

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# @A300 SERVICE BULLETIN

Compliance Time Condition Action Threshold (FC or FH whichever occurs first) Grace period (FC or FH whichever occurs first) Repetitive Interval (FC or FH whichever occurs first) Conf . 004 The Installation of the doubler on the LH / RH Pylon is accomplished. Do a Special Detailed Inspection of the LH /RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001. 6,000 FC / 6,800FH 500 FC see note (1) 1,000 FC see note (2) None

Crack found Contact AIRBUS Before next flight None None No crack found Do Re-Inspection of the LH /RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001. None 500 FC see note (1) 1,000 FC see note (2) 3,100 FC / 3,500 FH

Table 3, Special Detailed Inspection between RIB6 and RIB7 Post repair.
NOTE (1): For repaired A300 GE polyvalent pylon with more than 33.100 FC from repair embodiment: For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 500 FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this ISB. NOTE (2): Other Configurations of A300 GE basic pylon post SB 54-0080 or post repair: For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 1000 FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this ISB. **CONF 005 This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. Compliance Time Condition Action Threshold Grace period Repetitive Interval Config . 005 Do a Special Detailed Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 10,900 FC None None

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 22 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Do Re-Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 None None 6,700 FC

Or Apply the SB 54-0080 Before next flight None None And No crack found

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 (Task 540073-832-805-001) Refer to table 2

Crack found Do a special Detailed Inspection of the LH/RH Engine Pylon without the aluminium spray protection Refer to Subtask 540073-832-005-001 Before next flight None None

Do Re-Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 None None 6,700 FC

Or Apply the SB 54-0080 Before next flight None None And No crack found (After embodiement of Subtask 540073-832-005-001)

Do a Special Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 (Task 540073-832-805-001) Refer to table 2

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 23 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Install the doubler on the LH and/or RH Pylon Refer to Subtask 540073-833-001-001 and/or Refer to Subtask 540073-833-002-001 (Task 540073-833-801-001) 500 FC None None

And Crack found =< 30 mm (1.181in.) (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001 (Task 540073-832-804-001) Refer to table 3

Install the doubler on the LH and/or RH Pylon Refer to Subtask 540073-833-001-001 and/or Refer to Subtask 540073-833-002-001 (Task 540073-833-801-001) 250 FC None None

And Crack found between 30 mm (1.181in.) and 35 mm (1.378in.) (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001 (Task 540073-832-804-001) Refer to table 3

Crack found > 35 mm (1.378in.) (After embodiement of Subtask 540073-832-005-001) Contact AIRBUS Before next flight None None

Table 1, Special Detailed Inspection between RIB6 and RIB7 Pre-repair and Pre-SB 54-0080.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 24 5

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# @A300 SERVICE BULLETIN

Compliance Time Condition Action Threshold (FC or FH whichever occurs first) Grace period (FC or FH whichever occurs first) Repetitive Interval (FC or FH whichever occurs first) Conf . 005 SB 54-0080 is accomplished. Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 12,200 FC / 16,700 FH 500 FC see note (1) 1,000 FC see note (2) None

Crack found. Contact AIRBUS Before next flight None None No crack found Do Re-Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 None 500 FC see note (1) 1,000 FC see note (2) 7,200 FC / 9,800 FH

Table 2, Special Detailed Inspection between RIB6 and RIB7 Post SB 54-0080. Compliance Time Condition Action Threshold (FC or FH whichever occurs first) Grace period (FC or FH whichever occurs first) Repetitive Interval (FC or FH whichever occurs first) Conf . 005 The Installation of the doubler on the LH / RH Pylon is accomplished. Do a Special Detailed Inspection of the LH /RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001 6,000 FC / 8,200FH 500 FC see note (1) 1,000 FC see note (2) None

Crack found Contact AIRBUS Before next flight None None No crack found Do Re-Inspection of the LH /RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001 None 500 FC see note (1) 1,000 FC see note (2) 3,100 FC / 4,200 FH

Table 3, Special Detailed Inspection between RIB6 and RIB7 Post repair.
NOTE (1): For repaired A300 GE polyvalent pylon with more than 33.100 FC from repair embodiment: For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 500 FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this ISB. NOTE (2): Other Configurations of A300 GE basic pylon post SB 54-0080 or post repair:

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 25 5

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# @A300 SERVICE BULLETIN For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 1000 FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this ISB. **CONF 006 This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. Compliance Time Condition Action Threshold Grace period Repetitive Interval Config . 006 Do a Special Detailed Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 10,900 FC None None

Do Re-Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 None None 6,700 FC

Or Apply the SB 54-0080 Before next flight None None And No crack found

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 (Task 540073-832-805-001) Refer to table 2

Crack found Do a special Detailed Inspection of the LH/RH Engine Pylon without the aluminium spray protection Refer to Subtask 540073-832-005-001. Before next flight None None

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 26 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Do Re-Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 None None 6,700 FC

Or Apply the SB 54-0080 Before next flight None None And No crack found (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001. Refer to table 2

Install the doubler on the LH and/or RH Pylon Refer to Subtask 540073-833-001-001 and/or Refer to Subtask 540073-833-002-001 (Task 540073-833-801-001) 500 FC None None

And Crack found =< 30 mm (1.181in.) (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001. Refer to table 3

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 27 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Install the doubler on the LH and/or RH Pylon Refer to Subtask 540073-833-001-001 and/or Refer to Subtask 540073-833-002-001 (Task 540073-833-801-001) 250 FC None None

And Crack found between 30 mm (1.181in.) and 35 mm (1.378in.) (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001. Refer to table 3

Crack found > 35 mm (1.378in.) (After embodiement of Subtask 540073-832-005-001) Contact AIRBUS Before next flight None None

Table 1, Special Detailed Inspection between RIB6 and RIB7 Pre-repair and Pre-SB 54-0080. Compliance Time Condition Action Threshold (FC or FH whichever occurs first) Grace period (FC or FH whichever occurs first) Repetitive Interval (FC or FH whichever occurs first) SR: 12,200 FC / 27,100 FH Conf . 006 SB 54-0080 is accomplished. Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001. LR: 13,500 FC / 19,600 FH 500 FC see note (1) 1,000 FC see note (2) None

Crack found. Contact AIRBUS Before next flight None None SR: 7,200 FC / 16,000 FH No crack found Do Re-Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001. None 500 FC see note (1) 1,000 FC see note (2) LR: 7,900 FC / 11,600 FH Table 2, Special Detailed Inspection between RIB6 and RIB7 Post SB 54-0080.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 28 5

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# @A300 SERVICE BULLETIN

Compliance Time Condition Action Threshold (FC or FH whichever occurs first) Grace period (FC or FH whichever occurs first) Repetitive Interval (FC or FH whichever occurs first) SR: 6,000 FC / 13,400FH Conf . 006 The Installation of the doubler on the LH / RH Pylon is accomplished. Do a Special Detailed Inspection of the LH /RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001. LR: 6,600 FC / 9,700 FH 500 FC see note (1) 1,000 FC see note (2) None

Crack found Contact AIRBUS Before next flight None None SR: 3,100 FC / 6,900 FH No crack found Do Re-Inspection of the LH /RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001. None 500 FC see note (1) 1,000 FC see note (2) LR: 3,400 FC / 5,000 FH Table 3, Special Detailed Inspection between RIB6 and RIB7 Post repair.
NOTE: For Average Flight Time (AFT - limit between Short Range (SR) and Long Range (LR)) configuration refer to Airworthiness Limitation Item Documentation Section B. NOTE (1): For repaired A300 GE polyvalent pylon with more than 33.100 FC from repair embodiment: For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 500 FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this ISB. NOTE (2): Other Configurations of A300 GE basic pylon post SB 54-0080 or post repair: For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 1000 FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this ISB. **CONF 007 This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 29 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Config . 007 Do a Special Detailed Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 8,600 FC None None

Do Re-Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 None None 5,700 FC

Or Apply the SB 54-0080 Before next flight None None And No crack found

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 (Task 540073-832-805-001) Refer to table 2

Crack found Do a special Detailed Inspection of the LH/RH Engine Pylon without the aluminium spray protection Refer to Subtask 540073-832-005-001 Before next flight None None

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 30 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Do Re-Inspection of the LH/RH Engine Pylon Pre-repair and Pre-SB 54-0080 Refer to Subtask 540073-832-001-001 None None 5,700 FC

Or Apply the SB 54-0080 Before next flight None None And No crack found (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001 (Task 540073-832-805-001) Refer to table 2

Install the doubler on the LH and/or RH Pylon Refer to Subtask 540073-833-001-001 and/or Refer to Subtask 540073-833-002-001 (Task 540073-833-801-001) 500 FC None None

And Crack found =< 30 mm (1.181in.) (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001. Refer to table 3

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 31 5

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# @A300 SERVICE BULLETIN
Compliance Time Condition Action Threshold Grace period Repetitive Interval Install the doubler on the LH and/or RH Pylon Refer to Subtask 540073-833-001-001 and/or Refer to Subtask 540073-833-002-001 (Task 540073-833-801-001) 250 FC None None

And Crack found between 30 mm (1.181in.) and 35 mm (1.378in.) (After embodiement of Subtask 540073-832-005-001)

Do a Special Detailed Inspection of the LH/RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001 Refer to table 3

Crack found > 35 mm (1.378in.) (After embodiement of Subtask 540073-832-005-001) Contact AIRBUS Before next flight None None

Table 1, Special Detailed Inspection between RIB6 and RIB7 Pre-repair and Pre-SB 54-0080. Compliance Time Condition Action Threshold (FC or FH whichever occurs first) Grace period (FC or FH whichever occurs first) Repetitive Interval (FC or FH whichever occurs first) Conf . 007 SB 54-0080 is accomplished. Do a Special Detailed Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001. 13,000 FC / 17,800 FH 500 FC see note (1) 1,000 FC see note (2) None

Crack found. Contact AIRBUS Before next flight None None No crack found Do Re-Inspection of the LH/RH Engine Pylon Post SB 54-0080 Refer to Subtask 540073-832-009-001. None 500 FC see note (1) 1,000 FC see note (2) 7,700 FC / 10,500 FH

Table 2, Special Detailed Inspection between RIB6 and RIB7 Post SB 54-0080.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 32 5

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# @A300 SERVICE BULLETIN

Compliance Time Condition Action Threshold (FC or FH whichever occurs first) Grace period (FC or FH whichever occurs first) Repetitive Interval (FC or FH whichever occurs first) Conf . 007 The Installation of the doubler on the LH / RH Pylon is accomplished. Do a Special Detailed Inspection of the LH /RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001. 6,400 FC / 8,700 FH 500 FC see note (1) 1,000 FC see note (2) None

Crack found Contact AIRBUS Before next flight None None No crack found Do Re-Inspection of the LH /RH Engine Pylon Post repair Refer to Subtask 540073-832-008-001. None 500 FC see note (1) 1,000 FC see note (2) 3,300 FC / 4,500 FH

Table 3, Special Detailed Inspection between RIB6 and RIB7 Post repair.
NOTE (1): For repaired A300 PW polyvalent pylon with more than 33.100 FC from repair embodiment: For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 500 FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this ISB. NOTE (2): Other Configurations of A300 GE basic pylon post SB 54-0080 or post repair: For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 1000 FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this ISB. **CONF ALL F. APPROVAL The technical content of this document is approved under the authority of 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: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 33 5

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# @A300 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. **CONF 001 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. 1.00 Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. 2.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 NOTE: These values are valid only for one pylon. Task 540073-832-804-001: Inspection Post Repair Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. 1.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 NOTE: These values are valid only for one pylon. Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. 1.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 NOTE: These values are valid only for one pylon.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 34 5

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# @A300 SERVICE BULLETIN
Task 540073-833-801-001: Repair Get Access 17.50 On Aircraft Install the doubler on the LH Pylon 7.50 Install the doubler on the RH Pylon 7.50 Tests 5.00 Close-Up 23.00 TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 NOTE: These values are valid only for one pylon. **CONF 002 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. 1.00 Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. 2.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 NOTE: These values are valid only for one pylon. Task 540073-832-804-001: Inspection Post Repair Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. 1.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 NOTE: These values are valid only for one pylon. Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. 1.00 Tests 1.00 Close-Up 1.50
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 35 5

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# @A300 SERVICE BULLETIN
Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 NOTE: These values are valid only for one pylon. Task 540073-833-801-001: Repair Get Access 17.50 On Aircraft Install the doubler on the LH Pylon 7.50 Install the doubler on the RH Pylon 7.50 Tests 5.00 Close-Up 23.00 TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 NOTE: These values are valid only for one pylon. **CONF 003 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. 1.00 Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. 2.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 NOTE: These values are valid only for one pylon. Task 540073-832-804-001: Inspection Post Repair Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. 1.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 NOTE: These values are valid only for one pylon. Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 Get Access 1.50 DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 36 5

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# @A300 SERVICE BULLETIN
Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. 1.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 NOTE: These values are valid only for one pylon. Task 540073-833-801-001: Repair Get Access 17.50 On Aircraft Install the doubler on the LH Pylon 7.50 Install the doubler on the RH Pylon 7.50 Tests 5.00 Close-Up 23.00 TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 NOTE: These values are valid only for one pylon. **CONF 004 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. 1.00 Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. 2.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 NOTE: These values are valid only for one pylon. Task 540073-832-804-001: Inspection Post Repair Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. 1.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 5.00
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 37 5

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# @A300 SERVICE BULLETIN
Task 540073-832-804-001: Inspection Post Repair ELAPSED TIME (HOURS) 5.00 NOTE: These values are valid only for one pylon. Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. 1.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 NOTE: These values are valid only for one pylon. Task 540073-833-801-001: Repair Get Access 17.50 On Aircraft Install the doubler on the LH Pylon 7.50 Install the doubler on the RH Pylon 7.50 Tests 5.00 Close-Up 23.00 TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 NOTE: These values are valid only for one pylon. **CONF 005 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. 1.00 Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. 2.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 NOTE: These values are valid only for one pylon. Task 540073-832-804-001: Inspection Post Repair Get Access 1.50 On Aircraft DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 38 5

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# @A300 SERVICE BULLETIN
Task 540073-832-804-001: Inspection Post Repair Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. 1.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 NOTE: These values are valid only for one pylon. Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. 1.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 NOTE: These values are valid only for one pylon. Task 540073-833-801-001: Repair Get Access 17.50 On Aircraft Install the doubler on the LH Pylon 7.50 Install the doubler on the RH Pylon 7.50 Tests 5.00 Close-Up 23.00 TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 NOTE: These values are valid only for one pylon. **CONF 006 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. 1.00 Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. 2.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 39 5

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# @A300 SERVICE BULLETIN
NOTE: These values are valid only for one pylon. Task 540073-832-804-001: Inspection Post Repair Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. 1.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 NOTE: These values are valid only for one pylon. Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. 1.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 NOTE: These values are valid only for one pylon. Task 540073-833-801-001: Repair Get Access 17.50 On Aircraft Install the doubler on the LH Pylon 7.50 Install the doubler on the RH Pylon 7.50 Tests 5.00 Close-Up 23.00 TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 NOTE: These values are valid only for one pylon. **CONF 007 Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. 1.00 Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. 2.00 Tests 1.00 DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 40 5

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# @A300 SERVICE BULLETIN
Task 540073-832-801-001: Inspection Pre Repair and Pre Service Bulletin No.A300-54-0080 Close-Up 1.50 TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 NOTE: These values are valid only for one pylon. Task 540073-832-804-001: Inspection Post Repair Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. 1.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 NOTE: These values are valid only for one pylon. Task 540073-832-805-001: Inspection Post Service Bulletin No.A300-54-0080 Get Access 1.50 On Aircraft Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. 1.00 Tests 1.00 Close-Up 1.50 TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 NOTE: These values are valid only for one pylon. Task 540073-833-801-001: Repair Get Access 17.50 On Aircraft Install the doubler on the LH Pylon 7.50 Install the doubler on the RH Pylon 7.50 Tests 5.00 Close-Up 23.00 TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 NOTE: These values are valid only for one pylon.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 41 5

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# @A300 SERVICE BULLETIN
**CONF ALL H. WEIGHT AND BALANCE NOTE: If repaired: Manufacturers Empty Weight +2.00 KG (+4.4092 LB) Effect on Balance +55.22 KGM (+399.406 LB.FT ) I. ELECTRICAL LOAD DATA None J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-21-00 06-21-54 24-00-00 24-41-00 36-00-00 36-11-00 36-11-15 53-00-00 54-11-15 71-00-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-31-11 51-32-03 51-33-02 51-34-04 54-40-11 Service Bulletin (SB) A300-54-0080 Standards Manual (SM) Structural Repair Manual (SRM) 51-30-38 51-30-43 51-40-12 51-40-18 51-73-11 **CONF 002 Aircraft Maintenance Manual (AMM) 06-21-00 06-21-54 24-00-00 24-41-00 36-00-00 36-11-00 36-11-15 53-00-00 54-11-15 71-00-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-31-11 51-32-03 51-33-02 51-34-04 54-40-11 Service Bulletin (SB) A300-54-0080 Standards Manual (SM) Structural Repair Manual (SRM) 51-30-38 51-30-43 51-40-12 51-40-18 51-73-11 **CONF 003 Aircraft Maintenance Manual (AMM) 06-21-00 06-21-54 24-00-00 24-41-00 36-00-00 36-11-00 36-11-15 53-00-00 54-11-15 71-00-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-31-11 51-32-03 51-33-02 51-34-04 54-40-11 Service Bulletin (SB) A300-54-0080 DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 42 5

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# @A300 SERVICE BULLETIN
Standards Manual (SM) Structural Repair Manual (SRM) 51-30-38 51-30-43 51-40-12 51-40-18 51-73-11 **CONF 004 Aircraft Maintenance Manual (AMM) 06-21-00 06-21-54 24-00-00 24-41-00 36-00-00 36-11-00 36-11-15 53-00-00 54-11-15 71-00-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-31-11 51-32-03 51-33-02 51-34-04 54-40-11 Service Bulletin (SB) A300-54-0080 Standards Manual (SM) Structural Repair Manual (SRM) 51-30-38 51-30-43 51-40-12 51-40-18 51-73-11 **CONF 005 Aircraft Maintenance Manual (AMM) 06-21-00 06-21-54 24-00-00 24-41-00 36-00-00 36-11-00 36-11-15 53-00-00 54-11-15 71-00-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-31-11 51-32-03 51-33-02 51-34-04 54-40-11 Service Bulletin (SB) A300-54-0080 Standards Manual (SM) Structural Repair Manual (SRM) 51-30-38 51-30-43 51-40-12 51-40-18 51-73-11 **CONF 006 Aircraft Maintenance Manual (AMM) 06-21-00 06-21-54 24-00-00 24-41-00 36-00-00 36-11-00 36-11-15 53-00-00 54-11-15 71-00-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-31-11 51-32-03 51-33-02 51-34-04 54-40-11 Service Bulletin (SB) A300-54-0080 Standards Manual (SM) Structural Repair Manual (SRM) 51-30-38 51-30-43 51-40-12 51-40-18 51-73-11 **CONF 007 Aircraft Maintenance Manual (AMM) 06-21-00 06-21-54 24-00-00 24-41-00 36-00-00 36-11-00 36-11-15 53-00-00 54-11-15 71-00-00 Elec. Std. Practices Manual (ESPM) 20-55-00 DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 43 5

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# @A300 SERVICE BULLETIN
Non Destructive Test Manual (NTM) 51-31-11 51-32-03 51-33-02 51-34-04 54-40-11 Service Bulletin (SB) A300-54-0080 Standards Manual (SM) Structural Repair Manual (SRM) 51-30-38 51-30-43 51-40-12 51-40-18 51-73-11 **CONF ALL K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 541107-0603-1 541107-0603-2 541107-0603-3 541107-0603-4 541107-0603-5 541107-0603-6 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 44 5

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# @A300 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Kit 540073A01R03 Kit 540073A02R02 Kit 540073A03R00 Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is: AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 2590 For ordering by E-mail: airbus.kit@airbus.com (2) Price and Availability

Kit 540073A01R03 Cost 1,440.00 USD Availability 120 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 540073A02R02 Cost 1,420.00 USD Availability 120 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 540073A03R00 Cost 1,440.00 USD Availability 120 calendar days from receipt of order

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 45 5

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# @A300 SERVICE BULLETIN The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS Kit 540073A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 54 NUT 3 NSA5414-32-18 10 RIVET (3) NSA5415-32 4 NAS1149CN832R 12 WASHER 5 MS21043-08 6 NUT 6 NAS1152E3 6 BOLT 8 NAS1153E4 42 BOLT 9 NAS1153E7 12 BOLT (7) NSA5415-40 NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Kit 540073A02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 60 NUT 3 NSA5414-32-18 10 RIVET (3) NSA5415-32 10 NAS6703U3 6 BOLT 11 NAS6703U4 42 BOLT 12 NAS6703U6 12 BOLT 13 NAS6703U8 9 BOLT (13) NSA6703U6 14 NAS6703U10 9 BOLT (14) NSA6703U8 15 NAS1149C0363R 9 WASHER (15) AN960C8 NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 46 5

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# @A300 SERVICE BULLETIN
Kit 540073A03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 54 NUT 3 NSA5414-32-18 10 RIVET (3) NSA5415-32 4 NAS1149CN832R 12 WASHER 5 MS21043-08 6 NUT 6 NAS1152E3 6 BOLT 7 NAS1153E6 12 BOLT (7) NSA5415-40 8 NAS1153E4 42 BOLT NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability To accomplish this Service Bulletin, it is necessary to use the following tools and equipment. Equipment and material for control by Eddy Current as per NTM 54-40-11 Part 6. Equipment and material for Liquid Penetrant as per NTM 54-40-11 Part 9.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 47 5

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# @A300 SERVICE BULLETIN Equipment and materials for the check of the holes as per NTM 51-31-11 Part 1 - procedure A with calibration standard PN 99A53003001108 as per NTM 51-34-04 Part 1. Supplier: AIRBUS WEG BEIM JAEGER 150 D - 22453 HAMBURG GERMANY Tel. : 49.(0)40/5076 - 0 Fax. : 49.(0)40/503168 (2) Tools None (3) Special Tools None

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 48 5

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# @A300 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 540073-832-801-001 - Inspection Pre Repairand Pre Service Bulletin No.A300-54-0080 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. IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00. NOTE: The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin. Task Associated Data **CONF 001 Zone 410 420 Manpower TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 **CONF 002 Zone 410 420 Manpower TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 **CONF 003 Zone 410 420
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 49 5

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# @A300 SERVICE BULLETIN
Manpower TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 **CONF 004 Zone 410 420 Manpower TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 **CONF 005 Zone 410 420 Manpower TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 **CONF 006 Zone 410 420 Manpower TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 **CONF 007 Zone 410 420 Manpower TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 7.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 540073-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 50 5

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# @A300 SERVICE BULLETIN
Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 540073-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 51 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 003 (1) Subtask 540073-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001).
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 52 5

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# @A300 SERVICE BULLETIN (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 004 (1) Subtask 540073-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12).
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 53 5

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# @A300 SERVICE BULLETIN (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 005 (1) Subtask 540073-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 54 5

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# @A300 SERVICE BULLETIN (2) Subtask 540073-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 006 (1) Subtask 540073-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 55 5

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# @A300 SERVICE BULLETIN
**CONF 007 (1) Subtask 540073-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 56 5

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# @A300 SERVICE BULLETIN
**CONF ALL B. PREPARATION **CONF 001 (1) Subtask 540073-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-001-001 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). **CONF 002 (1) Subtask 540073-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 57 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-001-001 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). **CONF 003 (1) Subtask 540073-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 58 5

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# @A300 SERVICE BULLETIN (2) Subtask 540073-010-001-001 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). **CONF 004 (1) Subtask 540073-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-001-002 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 59 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). **CONF 005 (1) Subtask 540073-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-001-002 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401).
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 60 5

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# @A300 SERVICE BULLETIN (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). **CONF 006 (1) Subtask 540073-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-001-002 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 61 5

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# @A300 SERVICE BULLETIN
**CONF 007 (1) Subtask 540073-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-001-002 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 62 5

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# @A300 SERVICE BULLETIN
**CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 540073-832-001-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Service Bulletin (SB) A300-54-0080 Fig. A-FBAAA Areas to Be Inspected Pre Repair and Pre SB 54-0080 Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2): Refer to Fig. A-FFAAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBAAA Sheet 01 1 If crack is found: - Refer to SUBTASK 540073-832-005 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection.

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# @A300 SERVICE BULLETIN

2 If no crack is found:
a Re-inspect the area as described in SUBTASK 540073-832-001 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. following the interval given in the Planning Information Paragraph E.(2).
or Accomplish Service Bulletin No. A300-54-0080 and apply the SUBTASK 540073-832-009 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. following the threshold given in the Planning Information Paragraph E.(2). b Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report (2) Subtask 540073-832-005-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Service Bulletin (SB) A300-54-0080 Structural Repair Manual (SRM) 51-40-12 51-40-18 51-73-11 Fig. A-FBAAA Areas to Be Inspected Pre Repair and Pre SB 54-0080 Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01
Refer to Fig. A-FFAAA Sheet 01 (a) Smooth blend out the area to remove the aluminium spray protection or cadmium plating protection 0.17 mm (0.007 in.) (Refer to SRM 51-73-11).

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# @A300 SERVICE BULLETIN (b) From the inside, on left and right pylon, do an Eddy Current re-Inspection (Refer to NTM 54-40-11 Part 6) and Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBAAA Sheet 01 1 If crack is found =< 20 mm (0.787 in.):
a Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report b Repair before 500 FC, Refer to SUBTASK 540073-833-001 001 Install the doubler on the LH Pylon and/or SUBTASK 540073-833-002 001 Install the doubler on the RH Pylon and SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.
c Re-protect the area by pad cadmium plating (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). 2 If crack is found between 20 mm (0.787 in.) and 25 mm (0.984 in.):
a Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report b Repair before 250 FC, Refer to SUBTASK 540073-833-001 001 Install the doubler on the LH Pylon and/or SUBTASK 540073-833-002 001 Install the doubler on the RH Pylon and SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.
c Re-protect the area by pad cadmium plating (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). 3 If crack is found > 25 mm (0.984 in.): - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 4 If no crack is found:
a Re-protect the area by pad cadmium plating (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). b Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report

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# @A300 SERVICE BULLETIN

c Re-inspect the area as described in SUBTASK 540073-832-001 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. following the interval given in the Planning Information Paragraph E.(2).
or Accomplish Service Bulletin No. A300-54-0080 and apply the SUBTASK 540073-832-009 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. following the threshold given in the Planning Information Paragraph E.(2). **CONF 002 (1) Subtask 540073-832-001-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Service Bulletin (SB) A300-54-0080 Fig. A-FBAAA Areas to Be Inspected Pre Repair and Pre SB 54-0080 Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2): Refer to Fig. A-FFAAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBAAA Sheet 01

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# @A300 SERVICE BULLETIN

1 If crack is found: - Refer to SUBTASK 540073-832-005 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. 2 If no crack is found:
a Re-inspect the area as described in SUBTASK 540073-832-001 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. following the interval given in the Planning Information Paragraph E.(2).
or Accomplish Service Bulletin No. A300-54-0080 and apply the SUBTASK 540073-832-009 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. following the threshold given in the Planning Information Paragraph E.(2). b Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report (2) Subtask 540073-832-005-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Service Bulletin (SB) A300-54-0080 Structural Repair Manual (SRM) 51-40-12 51-40-18 51-73-11 Fig. A-FBAAA Areas to Be Inspected Pre Repair and Pre SB 54-0080 Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01
Refer to Fig. A-FFAAA Sheet 01
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 67 5

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

# @A300 SERVICE BULLETIN (a) Smooth blend out the area to remove the aluminium spray protection or cadmium plating protection 0.17 mm (0.007 in.) (Refer to SRM 51-73-11). (b) From the inside, on left and right pylon, do an Eddy Current re-Inspection (Refer to NTM 54-40-11 Part 6) and Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBAAA Sheet 01 1 If crack is found =< 20 mm (0.787 in.):
a Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report b Repair before 500 FC, Refer to SUBTASK 540073-833-001 001 Install the doubler on the LH Pylon and/or SUBTASK 540073-833-002 001 Install the doubler on the RH Pylon and SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.
c Re-protect the area by pad cadmium plating (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). 2 If crack is found between 20 mm (0.787 in.) and 25 mm (0.984 in.):
a Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report b Repair before 250 FC, Refer to SUBTASK 540073-833-001 001 Install the doubler on the LH Pylon and/or SUBTASK 540073-833-002 001 Install the doubler on the RH Pylon and SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.
c Re-protect the area by pad cadmium plating (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). 3 If crack is found > 25 mm (0.984 in.): - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 4 If no crack is found:
a Re-protect the area by pad cadmium plating (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). b Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 68 5

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

# @A300 SERVICE BULLETIN

c Re-inspect the area as described in SUBTASK 540073-832-001 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. following the interval given in the Planning Information Paragraph E.(2).
or Accomplish Service Bulletin No. A300-54-0080 and apply the SUBTASK 540073-832-009 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. following the threshold given in the Planning Information Paragraph E.(2). **CONF 003 (1) Subtask 540073-832-001-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Service Bulletin (SB) A300-54-0080 Fig. A-FBAAA Areas to Be Inspected Pre Repair and Pre SB 54-0080 Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2): Refer to Fig. A-FFAAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBAAA Sheet 01

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 69 5

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

# @A300 SERVICE BULLETIN

1 If crack is found: - Refer to SUBTASK 540073-832-005 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. 2 If no crack is found:
a Re-inspect the area as described in SUBTASK 540073-832-001 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. following the interval given in the Planning Information Paragraph E.(2).
or Accomplish Service Bulletin No. A300-54-0080 and apply the SUBTASK 540073-832-009 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. following the threshold given in the Planning Information Paragraph E.(2). b Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report (2) Subtask 540073-832-005-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Service Bulletin (SB) A300-54-0080 Structural Repair Manual (SRM) 51-40-12 51-40-18 51-73-11 Fig. A-FBAAA Areas to Be Inspected Pre Repair and Pre SB 54-0080 Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01
Refer to Fig. A-FFAAA Sheet 01
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 70 5

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

# @A300 SERVICE BULLETIN (a) Smooth blend out the area to remove the aluminium spray protection or cadmium plating protection 0.17 mm (0.007 in.) (Refer to SRM 51-73-11). (b) From the inside, on left and right pylon, do an Eddy Current re-Inspection (Refer to NTM 54-40-11 Part 6) and Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBAAA Sheet 01 1 If crack is found =< 20 mm (0.787 in.):
a Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report b Repair before 500 FC, Refer to SUBTASK 540073-833-001 001 Install the doubler on the LH Pylon and/or SUBTASK 540073-833-002 001 Install the doubler on the RH Pylon and SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.
c Re-protect the area by pad cadmium plating (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). 2 If crack is found between 20 mm (0.787 in.) and 25 mm (0.984 in.):
a Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report b Repair before 250 FC, Refer to SUBTASK 540073-833-001 001 Install the doubler on the LH Pylon and/or SUBTASK 540073-833-002 001 Install the doubler on the RH Pylon and SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.
c Re-protect the area by pad cadmium plating (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). 3 If crack is found > 25 mm (0.984 in.): - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 4 If no crack is found:
a Re-protect the area by pad cadmium plating (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). b Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 71 5

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

# @A300 SERVICE BULLETIN

c Re-inspect the area as described in SUBTASK 540073-832-001 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. following the interval given in the Planning Information Paragraph E.(2).
or Accomplish Service Bulletin No. A300-54-0080 and apply the SUBTASK 540073-832-009 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. following the threshold given in the Planning Information Paragraph E.(2). **CONF 004 (1) Subtask 540073-832-001-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Service Bulletin (SB) A300-54-0080 Fig. A-FBAAA Areas to Be Inspected Pre Repair and Pre SB 54-0080 Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2): Refer to Fig. A-FFBAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBAAA Sheet 01

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 72 5

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

# @A300 SERVICE BULLETIN

1 If crack is found: - Refer to SUBTASK 540073-832-005 002 Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. 2 If no crack is found:
a Re-inspect the area as described in SUBTASK 540073-832-001 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. following the interval given in the Planning Information Paragraph E.(2).
or Accomplish Service Bulletin No. A300-54-0080 and apply the SUBTASK 540073-832-009 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. following the threshold given in the Planning Information Paragraph E.(2). b Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report (2) Subtask 540073-832-005-002 - Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Service Bulletin (SB) A300-54-0080 Structural Repair Manual (SRM) 51-40-12 51-40-18 51-73-11 Fig. A-FBAAA Areas to Be Inspected Pre Repair and Pre SB 54-0080 Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01
Refer to Fig. A-FFBAA Sheet 01
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 73 5

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

# @A300 SERVICE BULLETIN (a) Smooth blend out the area to remove the aluminium spray protection or cadmium plating protection 0.17 mm (0.007 in.) (Refer to SRM 51-73-11). (b) From the inside, on left and right pylon, do an Eddy Current re-Inspection (Refer to NTM 54-40-11 Part 6) and Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBAAA Sheet 01 1 If crack is found =< 30 mm (1.181 in.):
a Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report b Repair before 500 FC, Refer to SUBTASK 540073-833-001 003 Install the doubler on the LH Pylon and/or SUBTASK 540073-833-002 002 Install the doubler on the RH Pylon and SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.
c Re-protect the area by pad cadmium plating Refer to (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). 2 If crack is found between 30 mm (1.181 in.) and 35 mm (1.378 in.):
a Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report b Repair before 250 FC, Refer to SUBTASK 540073-833-001 003 Install the doubler on the LH Pylon and/or SUBTASK 540073-833-002 002 Install the doubler on the RH Pylon and SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.
c Re-protect the area by pad cadmium plating Refer to (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). 3 If crack is found > 35 mm (1.378 in.): - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 4 If no crack is found:
a Re-protect the area by pad cadmium plating Refer to (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). b Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 74 5

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

# @A300 SERVICE BULLETIN

c Re-inspect the area as described in SUBTASK 540073-832-001 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. following the interval given in the Planning Information Paragraph E.(2).
or Accomplish Service Bulletin No. A300-54-0080 and apply the SUBTASK 540073-832-009 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. following the threshold given in the Planning Information Paragraph E.(2). **CONF 005 (1) Subtask 540073-832-001-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Service Bulletin (SB) A300-54-0080 Fig. A-FBAAA Areas to Be Inspected Pre Repair and Pre SB 54-0080 Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2): Refer to Fig. A-FFBAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBAAA Sheet 01

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 75 5

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

# @A300 SERVICE BULLETIN

1 If crack is found: - Refer to SUBTASK 540073-832-005 002 Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. 2 If no crack is found:
a Re-inspect the area as described in SUBTASK 540073-832-001 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. following the interval given in the Planning Information Paragraph E.(2).
or Accomplish Service Bulletin No. A300-54-0080 and apply the SUBTASK 540073-832-009 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. following the threshold given in the Planning Information Paragraph E.(2). b Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report (2) Subtask 540073-832-005-002 - Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Service Bulletin (SB) A300-54-0080 Structural Repair Manual (SRM) 51-40-12 51-40-18 51-73-11 Fig. A-FBAAA Areas to Be Inspected Pre Repair and Pre SB 54-0080 Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01
Refer to Fig. A-FFBAA Sheet 01
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 76 5

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

# @A300 SERVICE BULLETIN (a) Smooth blend out the area to remove the aluminium spray protection or cadmium plating protection 0.17 mm (0.007 in.) (Refer to SRM 51-73-11). (b) From the inside, on left and right pylon, do an Eddy Current re-Inspection (Refer to NTM 54-40-11 Part 6) and Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBAAA Sheet 01 1 If crack is found =< 30 mm (1.181 in.):
a Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report b Repair before 500 FC, Refer to SUBTASK 540073-833-001 003 Install the doubler on the LH Pylon and/or SUBTASK 540073-833-002 002 Install the doubler on the RH Pylon and SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.
c Re-protect the area by pad cadmium plating Refer to (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). 2 If crack is found between 30 mm (1.181 in.) and 35 mm (1.378 in.):
a Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report b Repair before 250 FC, Refer to SUBTASK 540073-833-001 003 Install the doubler on the LH Pylon and/or SUBTASK 540073-833-002 002 Install the doubler on the RH Pylon and SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.
c Re-protect the area by pad cadmium plating Refer to (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). 3 If crack is found > 35 mm (1.378 in.): - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 4 If no crack is found:
a Re-protect the area by pad cadmium plating Refer to (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). b Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 77 5

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

# @A300 SERVICE BULLETIN

c Re-inspect the area as described in SUBTASK 540073-832-001 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. following the interval given in the Planning Information Paragraph E.(2).
or Accomplish Service Bulletin No. A300-54-0080 and apply the SUBTASK 540073-832-009 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. following the threshold given in the Planning Information Paragraph E.(2). **CONF 006 (1) Subtask 540073-832-001-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Service Bulletin (SB) A300-54-0080 Fig. A-FBAAA Areas to Be Inspected Pre Repair and Pre SB 54-0080 Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2): Refer to Fig. A-FFBAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBAAA Sheet 01

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 78 5

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

# @A300 SERVICE BULLETIN

1 If crack is found: - Refer to SUBTASK 540073-832-005 002 Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. 2 If no crack is found:
a Re-inspect the area as described in SUBTASK 540073-832-001 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. following the interval given in the Planning Information Paragraph E.(2).
or Accomplish Service Bulletin No. A300-54-0080 and apply the SUBTASK 540073-832-009 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. following the threshold given in the Planning Information Paragraph E.(2). b Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report (2) Subtask 540073-832-005-002 - Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Service Bulletin (SB) A300-54-0080 Structural Repair Manual (SRM) 51-40-12 51-40-18 51-73-11 Fig. A-FBAAA Areas to Be Inspected Pre Repair and Pre SB 54-0080 Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01
Refer to Fig. A-FFBAA Sheet 01
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 79 5

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

# @A300 SERVICE BULLETIN (a) Smooth blend out the area to remove the aluminium spray protection or cadmium plating protection 0.17 mm (0.007 in.) (Refer to SRM 51-73-11). (b) From the inside, on left and right pylon, do an Eddy Current re-Inspection (Refer to NTM 54-40-11 Part 6) and Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBAAA Sheet 01 1 If crack is found =< 30 mm (1.181 in.):
a Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report b Repair before 500 FC, Refer to SUBTASK 540073-833-001 003 Install the doubler on the LH Pylon and/or SUBTASK 540073-833-002 002 Install the doubler on the RH Pylon and SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.
c Re-protect the area by pad cadmium plating Refer to (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). 2 If crack is found between 30 mm (1.181 in.) and 35 mm (1.378 in.):
a Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report b Repair before 250 FC, Refer to SUBTASK 540073-833-001 003 Install the doubler on the LH Pylon and/or SUBTASK 540073-833-002 002 Install the doubler on the RH Pylon and SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.
c Re-protect the area by pad cadmium plating Refer to (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). 3 If crack is found > 35 mm (1.378 in.): - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 4 If no crack is found:
a Re-protect the area by pad cadmium plating Refer to (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). b Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 80 5

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

# @A300 SERVICE BULLETIN

c Re-inspect the area as described in SUBTASK 540073-832-001 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. following the interval given in the Planning Information Paragraph E.(2).
or Accomplish Service Bulletin No. A300-54-0080 and apply the SUBTASK 540073-832-009 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. following the threshold given in the Planning Information Paragraph E.(2). **CONF 007 (1) Subtask 540073-832-001-003 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Service Bulletin (SB) A300-54-0080 Fig. A-FBDAA Areas to Be Inspected Pre Repair and Pre SB 54-0080 Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2): Refer to Fig. A-FFBAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBDAA Sheet 01

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 81 5

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

# @A300 SERVICE BULLETIN

1 If crack is found: - Refer to SUBTASK 540073-832-005 003 Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. 2 If no crack is found:
a Re-inspect the area as described in SUBTASK 540073-832-001 003 Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. following the interval given in the Planning Information Paragraph E.(2).
or Accomplish Service Bulletin No. A300-54-0080 and apply the SUBTASK 540073-832-009 003 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. following the threshold given in the Planning Information Paragraph E.(2). b Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report (2) Subtask 540073-832-005-003 - Do a Special Detailed Inspection of the LH / RH Engine Pylon without protection. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Service Bulletin (SB) A300-54-0080 Structural Repair Manual (SRM) 51-40-12 51-40-18 51-73-11 Fig. A-FBDAA Areas to Be Inspected Pre Repair and Pre SB 54-0080 Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01
Refer to Fig. A-FFBAA Sheet 01
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 82 5

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# @A300 SERVICE BULLETIN (a) Smooth blend out the area to remove the aluminium spray protection or cadmium plating protection 0.17 mm (0.007 in.) (Refer to SRM 51-73-11). (b) From the inside, on left and right pylon, do an Eddy Current re-Inspection (Refer to NTM 54-40-11 Part 6) and Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBDAA Sheet 01 1 If crack is found =< 30 mm (1.181 in.):
a Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report b Repair before 500 FC, Refer to SUBTASK 540073-833-001 002 Install the doubler on the LH Pylon and/or SUBTASK 540073-833-002 003 Install the doubler on the RH Pylon and SUBTASK 540073-832-008 002 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.
c Re-protect the area by pad cadmium plating Refer to (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). 2 If crack is found between 30 mm (1.181 in.) and 35 mm (1.378 in.):
a Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report b Repair before 250 FC, Refer to SUBTASK 540073-833-001 002 Install the doubler on the LH Pylon and/or SUBTASK 540073-833-002 003 Install the doubler on the RH Pylon and SUBTASK 540073-832-008 002 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.
c Re-protect the area by pad cadmium plating Refer to (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). 3 If crack is found > 35 mm (1.378 in.): - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 4 If no crack is found:
a Re-protect the area by pad cadmium plating Refer to (Refer to SRM 51-40-18) and apply the paint coating (Refer to SRM 51-40-12). b Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 83 5

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# @A300 SERVICE BULLETIN

c Re-inspect the area as described in SUBTASK 540073-832-001 003 Do a Special Detailed Inspection of the LH / RH Engine Pylon Pre-repair and Pre-SB 54-0080. following the interval given in the Planning Information Paragraph E.(2).
or Accomplish Service Bulletin No. A300-54-0080 and apply the SUBTASK 540073-832-009 003 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. following the threshold given in the Planning Information Paragraph E.(2). **CONF ALL D. TEST **CONF 001 (1) Subtask 540073-700-002-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-001 001 or SUBTASK 540073-410-001 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF 002 (1) Subtask 540073-700-002-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-001 001 or SUBTASK 540073-410-001 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 84 5

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# @A300 SERVICE BULLETIN
**CONF 003 (1) Subtask 540073-700-002-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-001 001 or SUBTASK 540073-410-001 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF 004 (1) Subtask 540073-700-002-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-001 001 or SUBTASK 540073-410-001 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF 005 (1) Subtask 540073-700-002-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-001 001 or SUBTASK 540073-410-001 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 85 5

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# @A300 SERVICE BULLETIN
**CONF 006 (1) Subtask 540073-700-002-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-001 001 or SUBTASK 540073-410-001 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF 007 (1) Subtask 540073-700-002-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-001 001 or SUBTASK 540073-410-001 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 540073-410-001-001 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 86 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-002 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (2) Subtask 540073-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms. **CONF 002 (1) Subtask 540073-410-001-001 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 87 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-002 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (2) Subtask 540073-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms. **CONF 003 (1) Subtask 540073-410-001-001 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 88 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-002 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (2) Subtask 540073-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms. **CONF 004 (1) Subtask 540073-410-001-002 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 89 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-002 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (2) Subtask 540073-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms. **CONF 005 (1) Subtask 540073-410-001-002 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 90 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-002 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (2) Subtask 540073-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms. **CONF 006 (1) Subtask 540073-410-001-002 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 91 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-002 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (2) Subtask 540073-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms. **CONF 007 (1) Subtask 540073-410-001-002 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 92 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-002 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (2) Subtask 540073-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 93 5

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# @A300 SERVICE BULLETIN

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DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 94 5

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# @A300 SERVICE BULLETIN Task 540073-832-804-001 - Inspection Post Repair **CONF ALL 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. IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00. NOTE: The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin. Task Associated Data **CONF 001 Zone 410 420 Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 002 Zone 410 420 Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 003 Zone 410 420
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# @A300 SERVICE BULLETIN
Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 004 Zone 410 420 Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 005 Zone 410 420 Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 006 Zone 410 420 Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 007 Zone 410 420 Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 540073-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 96 5

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# @A300 SERVICE BULLETIN
Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-003-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 540073-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 97 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-003-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 003 (1) Subtask 540073-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001).
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 98 5

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# @A300 SERVICE BULLETIN (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-003-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 004 (1) Subtask 540073-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12).
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 99 5

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# @A300 SERVICE BULLETIN (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-003-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 005 (1) Subtask 540073-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 100 5

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# @A300 SERVICE BULLETIN (2) Subtask 540073-839-003-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 006 (1) Subtask 540073-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-003-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 101 5

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# @A300 SERVICE BULLETIN
**CONF 007 (1) Subtask 540073-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-003-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 102 5

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# @A300 SERVICE BULLETIN
**CONF ALL B. PREPARATION **CONF 001 (1) Subtask 540073-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-005-001 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). **CONF 002 (1) Subtask 540073-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 103 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-005-001 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). **CONF 003 (1) Subtask 540073-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 104 5

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# @A300 SERVICE BULLETIN (2) Subtask 540073-010-005-001 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). **CONF 004 (1) Subtask 540073-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-005-002 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 105 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). **CONF 005 (1) Subtask 540073-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-005-002 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401).
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 106 5

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# @A300 SERVICE BULLETIN (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). **CONF 006 (1) Subtask 540073-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-005-002 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 107 5

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# @A300 SERVICE BULLETIN
**CONF 007 (1) Subtask 540073-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-005-002 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 108 5

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# @A300 SERVICE BULLETIN
**CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 540073-832-008-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Fig. A-FBBAA Areas to Be Inspected Post Repair Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FFAAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBBAA Sheet 01 1 If crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 2 If no crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 109 5

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# @A300 SERVICE BULLETIN - Re-inspect the area as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. following the interval given in the Planning Information Paragraph E.(2). **CONF 002 (1) Subtask 540073-832-008-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Fig. A-FBBAA Areas to Be Inspected Post Repair Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FFAAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBBAA Sheet 01 1 If crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 2 If no crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 110 5

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# @A300 SERVICE BULLETIN - Re-inspect the area as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. following the interval given in the Planning Information Paragraph E.(2). **CONF 003 (1) Subtask 540073-832-008-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Fig. A-FBBAA Areas to Be Inspected Post Repair Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FFAAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBBAA Sheet 01 1 If crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 2 If no crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 111 5

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# @A300 SERVICE BULLETIN - Re-inspect the area as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. following the interval given in the Planning Information Paragraph E.(2). **CONF 004 (1) Subtask 540073-832-008-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Fig. A-FBBAA Areas to Be Inspected Post Repair Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FFBAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBBAA Sheet 01 1 If crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 2 If no crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 112 5

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# @A300 SERVICE BULLETIN - Re-inspect the area as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. following the interval given in the Planning Information Paragraph E.(2). **CONF 005 (1) Subtask 540073-832-008-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Fig. A-FBBAA Areas to Be Inspected Post Repair Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FFBAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBBAA Sheet 01 1 If crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 2 If no crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 113 5

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# @A300 SERVICE BULLETIN - Re-inspect the area as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. following the interval given in the Planning Information Paragraph E.(2). **CONF 006 (1) Subtask 540073-832-008-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Fig. A-FBBAA Areas to Be Inspected Post Repair Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FFBAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBBAA Sheet 01 1 If crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 2 If no crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 114 5

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# @A300 SERVICE BULLETIN - Re-inspect the area as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. following the interval given in the Planning Information Paragraph E.(2). **CONF 007 (1) Subtask 540073-832-008-002 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Fig. A-FBEAA Areas to Be Inspected Post Repair Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FFBAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBEAA Sheet 01 1 If crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 2 If no crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 115 5

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# @A300 SERVICE BULLETIN - Re-inspect the area as described in SUBTASK 540073-832-008 002 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. following the interval given in the Planning Information Paragraph E.(2). **CONF ALL D. TEST **CONF 001 (1) Subtask 540073-700-003-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-003 001 or SUBTASK 540073-410-003 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF 002 (1) Subtask 540073-700-003-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-003 001 or SUBTASK 540073-410-003 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF 003 (1) Subtask 540073-700-003-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 116 5

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# @A300 SERVICE BULLETIN to SUBTASK 540073-410-003 001 or SUBTASK 540073-410-003 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF 004 (1) Subtask 540073-700-003-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-003 001 or SUBTASK 540073-410-003 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF 005 (1) Subtask 540073-700-003-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-003 001 or SUBTASK 540073-410-003 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF 006 (1) Subtask 540073-700-003-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-003 001 or SUBTASK 540073-410-003 002)
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 117 5

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# @A300 SERVICE BULLETIN before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF 007 (1) Subtask 540073-700-003-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-003 001 or SUBTASK 540073-410-003 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 540073-410-003-001 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-003 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401).
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 118 5

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# @A300 SERVICE BULLETIN (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (2) Subtask 540073-942-004-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms. **CONF 002 (1) Subtask 540073-410-003-001 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-003 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 119 5

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# @A300 SERVICE BULLETIN (e) Close the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (2) Subtask 540073-942-004-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms. **CONF 003 (1) Subtask 540073-410-003-001 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-003 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 EL and 423 EL (Refer to AMM 06-21-54)

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 120 5

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# @A300 SERVICE BULLETIN (2) Subtask 540073-942-004-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms. **CONF 004 (1) Subtask 540073-410-003-002 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-003 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (2) Subtask 540073-942-004-001 - Close-up Manpower Resources Skills NON SPECIFIC

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 121 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms. **CONF 005 (1) Subtask 540073-410-003-002 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-003 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (2) Subtask 540073-942-004-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 122 5

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# @A300 SERVICE BULLETIN (b) Remove access platforms. **CONF 006 (1) Subtask 540073-410-003-002 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-003 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (2) Subtask 540073-942-004-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 123 5

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# @A300 SERVICE BULLETIN
**CONF 007 (1) Subtask 540073-410-003-002 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-003 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (2) Subtask 540073-942-004-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 124 5

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# @A300 SERVICE BULLETIN Task 540073-832-805-001 - Inspection Post Service Bulletin No.A300-54-0080 **CONF ALL 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. IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00. NOTE: The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin. Task Associated Data **CONF 001 Zone 410 420 Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 002 Zone 410 420 Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 003 Zone 410 420
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 125 5

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# @A300 SERVICE BULLETIN
Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 004 Zone 410 420 Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 005 Zone 410 420 Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 006 Zone 410 420 Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF 007 Zone 410 420 Manpower TOTAL MANHOURS 5.00 ELAPSED TIME (HOURS) 5.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 540073-910-004-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 126 5

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# @A300 SERVICE BULLETIN
Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-004-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 540073-910-004-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 127 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-004-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 003 (1) Subtask 540073-910-004-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001).
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 128 5

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# @A300 SERVICE BULLETIN (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-004-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 004 (1) Subtask 540073-910-004-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12).
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 129 5

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# @A300 SERVICE BULLETIN (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-004-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 005 (1) Subtask 540073-910-004-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 130 5

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# @A300 SERVICE BULLETIN (2) Subtask 540073-839-004-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 006 (1) Subtask 540073-910-004-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-004-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 131 5

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# @A300 SERVICE BULLETIN
**CONF 007 (1) Subtask 540073-910-004-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-004-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 132 5

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# @A300 SERVICE BULLETIN
**CONF ALL B. PREPARATION **CONF 001 (1) Subtask 540073-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-006-001 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). **CONF 002 (1) Subtask 540073-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 133 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-006-001 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). **CONF 003 (1) Subtask 540073-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 134 5

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# @A300 SERVICE BULLETIN (2) Subtask 540073-010-006-001 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). **CONF 004 (1) Subtask 540073-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-006-002 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 135 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). **CONF 005 (1) Subtask 540073-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-006-002 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401).
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 136 5

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# @A300 SERVICE BULLETIN (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). **CONF 006 (1) Subtask 540073-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-006-002 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 137 5

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# @A300 SERVICE BULLETIN
**CONF 007 (1) Subtask 540073-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 (a) De-energize the aircraft electrical circuits (Refer to AMM 24-41-00, Page Block 301) and electrically ground the aircraft (Refer to AMM 24-00-00, Page Block 301). (b) Install access platform for access to engine pylons. (2) Subtask 540073-010-006-002 - Remove for Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 (a) Open the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (b) Remove the precooler (Refer to AMM 36-11-15, Page Block 401). (c) Remove the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Remove the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 138 5

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# @A300 SERVICE BULLETIN
**CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 540073-832-009-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 9 54-40-11 Part 6 Service Bulletin (SB) A300-54-0080 Fig. A-FBCAA Areas to Be Inspected Post SB 54-0080 Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FFAAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBCAA Sheet 01 1 If crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 2 If no crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 139 5

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# @A300 SERVICE BULLETIN - Re-inspect the area as described in SUBTASK 540073-832-009 001 Doa Special Detailed Inspection of the LH / RH Engine Pylon PostSB 54-0080. following the interval given in the Planning Information Paragraph E.(2). **CONF 002 (1) Subtask 540073-832-009-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 9 54-40-11 Part 6 Service Bulletin (SB) A300-54-0080 Fig. A-FBCAA Areas to Be Inspected Post SB 54-0080 Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FFAAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBCAA Sheet 01 1 If crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 140 5

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# @A300 SERVICE BULLETIN

2 If no crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Re-inspect the area as described in SUBTASK 540073-832-009 001 Doa Special Detailed Inspection of the LH / RH Engine Pylon PostSB 54-0080. following the interval given in the Planning Information Paragraph E.(2). **CONF 003 (1) Subtask 540073-832-009-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 9 54-40-11 Part 6 Service Bulletin (SB) A300-54-0080 Fig. A-FBCAA Areas to Be Inspected Post SB 54-0080 Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FFAAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBCAA Sheet 01 1 If crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 141 5

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# @A300 SERVICE BULLETIN - Contact Airbus before next flight. 2 If no crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Re-inspect the area as described in SUBTASK 540073-832-009 001 Doa Special Detailed Inspection of the LH / RH Engine Pylon PostSB 54-0080. following the interval given in the Planning Information Paragraph E.(2). **CONF 004 (1) Subtask 540073-832-009-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 9 54-40-11 Part 6 Service Bulletin (SB) A300-54-0080 Fig. A-FBCAA Areas to Be Inspected Post SB 54-0080 Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FFBAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBCAA Sheet 01

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# @A300 SERVICE BULLETIN

1 If crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 2 If no crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Re-inspect the area as described in SUBTASK 540073-832-009 001 Doa Special Detailed Inspection of the LH / RH Engine Pylon PostSB 54-0080. following the interval given in the Planning Information Paragraph E.(2). **CONF 005 (1) Subtask 540073-832-009-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 9 54-40-11 Part 6 Service Bulletin (SB) A300-54-0080 Fig. A-FBCAA Areas to Be Inspected Post SB 54-0080 Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FFBAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 143 5

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# @A300 SERVICE BULLETIN
Refer to Fig. A-FBCAA Sheet 01 1 If crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 2 If no crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Re-inspect the area as described in SUBTASK 540073-832-009 001 Doa Special Detailed Inspection of the LH / RH Engine Pylon PostSB 54-0080. following the interval given in the Planning Information Paragraph E.(2). **CONF 006 (1) Subtask 540073-832-009-001 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 9 54-40-11 Part 6 Service Bulletin (SB) A300-54-0080 Fig. A-FBCAA Areas to Be Inspected Post SB 54-0080 Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01 (a) At the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FFBAA Sheet 01

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 144 5

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# @A300 SERVICE BULLETIN From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBCAA Sheet 01 1 If crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 2 If no crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Re-inspect the area as described in SUBTASK 540073-832-009 001 Doa Special Detailed Inspection of the LH / RH Engine Pylon PostSB 54-0080. following the interval given in the Planning Information Paragraph E.(2). **CONF 007 (1) Subtask 540073-832-009-003 - Do a Special Detailed Inspection of the LH / RH Engine Pylon Post-SB 54-0080. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-40-11 Part 6 54-40-11 Part 9 Service Bulletin (SB) A300-54-0080 Fig. A-FBFAA Areas to Be Inspected Post SB 54-0080 Sheet 01 Fig. A-FFBAA Flow Chart Sheet 01

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 145 5

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# @A300 SERVICE BULLETIN (a) At the threshold given in the Planning Information Paragraph E.(2) : Refer to Fig. A-FFBAA Sheet 01 From the inside, on left and right pylon, do an Eddy Current Inspection (Refer to NTM 54-40-11 Part 6) or Liquid Penetrant Inspection (Refer to NTM 54-40-11 Part 9) in the lower spar axis between ribs 6 and 7. Refer to Fig. A-FBFAA Sheet 01 1 If crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Contact Airbus before next flight. 2 If no crack is found: - Send to AIRBUS inspection report, refer to Appendix 01- Inspection Report - Re-inspect the area as described in SUBTASK 540073-832-009 003 Doa Special Detailed Inspection of the LH / RH Engine Pylon PostSB 54-0080. following the interval given in the Planning Information Paragraph E.(2). **CONF ALL D. TEST **CONF 001 (1) Subtask 540073-700-004-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-004 001 or SUBTASK 540073-410-004 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 146 5

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# @A300 SERVICE BULLETIN
**CONF 002 (1) Subtask 540073-700-004-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-004 001 or SUBTASK 540073-410-004 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF 003 (1) Subtask 540073-700-004-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-004 001 or SUBTASK 540073-410-004 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF 004 (1) Subtask 540073-700-004-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-004 001 or SUBTASK 540073-410-004 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 147 5

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# @A300 SERVICE BULLETIN
**CONF 005 (1) Subtask 540073-700-004-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-004 001 or SUBTASK 540073-410-004 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF 006 (1) Subtask 540073-700-004-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-004 001 or SUBTASK 540073-410-004 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201). **CONF 007 (1) Subtask 540073-700-004-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 36-11-00, Page Block 201 NOTE: Install the bleed air precooler cold air inlet duct and the precooler (refer to SUBTASK 540073-410-004 001 or SUBTASK 540073-410-004 002) before accomplishment of the test below. (a) Do a leak test of the engine bleed air supply system (Refer to AMM 36-11-00, Page Block 201).

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# @A300 SERVICE BULLETIN
**CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 540073-410-004-001 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-004 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (2) Subtask 540073-942-005-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 149 5

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# @A300 SERVICE BULLETIN
**CONF 002 (1) Subtask 540073-410-004-001 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-004 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (2) Subtask 540073-942-005-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms.

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# @A300 SERVICE BULLETIN
**CONF 003 (1) Subtask 540073-410-004-001 - Install the Access LH / RH Engine Pylon. Work Zones and Access Panels Zone Access/Work location 410 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-004 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 EL and 423 EL (Refer to AMM 06-21-54) (2) Subtask 540073-942-005-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 151 5

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# @A300 SERVICE BULLETIN
**CONF 004 (1) Subtask 540073-410-004-002 - Install the Access LH / RH Engine Pylon. Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-004 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (2) Subtask 540073-942-005-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms. **CONF 005 (1) Subtask 540073-410-004-002 - Install the Access LH / RH Engine Pylon. Manpower Resources Skills NON SPECIFIC

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-004 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (2) Subtask 540073-942-005-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms. **CONF 006 (1) Subtask 540073-410-004-002 - Install the Access LH / RH Engine Pylon. Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-004 001).

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# @A300 SERVICE BULLETIN (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401). (e) Close the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (2) Subtask 540073-942-005-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms. **CONF 007 (1) Subtask 540073-410-004-002 - Install the Access LH / RH Engine Pylon. Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-54 36-00-00, Page Block 401 36-11-15, Page Block 401 54-11-15, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-004 001). (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the bleed air precooler cold air inlet duct (Refer to AMM 36-00-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8 (Refer to AMM 54-11-15, Page Block 401). (d) Install the precooler (Refer to AMM 36-11-15, Page Block 401).
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# @A300 SERVICE BULLETIN (e) Close the access door 413 GL and 423 GL (Refer to AMM 06-21-54) (2) Subtask 540073-942-005-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) Disconnect the aircraft electrical ground connection (Refer to AMM 24-00-00, Page Block 301). (b) Remove access platforms.

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# @A300 SERVICE BULLETIN

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# @A300 SERVICE BULLETIN Task 540073-833-801-001 - Repair **CONF ALL 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. IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00. Task Associated Data **CONF 001 Zone 410 420 Manpower TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 **CONF 002 Zone 410 420 Manpower TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 **CONF 003 Zone 410 420 Manpower TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00

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# @A300 SERVICE BULLETIN
**CONF 004 Zone 410 420 Manpower TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 **CONF 005 Zone 410 420 Manpower TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 **CONF 006 Zone 410 420 Manpower TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 **CONF 007 Zone 410 420 Manpower TOTAL MANHOURS 60.50 ELAPSED TIME (HOURS) 53.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 540073-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 158 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-30-38 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For fastener hole diameters and drill and deburr data (Refer to SRM 51-30-38). (f) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (g) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 540073-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 159 5

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# @A300 SERVICE BULLETIN

References Structural Repair Manual (SRM) 51-30-38 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For fastener hole diameters and drill and deburr data (Refer to SRM 51-30-38). (f) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (g) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 003 (1) Subtask 540073-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-30-38 51-40-12

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 160 5

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# @A300 SERVICE BULLETIN (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For fastener hole diameters and drill and deburr data (Refer to SRM 51-30-38). (f) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (g) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 004 (1) Subtask 540073-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-30-38 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List.
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 161 5

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# @A300 SERVICE BULLETIN (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For fastener hole diameters and drill and deburr data (Refer to SRM 51-30-38). (f) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (g) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 005 (1) Subtask 540073-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-30-38 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12).
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 162 5

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# @A300 SERVICE BULLETIN (e) For fastener hole diameters and drill and deburr data (Refer to SRM 51-30-38). (f) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (g) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 006 (1) Subtask 540073-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-30-38 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For fastener hole diameters and drill and deburr data (Refer to SRM 51-30-38). (f) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML).
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 163 5

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# @A300 SERVICE BULLETIN (g) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required (2) Subtask 540073-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 007 (1) Subtask 540073-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 53-00-00, Page Block 001 Structural Repair Manual (SRM) 51-30-38 51-40-12 (a) For the Frame (FR) identification (Refer to AMM 53-00-00, Page Block 001). (b) For the identification of zones (Refer to AMM 06-21-00, Page Block 001) and Manual Matter Zone List. (c) For the identification of access panels (Refer to AMM 06-21-00, Page Block 001) and Manual Front Matter Panel list. (d) Renew the protective finish (Refer to SRM 51-40-12). (e) For fastener hole diameters and drill and deburr data (Refer to SRM 51-30-38). (f) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (g) Clean the surfaces to be sealed with solvent: Solvent General Purpose 11-026 As required

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 164 5

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# @A300 SERVICE BULLETIN (2) Subtask 540073-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 540073-010-003-001 - Remove the LH Engine. Work Zones and Access Panels Zone Access/Work location 410 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Do the preparation procedure as specified in the removal of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Remove the Left Engine (Refer to AMM 71-00-00, Page Block 401). (2) Subtask 540073-010-004-001 - Remove the RH Engine. Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Do the preparation procedure as specified in the removal of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Remove the Right Engine (Refer to AMM 71-00-00, Page Block 401).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 165 5

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# @A300 SERVICE BULLETIN
**CONF 002 (1) Subtask 540073-010-003-001 - Remove the LH Engine. Work Zones and Access Panels Zone Access/Work location 410 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Do the preparation procedure as specified in the removal of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Remove the Left Engine (Refer to AMM 71-00-00, Page Block 401). (2) Subtask 540073-010-004-001 - Remove the RH Engine. Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Do the preparation procedure as specified in the removal of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Remove the Right Engine (Refer to AMM 71-00-00, Page Block 401). **CONF 003 (1) Subtask 540073-010-003-001 - Remove the LH Engine. Work Zones and Access Panels Zone Access/Work location 410 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 166 5

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# @A300 SERVICE BULLETIN (a) Do the preparation procedure as specified in the removal of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Remove the Left Engine (Refer to AMM 71-00-00, Page Block 401). (2) Subtask 540073-010-004-001 - Remove the RH Engine. Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Do the preparation procedure as specified in the removal of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Remove the Right Engine (Refer to AMM 71-00-00, Page Block 401). **CONF 004 (1) Subtask 540073-010-003-001 - Remove the LH Engine. Work Zones and Access Panels Zone Access/Work location 410 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Do the preparation procedure as specified in the removal of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Remove the Left Engine (Refer to AMM 71-00-00, Page Block 401). (2) Subtask 540073-010-004-001 - Remove the RH Engine. Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Skills NON SPECIFIC

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 167 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Do the preparation procedure as specified in the removal of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Remove the Right Engine (Refer to AMM 71-00-00, Page Block 401). **CONF 005 (1) Subtask 540073-010-003-001 - Remove the LH Engine. Work Zones and Access Panels Zone Access/Work location 410 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Do the preparation procedure as specified in the removal of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Remove the Left Engine (Refer to AMM 71-00-00, Page Block 401). (2) Subtask 540073-010-004-001 - Remove the RH Engine. Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Do the preparation procedure as specified in the removal of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Remove the Right Engine (Refer to AMM 71-00-00, Page Block 401). **CONF 006 (1) Subtask 540073-010-003-001 - Remove the LH Engine. Work Zones and Access Panels Zone Access/Work location 410
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 168 5

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# @A300 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Do the preparation procedure as specified in the removal of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Remove the Left Engine (Refer to AMM 71-00-00, Page Block 401). (2) Subtask 540073-010-004-001 - Remove the RH Engine. Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Do the preparation procedure as specified in the removal of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Remove the Right Engine (Refer to AMM 71-00-00, Page Block 401). **CONF 007 (1) Subtask 540073-010-003-001 - Remove the LH Engine. Work Zones and Access Panels Zone Access/Work location 410 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Do the preparation procedure as specified in the removal of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Remove the Left Engine (Refer to AMM 71-00-00, Page Block 401).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 169 5

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# @A300 SERVICE BULLETIN (2) Subtask 540073-010-004-001 - Remove the RH Engine. Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 (a) Do the preparation procedure as specified in the removal of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Remove the Right Engine (Refer to AMM 71-00-00, Page Block 401). **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 540073-833-001-001 - Install the doubler on the LH Pylon Work Zones and Access Panels Zone Access/Work location 410 Work location from Rib 6 to Rib 7 Manpower Resources Manhours 7.50 Minimum number of person 1 Subtask elapsed time 7.50 Skills AIRFRAME Material necessary to do the job Kit 540073A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 54 NUT 3 NSA5414-32-18 10 RIVET 4 NAS1149CN832R 12 WASHER 5 MS21043-08 6 NUT 6 NAS1152E3 6 BOLT 8 NAS1153E4 42 BOLT 9 NAS1153E7 12 BOLT

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# @A300 SERVICE BULLETIN

References Non Destructive Test Manual (NTM) 51-31-11 Part 1 - Procedure A 51-32-03 Part 1 51-33-02 Part 1 51-34-04 Part 1 Structural Repair Manual (SRM) 51-30-43 Fig. A-FBGAA Installation of Doubler under Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 (a) Remove the heat shield between ribs 6 and 8 Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 1 Heat Shield Item (16) Retain 9 Bolts Item (17) Retain 5 Shim or Washer Item (18) Retain (b) Remove the rivets and plates : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 10 Rivets Item (3) Discard 4 Plates Item (19) Retain 1 Plate Item (20) Retain 2 Contersink at location of removed rivets Item (3) (Refer to SRM 51-30-43) to obtain a correct contact at location of doubler Item 1. (c) Drill two stop holes : 1 Drill two 6mm (0.236 in.) dia. holes at the ends of the crack. 2 Do an additional inspection after drilling of crack stop holes as specified below: Refer to NTM 51-31-11 Part 1 - Procedure A
a Calibration Standard: PN 99A53003001108 as per NTM 51-34-04 Part 1. - If crack is found, contact AIRBUS.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 171 5

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# @A300 SERVICE BULLETIN (d) Remove the fasteners at ribs 6 and 7 : 1 Remove : 12 Rivet NSA5415-40 Item (7) Discard (e) Offer-up and position under lower spar : 1 Doubler R5460005520000 Item 1 (f) Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Drill 9 holes for the passage of the attachments bolts Item (17) of the heat shield Item (16) on the doubler Item 1 to : Dia. mini. 5.0 mm (0.196 in.) Dia. mini. 5.1 mm (0.200 in.) 2 Before attaching the doubler Item 1, attach : 4 Plates Item (19) Retained at removal 1 Plate Item (20) Retained at removal with : 10 Rivet NSA5414-32-18 Item 3 3 Drill 12 holes for the Bolts Item 9 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 4 Drill 42 holes for the Bolts Item 8 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 5 Drill 6 holes for the Bolts Item 6 : Dia. mini. 4.15 mm (0.163 in.) Dia. mini. 4.17 mm (0.164 in.) 6 Attach the doubler Item 1 : 12 Bolt NAS1153E7 Item 9
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# @A300 SERVICE BULLETIN

54 Nut NAS1726C3E Item 2 42 Bolt NAS1153E4 Item 8 6 Bolt NAS1152E3 Item 6 6 Nut MS21043-08 Item 5 12 Washer NAS1149CN832R Item 4 (g) Installation of the heat shield : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Heat Shield Item (16) Retained at removal 9 Bolt Item (17) Retained at removal 5 Shim or Washer Item (18) Retained at removal NOTE: Reduce the thickness of the original shims or washers Item 18 by 3 mm (0.118 in.) at location of the doubler Item 1 to keep the same gap at installation of the heat shield Item 16. (h) Do a new inspection as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. (2) Subtask 540073-833-002-001 - Install the doubler on the RH Pylon Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Manhours 7.50 Minimum number of person 1 Subtask elapsed time 7.50 Skills AIRFRAME Material necessary to do the job Kit 540073A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 54 NUT 3 NSA5414-32-18 10 RIVET 4 NAS1149CN832R 12 WASHER DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 173 5

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# @A300 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 5 MS21043-08 6 NUT 6 NAS1152E3 6 BOLT 8 NAS1153E4 42 BOLT 9 NAS1153E7 12 BOLT References Non Destructive Test Manual (NTM) 51-31-11 Part 1 Procedure A 51-32-03 Part 1 51-33-02 Part 1 51-34-04 Part 1 Structural Repair Manual (SRM) 51-30-43 Fig. A-FBGAA Installation of Doubler under Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 (a) Remove the heat shield between ribs 6 and 8 Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 1 Heat Shield Item (16) Retain 9 Bolts Item (17) Retain 5 Shim or Washer Item (18) Retain (b) Remove the rivets and plates : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 10 Rivets Item (3) Discard 4 Plates Item (19) Retain 1 Plate Item (20) Retain 2 Contersink at location of removed rivets Item (3) (Refer to SRM 51-30-43) to obtain a correct contact at location of doubler Item 1. (c) Drill two stop holes : 1 Drill two 6mm (0.236 in.) dia. holes at the ends of the crack. 2 Do an additional inspection after drilling of crack stop holes as specified below: Refer to NTM 51-31-11 Part 1 Procedure A DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 174 5

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# @A300 SERVICE BULLETIN

a Calibration Standard: PN 99A53003001108 as per NTM 51-34-04 Part 1. - If crack is found, contact AIRBUS. (d) Remove the fasteners at ribs 6 and 7 : 1 Remove : 12 Rivet NSA5415-40 Item (7) Discard (e) Offer-up and position under lower spar : 1 Doubler R5460005520000 Item 1 (f) Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Drill 9 holes for the passage of the attachments bolts Item (17) of the heat shield Item (16) on the doubler Item 1 to : Dia. mini. 5.0 mm (0.196 in.) Dia. mini. 5.1 mm (0.200 in.) 2 Before attaching the doubler Item 1, attach : 4 Plates Item (19) Retained at removal 1 Plate Item (20) Retained at removal with : 10 Rivet NSA5414-32-18 Item 3 3 Drill 12 holes for the Bolts Item 9 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 4 Drill 42 holes for the e Bolts Item 8 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 5 Drill 6 holes for the Bolts Item 6 : Dia. mini. 4.15 mm (0.163 in.) Dia. mini. 4.17 mm (0.164 in.)
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 175 5

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# @A300 SERVICE BULLETIN

6 Attach the doubler Item 1 : 12 Bolt NAS1153E7 Item 9 54 Nut NAS1726C3E Item 2 42 Bolt NAS1153E4 Item 8 6 Bolt NAS1152E3 Item 6 6 Nut MS21043-08 Item 5 12 Washer NAS1149CN832R Item 4 (g) Installation of the heat shield : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Heat Shield Item (16) Retained at removal 9 Bolt Item (17) Retained at removal 5 Shim or Washer Item (18) Retained at removal NOTE: Reduce the thickness of the original shims or washers Item 18 by 3 mm (0.118 in.) at location of the doubler Item 1 to keep the same gap at installation of the heat shield Item 16. (h) Do a new inspection as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. **CONF 002 (1) Subtask 540073-833-001-001 - Install the doubler on the LH Pylon Work Zones and Access Panels Zone Access/Work location 410 Work location from Rib 6 to Rib 7 Manpower Resources Manhours 7.50 Minimum number of person 1 Subtask elapsed time 7.50 Skills AIRFRAME

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 176 5

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# @A300 SERVICE BULLETIN
Material necessary to do the job Kit 540073A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 54 NUT 3 NSA5414-32-18 10 RIVET 4 NAS1149CN832R 12 WASHER 5 MS21043-08 6 NUT 6 NAS1152E3 6 BOLT 8 NAS1153E4 42 BOLT 9 NAS1153E7 12 BOLT References Non Destructive Test Manual (NTM) 51-31-11 Part 1 - Procedure A 51-32-03 Part 1 51-33-02 Part 1 51-34-04 Part 1 Structural Repair Manual (SRM) 51-30-43 Fig. A-FBGAA Installation of Doubler under Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 (a) Remove the heat shield between ribs 6 and 8 Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 1 Heat Shield Item (16) Retain 9 Bolts Item (17) Retain 5 Shim or Washer Item (18) Retain (b) Remove the rivets and plates : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 10 Rivets Item (3) Discard 4 Plates Item (19) Retain 1 Plate Item (20) Retain 2 Contersink at location of removed rivets Item (3) (Refer to SRM 51-30-43) to obtain a correct contact at location of doubler Item 1.
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 177 5

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# @A300 SERVICE BULLETIN (c) Drill two stop holes : 1 Drill two 6mm (0.236 in.) dia. holes at the ends of the crack. 2 Do an additional inspection after drilling of crack stop holes as specified below: Refer to NTM 51-31-11 Part 1 - Procedure A
a Calibration Standard: PN 99A53003001108 as per NTM 51-34-04 Part 1. - If crack is found, contact AIRBUS. (d) Remove the fasteners at ribs 6 and 7 : 1 Remove : 12 Rivet NSA5415-40 Item (7) Discard (e) Offer-up and position under lower spar : 1 Doubler R5460005520000 Item 1 (f) Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Drill 9 holes for the passage of the attachments bolts Item (17) of the heat shield Item (16) on the doubler Item 1 to : Dia. mini. 5.0 mm (0.196 in.) Dia. mini. 5.1 mm (0.200 in.) 2 Before attaching the doubler Item 1, attach : 4 Plates Item (19) Retained at removal 1 Plate Item (20) Retained at removal with : 10 Rivet NSA5414-32-18 Item 3 3 Drill 12 holes for the Bolts Item 9 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.)

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 178 5

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# @A300 SERVICE BULLETIN

4 Drill 42 holes for the Bolts Item 8 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 5 Drill 6 holes for the Bolts Item 6 : Dia. mini. 4.15 mm (0.163 in.) Dia. mini. 4.17 mm (0.164 in.) 6 Attach the doubler Item 1 : 12 Bolt NAS1153E7 Item 9 54 Nut NAS1726C3E Item 2 42 Bolt NAS1153E4 Item 8 6 Bolt NAS1152E3 Item 6 6 Nut MS21043-08 Item 5 12 Washer NAS1149CN832R Item 4 (g) Installation of the heat shield : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Heat Shield Item (16) Retained at removal 9 Bolt Item (17) Retained at removal 5 Shim or Washer Item (18) Retained at removal NOTE: Reduce the thickness of the original shims or washers Item 18 by 3 mm (0.118 in.) at location of the doubler Item 1 to keep the same gap at installation of the heat shield Item 16. (h) Do a new inspection as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. (2) Subtask 540073-833-002-001 - Install the doubler on the RH Pylon Work Zones and Access Panels Zone Access/Work location 420

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 179 5

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# @A300 SERVICE BULLETIN
Manpower Resources Manhours 7.50 Minimum number of person 1 Subtask elapsed time 7.50 Skills AIRFRAME Material necessary to do the job Kit 540073A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 54 NUT 3 NSA5414-32-18 10 RIVET 4 NAS1149CN832R 12 WASHER 5 MS21043-08 6 NUT 6 NAS1152E3 6 BOLT 8 NAS1153E4 42 BOLT 9 NAS1153E7 12 BOLT References Non Destructive Test Manual (NTM) 51-31-11 Part 1 Procedure A 51-32-03 Part 1 51-33-02 Part 1 51-34-04 Part 1 Structural Repair Manual (SRM) 51-30-43 Fig. A-FBGAA Installation of Doubler under Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 (a) Remove the heat shield between ribs 6 and 8 Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 1 Heat Shield Item (16) Retain 9 Bolts Item (17) Retain 5 Shim or Washer Item (18) Retain (b) Remove the rivets and plates : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 10 Rivets Item (3) Discard

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 180 5

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# @A300 SERVICE BULLETIN
4 Plates Item (19) Retain 1 Plate Item (20) Retain 2 Contersink at location of removed rivets Item (3) (Refer to SRM 51-30-43) to obtain a correct contact at location of doubler Item 1. (c) Drill two stop holes : 1 Drill two 6mm (0.236 in.) dia. holes at the ends of the crack. 2 Do an additional inspection after drilling of crack stop holes as specified below: Refer to NTM 51-31-11 Part 1 Procedure A
a Calibration Standard: PN 99A53003001108 as per NTM 51-34-04 Part 1. - If crack is found, contact AIRBUS. (d) Remove the fasteners at ribs 6 and 7 : 1 Remove : 12 Rivet NSA5415-40 Item (7) Discard (e) Offer-up and position under lower spar : 1 Doubler R5460005520000 Item 1 (f) Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Drill 9 holes for the passage of the attachments bolts Item (17) of the heat shield Item (16) on the doubler Item 1 to : Dia. mini. 5.0 mm (0.196 in.) Dia. mini. 5.1 mm (0.200 in.) 2 Before attaching the doubler Item 1, attach : 4 Plates Item (19) Retained at removal 1 Plate Item (20) Retained at removal with : 10 Rivet NSA5414-32-18 Item 3

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 181 5

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# @A300 SERVICE BULLETIN

3 Drill 12 holes for the Bolts Item 9 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 4 Drill 42 holes for the e Bolts Item 8 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 5 Drill 6 holes for the Bolts Item 6 : Dia. mini. 4.15 mm (0.163 in.) Dia. mini. 4.17 mm (0.164 in.) 6 Attach the doubler Item 1 : 12 Bolt NAS1153E7 Item 9 54 Nut NAS1726C3E Item 2 42 Bolt NAS1153E4 Item 8 6 Bolt NAS1152E3 Item 6 6 Nut MS21043-08 Item 5 12 Washer NAS1149CN832R Item 4 (g) Installation of the heat shield : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Heat Shield Item (16) Retained at removal 9 Bolt Item (17) Retained at removal 5 Shim or Washer Item (18) Retained at removal NOTE: Reduce the thickness of the original shims or washers Item 18 by 3 mm (0.118 in.) at location of the doubler Item 1 to keep the same gap at installation of the heat shield Item 16. (h) Do a new inspection as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 182 5

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# @A300 SERVICE BULLETIN
**CONF 003 (1) Subtask 540073-833-001-001 - Install the doubler on the LH Pylon Work Zones and Access Panels Zone Access/Work location 410 Work location from Rib 6 to Rib 7 Manpower Resources Manhours 7.50 Minimum number of person 1 Subtask elapsed time 7.50 Skills AIRFRAME Material necessary to do the job Kit 540073A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 54 NUT 3 NSA5414-32-18 10 RIVET 4 NAS1149CN832R 12 WASHER 5 MS21043-08 6 NUT 6 NAS1152E3 6 BOLT 8 NAS1153E4 42 BOLT 9 NAS1153E7 12 BOLT References Non Destructive Test Manual (NTM) 51-31-11 Part 1 - Procedure A 51-32-03 Part 1 51-33-02 Part 1 51-34-04 Part 1 Structural Repair Manual (SRM) 51-30-43 Fig. A-FBGAA Installation of Doubler under Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 (a) Remove the heat shield between ribs 6 and 8 Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 1 Heat Shield Item (16) Retain 9 Bolts Item (17) Retain 5 Shim or Washer Item (18) Retain
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 183 5

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# @A300 SERVICE BULLETIN (b) Remove the rivets and plates : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 10 Rivets Item (3) Discard 4 Plates Item (19) Retain 1 Plate Item (20) Retain 2 Contersink at location of removed rivets Item (3) (Refer to SRM 51-30-43) to obtain a correct contact at location of doubler Item 1. (c) Drill two stop holes : 1 Drill two 6mm (0.236 in.) dia. holes at the ends of the crack. 2 Do an additional inspection after drilling of crack stop holes as specified below: Refer to NTM 51-31-11 Part 1 - Procedure A
a Calibration Standard: PN 99A53003001108 as per NTM 51-34-04 Part 1. - If crack is found, contact AIRBUS. (d) Remove the fasteners at ribs 6 and 7 : 1 Remove : 12 Rivet NSA5415-40 Item (7) Discard (e) Offer-up and position under lower spar : 1 Doubler R5460005520000 Item 1 (f) Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Drill 9 holes for the passage of the attachments bolts Item (17) of the heat shield Item (16) on the doubler Item 1 to : Dia. mini. 5.0 mm (0.196 in.) Dia. mini. 5.1 mm (0.200 in.) 2 Before attaching the doubler Item 1, attach : 4 Plates Item (19) Retained at removal
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 184 5

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# @A300 SERVICE BULLETIN
1 Plate Item (20) Retained at removal with : 10 Rivet NSA5414-32-18 Item 3 3 Drill 12 holes for the Bolts Item 9 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 4 Drill 42 holes for the Bolts Item 8 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 5 Drill 6 holes for the Bolts Item 6 : Dia. mini. 4.15 mm (0.163 in.) Dia. mini. 4.17 mm (0.164 in.) 6 Attach the doubler Item 1 : 12 Bolt NAS1153E7 Item 9 54 Nut NAS1726C3E Item 2 42 Bolt NAS1153E4 Item 8 6 Bolt NAS1152E3 Item 6 6 Nut MS21043-08 Item 5 12 Washer NAS1149CN832R Item 4 (g) Installation of the heat shield : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Heat Shield Item (16) Retained at removal 9 Bolt Item (17) Retained at removal 5 Shim or Washer Item (18) Retained at removal NOTE: Reduce the thickness of the original shims or washers Item 18 by 3 mm (0.118 in.) at location of the doubler Item 1 to keep the same DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 185 5

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# @A300 SERVICE BULLETIN gap at installation of the heat shield Item 16. (h) Do a new inspection as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. (2) Subtask 540073-833-002-001 - Install the doubler on the RH Pylon Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Manhours 7.50 Minimum number of person 1 Subtask elapsed time 7.50 Skills AIRFRAME Material necessary to do the job Kit 540073A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 54 NUT 3 NSA5414-32-18 10 RIVET 4 NAS1149CN832R 12 WASHER 5 MS21043-08 6 NUT 6 NAS1152E3 6 BOLT 8 NAS1153E4 42 BOLT 9 NAS1153E7 12 BOLT References Non Destructive Test Manual (NTM) 51-31-11 Part 1 Procedure A 51-32-03 Part 1 51-33-02 Part 1 51-34-04 Part 1 Structural Repair Manual (SRM) 51-30-43 Fig. A-FBGAA Installation of Doubler under Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 (a) Remove the heat shield between ribs 6 and 8 Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 1 Heat Shield Item (16) Retain 9 Bolts Item (17) Retain
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 186 5

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# @A300 SERVICE BULLETIN
5 Shim or Washer Item (18) Retain (b) Remove the rivets and plates : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 10 Rivets Item (3) Discard 4 Plates Item (19) Retain 1 Plate Item (20) Retain 2 Contersink at location of removed rivets Item (3) (Refer to SRM 51-30-43) to obtain a correct contact at location of doubler Item 1. (c) Drill two stop holes : 1 Drill two 6mm (0.236 in.) dia. holes at the ends of the crack. 2 Do an additional inspection after drilling of crack stop holes as specified below: Refer to NTM 51-31-11 Part 1 Procedure A
a Calibration Standard: PN 99A53003001108 as per NTM 51-34-04 Part 1. - If crack is found, contact AIRBUS. (d) Remove the fasteners at ribs 6 and 7 : 1 Remove : 12 Rivet NSA5415-40 Item (7) Discard (e) Offer-up and position under lower spar : 1 Doubler R5460005520000 Item 1 (f) Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Drill 9 holes for the passage of the attachments bolts Item (17) of the heat shield Item (16) on the doubler Item 1 to : Dia. mini. 5.0 mm (0.196 in.) Dia. mini. 5.1 mm (0.200 in.)

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 187 5

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# @A300 SERVICE BULLETIN

2 Before attaching the doubler Item 1, attach : 4 Plates Item (19) Retained at removal 1 Plate Item (20) Retained at removal with : 10 Rivet NSA5414-32-18 Item 3 3 Drill 12 holes for the Bolts Item 9 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 4 Drill 42 holes for the e Bolts Item 8 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 5 Drill 6 holes for the Bolts Item 6 : Dia. mini. 4.15 mm (0.163 in.) Dia. mini. 4.17 mm (0.164 in.) 6 Attach the doubler Item 1 : 12 Bolt NAS1153E7 Item 9 54 Nut NAS1726C3E Item 2 42 Bolt NAS1153E4 Item 8 6 Bolt NAS1152E3 Item 6 6 Nut MS21043-08 Item 5 12 Washer NAS1149CN832R Item 4 (g) Installation of the heat shield : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Heat Shield Item (16) Retained at removal 9 Bolt Item (17) Retained at removal
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 188 5

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# @A300 SERVICE BULLETIN
5 Shim or Washer Item (18) Retained at removal NOTE: Reduce the thickness of the original shims or washers Item 18 by 3 mm (0.118 in.) at location of the doubler Item 1 to keep the same gap at installation of the heat shield Item 16. (h) Do a new inspection as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. **CONF 004 (1) Subtask 540073-833-001-003 - Install the doubler on the LH Pylon Work Zones and Access Panels Zone Access/Work location 410 Manpower Resources Manhours 7.50 Minimum number of person 1 Subtask elapsed time 7.50 Skills AIRFRAME Material necessary to do the job Kit 540073A03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 54 NUT 3 NSA5414-32-18 10 RIVET 4 NAS1149CN832R 12 WASHER 5 MS21043-08 6 NUT 6 NAS1152E3 6 BOLT 7 NAS1153E6 12 BOLT 8 NAS1153E4 42 BOLT References Non Destructive Test Manual (NTM) 51-31-11 Part 1 - Procedure A 51-32-03 Part 1 51-33-02 Part 1 51-34-04 Part 1 Structural Repair Manual (SRM) 51-30-43 Fig. A-FBGAA Installation of Doubler under Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 189 5

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# @A300 SERVICE BULLETIN (a) Remove the heat shield between ribs 6 and 8 Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 1 Heat Shield Item (16) Retain 9 Bolts Item (17) Retain 5 Shim or Washer Item (18) Retain (b) Remove the rivets and plates : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 10 Rivets Item (3) Discard 4 Plates Item (19) Retain 1 Plate Item (20) Retain 2 Contersink at location of removed rivets Item (3) (Refer to SRM 51-30-43) to obtain a correct contact at location of doubler Item 1. (c) Drill two stop holes : 1 Drill two 6mm (0.236 in.) dia. holes at the ends of the crack. 2 Do an additional inspection after drilling of crack stop holes as specified below: Refer to NTM 51-31-11 Part 1 - Procedure A
a Calibration Standard: PN 99A53003001108 as per NTM 51-34-04 Part 1. - If crack is found, contact AIRBUS. (d) Remove the fasteners at ribs 6 and 7 : 1 Remove : 12 Rivet NSA5415-40 Item (7) Discard (e) Offer-up and position under lower spar : 1 Doubler R5460005520000 Item 1 (f) Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 190 5

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# @A300 SERVICE BULLETIN

1 Drill 9 holes for the passage of the attachments bolts Item (17) of the heat shield Item (16) on the doubler Item 1 to : Dia. mini. 5.0 mm (0.196 in.) Dia. mini. 5.1 mm (0.200 in.) 2 Before attaching the doubler Item 1, attach : 4 Plates Item (19) Retained at removal 1 Plate Item (20) Retained at removal with : 10 Rivet NSA5414-32-18 Item 3 3 Drill 12 holes for the Bolts Item 7 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 4 Drill 42 holes for the Bolts Item 8 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 5 Drill 6 holes for the Bolts Item 6 : Dia. mini. 4.15 mm (0.163 in.) Dia. mini. 4.17 mm (0.164 in.) 6 Attach the doubler Item 1 : 12 Bolt NAS1153E6 Item 7 54 Nut NAS1726C3E Item 2 42 Bolt NAS1153E4 Item 8 6 Bolt NAS1152E3 Item 6 6 Nut MS21043-08 Item 5 12 Washer NAS1149CN832R Item 4 (g) Installation of the heat shield : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 191 5

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# @A300 SERVICE BULLETIN
1 Heat Shield Item (16) Retained at removal 9 Bolt Item (17) Retained at removal 5 Shim or Washer Item (18) Retained at removal NOTE: Reduce the thickness of the original shims or washers Item 18 by 3 mm (0.118 in.) at location of the doubler Item 1 to keep the same gap at installation of the heat shield Item 16. (h) Do a new inspection as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. (2) Subtask 540073-833-002-002 - Install the doubler on the RH Pylon Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Manhours 7.50 Minimum number of person 1 Subtask elapsed time 7.50 Skills AIRFRAME Material necessary to do the job Kit 540073A03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 54 NUT 3 NSA5414-32-18 10 RIVET 4 NAS1149CN832R 12 WASHER 5 MS21043-08 6 NUT 6 NAS1152E3 6 BOLT 7 NAS1153E6 12 BOLT 8 NAS1153E4 42 BOLT References Non Destructive Test Manual (NTM) 51-31-11 Part 1 Procedure A 51-32-03 Part 1 51-33-02 Part 1 51-34-04 Part 1 Structural Repair Manual (SRM) 51-30-43

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 192 5

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# @A300 SERVICE BULLETIN

References Fig. A-FBGAA Installation of Doubler under Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 (a) Remove the heat shield between ribs 6 and 8 Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 1 Heat Shield Item (16) Retain 9 Bolts Item (17) Retain 5 Shim or Washer Item (18) Retain (b) Remove the rivets and plates : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 10 Rivets Item (3) Discard 4 Plates Item (19) Retain 1 Plate Item (20) Retain 2 Contersink at location of removed rivets Item (3) (Refer to SRM 51-30-43) to obtain a correct contact at location of doubler Item 1. (c) Drill two stop holes : 1 Drill two 6mm (0.236 in.) dia. holes at the ends of the crack. 2 Do an additional inspection after drilling of crack stop holes as specified below: Refer to NTM 51-31-11 Part 1 Procedure A
a Calibration Standard: PN 99A53003001108 as per NTM 51-34-04 Part 1. - If crack is found, contact AIRBUS. (d) Remove the fasteners at ribs 6 and 7 : 1 Remove : 12 Rivet NSA5415-40 Item (7) Discard

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 193 5

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# @A300 SERVICE BULLETIN (e) Offer-up and position under lower spar : 1 Doubler R5460005520000 Item 1 (f) Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Drill 9 holes for the passage of the attachments bolts Item (17) 1of the heat shield Item (16) on the doubler Item 1 to : Dia. mini. 5.0 mm (0.196 in.) Dia. mini. 5.1 mm (0.200 in.) 2 Before attaching the doubler Item 1, attach : 4 Plates Item (19) Retained at removal 1 Plate Item (20) Retained at removal with : 10 Rivet NSA5414-32-18 Item 3 3 Drill 12 holes for the Bolts Item 7 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 4 Drill 42 holes for the Bolts Item 8 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 5 Drill 6 holes for the Bolts Item 6 : Dia. mini. 4.15 mm (0.163 in.) Dia. mini. 4.17 mm (0.164 in.) 6 Attach the doubler Item 1 : 12 Bolt NAS1153E6 Item 7 54 Nut NAS1726C3E Item 2 42 Bolt NAS1153E4 Item 8 6 Bolt NAS1152E3 Item 6 DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 194 5

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# @A300 SERVICE BULLETIN

6 Nut MS21043-08 Item 5 12 Washer NAS1149CN832R Item 4 (g) Installation of the heat shield : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Heat Shield Item (16) Retained at removal 9 Bolt Item (17) Retained at removal 5 Shim or Washer Item (18) Retained at removal NOTE: Reduce the thickness of the original shims or washers Item 18 by 3 mm (0.118 in.) at location of the doubler Item 1 to keep the same gap at installation of the heat shield Item 16. (h) Do a new inspection as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. **CONF 005 (1) Subtask 540073-833-001-003 - Install the doubler on the LH Pylon Work Zones and Access Panels Zone Access/Work location 410 Manpower Resources Manhours 7.50 Minimum number of person 1 Subtask elapsed time 7.50 Skills AIRFRAME Material necessary to do the job Kit 540073A03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 54 NUT 3 NSA5414-32-18 10 RIVET 4 NAS1149CN832R 12 WASHER 5 MS21043-08 6 NUT 6 NAS1152E3 6 BOLT 7 NAS1153E6 12 BOLT
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 195 5

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# @A300 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 NAS1153E4 42 BOLT References Non Destructive Test Manual (NTM) 51-31-11 Part 1 - Procedure A 51-32-03 Part 1 51-33-02 Part 1 51-34-04 Part 1 Structural Repair Manual (SRM) 51-30-43 Fig. A-FBGAA Installation of Doubler under Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 (a) Remove the heat shield between ribs 6 and 8 Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 1 Heat Shield Item (16) Retain 9 Bolts Item (17) Retain 5 Shim or Washer Item (18) Retain (b) Remove the rivets and plates : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 10 Rivets Item (3) Discard 4 Plates Item (19) Retain 1 Plate Item (20) Retain 2 Contersink at location of removed rivets Item (3) (Refer to SRM 51-30-43) to obtain a correct contact at location of doubler Item 1. (c) Drill two stop holes : 1 Drill two 6mm (0.236 in.) dia. holes at the ends of the crack. 2 Do an additional inspection after drilling of crack stop holes as specified below: Refer to NTM 51-31-11 Part 1 - Procedure A

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 196 5

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# @A300 SERVICE BULLETIN

a Calibration Standard: PN 99A53003001108 as per NTM 51-34-04 Part 1. - If crack is found, contact AIRBUS. (d) Remove the fasteners at ribs 6 and 7 : 1 Remove : 12 Rivet NSA5415-40 Item (7) Discard (e) Offer-up and position under lower spar : 1 Doubler R5460005520000 Item 1 (f) Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Drill 9 holes for the passage of the attachments bolts Item (17) of the heat shield Item (16) on the doubler Item 1 to : Dia. mini. 5.0 mm (0.196 in.) Dia. mini. 5.1 mm (0.200 in.) 2 Before attaching the doubler Item 1, attach : 4 Plates Item (19) Retained at removal 1 Plate Item (20) Retained at removal with : 10 Rivet NSA5414-32-18 Item 3 3 Drill 12 holes for the Bolts Item 7 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 4 Drill 42 holes for the Bolts Item 8 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 5 Drill 6 holes for the Bolts Item 6 : Dia. mini. 4.15 mm (0.163 in.) Dia. mini. 4.17 mm (0.164 in.)
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 197 5

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# @A300 SERVICE BULLETIN

6 Attach the doubler Item 1 : 12 Bolt NAS1153E6 Item 7 54 Nut NAS1726C3E Item 2 42 Bolt NAS1153E4 Item 8 6 Bolt NAS1152E3 Item 6 6 Nut MS21043-08 Item 5 12 Washer NAS1149CN832R Item 4 (g) Installation of the heat shield : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Heat Shield Item (16) Retained at removal 9 Bolt Item (17) Retained at removal 5 Shim or Washer Item (18) Retained at removal NOTE: Reduce the thickness of the original shims or washers Item 18 by 3 mm (0.118 in.) at location of the doubler Item 1 to keep the same gap at installation of the heat shield Item 16. (h) Do a new inspection as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. (2) Subtask 540073-833-002-002 - Install the doubler on the RH Pylon Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Manhours 7.50 Minimum number of person 1 Subtask elapsed time 7.50 Skills AIRFRAME

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 198 5

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# @A300 SERVICE BULLETIN
Material necessary to do the job Kit 540073A03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 54 NUT 3 NSA5414-32-18 10 RIVET 4 NAS1149CN832R 12 WASHER 5 MS21043-08 6 NUT 6 NAS1152E3 6 BOLT 7 NAS1153E6 12 BOLT 8 NAS1153E4 42 BOLT References Non Destructive Test Manual (NTM) 51-31-11 Part 1 Procedure A 51-32-03 Part 1 51-33-02 Part 1 51-34-04 Part 1 Structural Repair Manual (SRM) 51-30-43 Fig. A-FBGAA Installation of Doubler under Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 (a) Remove the heat shield between ribs 6 and 8 Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 1 Heat Shield Item (16) Retain 9 Bolts Item (17) Retain 5 Shim or Washer Item (18) Retain (b) Remove the rivets and plates : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 10 Rivets Item (3) Discard 4 Plates Item (19) Retain 1 Plate Item (20) Retain 2 Contersink at location of removed rivets Item (3) (Refer to SRM 51-30-43) to obtain a correct contact at location of doubler Item 1.
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 199 5

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# @A300 SERVICE BULLETIN (c) Drill two stop holes : 1 Drill two 6mm (0.236 in.) dia. holes at the ends of the crack. 2 Do an additional inspection after drilling of crack stop holes as specified below: Refer to NTM 51-31-11 Part 1 Procedure A
a Calibration Standard: PN 99A53003001108 as per NTM 51-34-04 Part 1. - If crack is found, contact AIRBUS. (d) Remove the fasteners at ribs 6 and 7 : 1 Remove : 12 Rivet NSA5415-40 Item (7) Discard (e) Offer-up and position under lower spar : 1 Doubler R5460005520000 Item 1 (f) Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Drill 9 holes for the passage of the attachments bolts Item (17) 1of the heat shield Item (16) on the doubler Item 1 to : Dia. mini. 5.0 mm (0.196 in.) Dia. mini. 5.1 mm (0.200 in.) 2 Before attaching the doubler Item 1, attach : 4 Plates Item (19) Retained at removal 1 Plate Item (20) Retained at removal with : 10 Rivet NSA5414-32-18 Item 3 3 Drill 12 holes for the Bolts Item 7 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.)

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 200 5

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# @A300 SERVICE BULLETIN

4 Drill 42 holes for the Bolts Item 8 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 5 Drill 6 holes for the Bolts Item 6 : Dia. mini. 4.15 mm (0.163 in.) Dia. mini. 4.17 mm (0.164 in.) 6 Attach the doubler Item 1 : 12 Bolt NAS1153E6 Item 7 54 Nut NAS1726C3E Item 2 42 Bolt NAS1153E4 Item 8 6 Bolt NAS1152E3 Item 6 6 Nut MS21043-08 Item 5 12 Washer NAS1149CN832R Item 4 (g) Installation of the heat shield : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Heat Shield Item (16) Retained at removal 9 Bolt Item (17) Retained at removal 5 Shim or Washer Item (18) Retained at removal NOTE: Reduce the thickness of the original shims or washers Item 18 by 3 mm (0.118 in.) at location of the doubler Item 1 to keep the same gap at installation of the heat shield Item 16. (h) Do a new inspection as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. **CONF 006 (1) Subtask 540073-833-001-003 - Install the doubler on the LH Pylon Work Zones and Access Panels Zone Access/Work location 410
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 201 5

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# @A300 SERVICE BULLETIN
Manpower Resources Manhours 7.50 Minimum number of person 1 Subtask elapsed time 7.50 Skills AIRFRAME Material necessary to do the job Kit 540073A03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 54 NUT 3 NSA5414-32-18 10 RIVET 4 NAS1149CN832R 12 WASHER 5 MS21043-08 6 NUT 6 NAS1152E3 6 BOLT 7 NAS1153E6 12 BOLT 8 NAS1153E4 42 BOLT References Non Destructive Test Manual (NTM) 51-31-11 Part 1 - Procedure A 51-32-03 Part 1 51-33-02 Part 1 51-34-04 Part 1 Structural Repair Manual (SRM) 51-30-43 Fig. A-FBGAA Installation of Doubler under Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 (a) Remove the heat shield between ribs 6 and 8 Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 1 Heat Shield Item (16) Retain 9 Bolts Item (17) Retain 5 Shim or Washer Item (18) Retain (b) Remove the rivets and plates : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 10 Rivets Item (3) Discard

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 202 5

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# @A300 SERVICE BULLETIN
4 Plates Item (19) Retain 1 Plate Item (20) Retain 2 Contersink at location of removed rivets Item (3) (Refer to SRM 51-30-43) to obtain a correct contact at location of doubler Item 1. (c) Drill two stop holes : 1 Drill two 6mm (0.236 in.) dia. holes at the ends of the crack. 2 Do an additional inspection after drilling of crack stop holes as specified below: Refer to NTM 51-31-11 Part 1 - Procedure A
a Calibration Standard: PN 99A53003001108 as per NTM 51-34-04 Part 1. - If crack is found, contact AIRBUS. (d) Remove the fasteners at ribs 6 and 7 : 1 Remove : 12 Rivet NSA5415-40 Item (7) Discard (e) Offer-up and position under lower spar : 1 Doubler R5460005520000 Item 1 (f) Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Drill 9 holes for the passage of the attachments bolts Item (17) of the heat shield Item (16) on the doubler Item 1 to : Dia. mini. 5.0 mm (0.196 in.) Dia. mini. 5.1 mm (0.200 in.) 2 Before attaching the doubler Item 1, attach : 4 Plates Item (19) Retained at removal 1 Plate Item (20) Retained at removal with : 10 Rivet NSA5414-32-18 Item 3

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 203 5

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# @A300 SERVICE BULLETIN

3 Drill 12 holes for the Bolts Item 7 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 4 Drill 42 holes for the Bolts Item 8 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 5 Drill 6 holes for the Bolts Item 6 : Dia. mini. 4.15 mm (0.163 in.) Dia. mini. 4.17 mm (0.164 in.) 6 Attach the doubler Item 1 : 12 Bolt NAS1153E6 Item 7 54 Nut NAS1726C3E Item 2 42 Bolt NAS1153E4 Item 8 6 Bolt NAS1152E3 Item 6 6 Nut MS21043-08 Item 5 12 Washer NAS1149CN832R Item 4 (g) Installation of the heat shield : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Heat Shield Item (16) Retained at removal 9 Bolt Item (17) Retained at removal 5 Shim or Washer Item (18) Retained at removal NOTE: Reduce the thickness of the original shims or washers Item 18 by 3 mm (0.118 in.) at location of the doubler Item 1 to keep the same gap at installation of the heat shield Item 16. (h) Do a new inspection as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 204 5

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# @A300 SERVICE BULLETIN (2) Subtask 540073-833-002-002 - Install the doubler on the RH Pylon Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Manhours 7.50 Minimum number of person 1 Subtask elapsed time 7.50 Skills AIRFRAME Material necessary to do the job Kit 540073A03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 54 NUT 3 NSA5414-32-18 10 RIVET 4 NAS1149CN832R 12 WASHER 5 MS21043-08 6 NUT 6 NAS1152E3 6 BOLT 7 NAS1153E6 12 BOLT 8 NAS1153E4 42 BOLT References Non Destructive Test Manual (NTM) 51-31-11 Part 1 Procedure A 51-32-03 Part 1 51-33-02 Part 1 51-34-04 Part 1 Structural Repair Manual (SRM) 51-30-43 Fig. A-FBGAA Installation of Doubler under Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 (a) Remove the heat shield between ribs 6 and 8 Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 1 Heat Shield Item (16) Retain 9 Bolts Item (17) Retain 5 Shim or Washer Item (18) Retain

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 205 5

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# @A300 SERVICE BULLETIN (b) Remove the rivets and plates : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Remove : 10 Rivets Item (3) Discard 4 Plates Item (19) Retain 1 Plate Item (20) Retain 2 Contersink at location of removed rivets Item (3) (Refer to SRM 51-30-43) to obtain a correct contact at location of doubler Item 1. (c) Drill two stop holes : 1 Drill two 6mm (0.236 in.) dia. holes at the ends of the crack. 2 Do an additional inspection after drilling of crack stop holes as specified below: Refer to NTM 51-31-11 Part 1 Procedure A
a Calibration Standard: PN 99A53003001108 as per NTM 51-34-04 Part 1. - If crack is found, contact AIRBUS. (d) Remove the fasteners at ribs 6 and 7 : 1 Remove : 12 Rivet NSA5415-40 Item (7) Discard (e) Offer-up and position under lower spar : 1 Doubler R5460005520000 Item 1 (f) Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Drill 9 holes for the passage of the attachments bolts Item (17) 1of the heat shield Item (16) on the doubler Item 1 to : Dia. mini. 5.0 mm (0.196 in.) Dia. mini. 5.1 mm (0.200 in.) 2 Before attaching the doubler Item 1, attach : 4 Plates Item (19) Retained at removal
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 206 5

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# @A300 SERVICE BULLETIN
1 Plate Item (20) Retained at removal with : 10 Rivet NSA5414-32-18 Item 3 3 Drill 12 holes for the Bolts Item 7 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 4 Drill 42 holes for the Bolts Item 8 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 5 Drill 6 holes for the Bolts Item 6 : Dia. mini. 4.15 mm (0.163 in.) Dia. mini. 4.17 mm (0.164 in.) 6 Attach the doubler Item 1 : 12 Bolt NAS1153E6 Item 7 54 Nut NAS1726C3E Item 2 42 Bolt NAS1153E4 Item 8 6 Bolt NAS1152E3 Item 6 6 Nut MS21043-08 Item 5 12 Washer NAS1149CN832R Item 4 (g) Installation of the heat shield : Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 1 Heat Shield Item (16) Retained at removal 9 Bolt Item (17) Retained at removal 5 Shim or Washer Item (18) Retained at removal NOTE: Reduce the thickness of the original shims or washers Item 18 by 3 mm (0.118 in.) at location of the doubler Item 1 to keep the same DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 207 5

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# @A300 SERVICE BULLETIN gap at installation of the heat shield Item 16. (h) Do a new inspection as described in SUBTASK 540073-832-008 001 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. **CONF 007 (1) Subtask 540073-833-001-002 - Install the doubler on the LH Pylon Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Manhours 7.50 Minimum number of person 1 Subtask elapsed time 7.50 Skills AIRFRAME Material necessary to do the job Kit 540073A02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 60 NUT 3 NSA5414-32-18 10 RIVET 10 NAS6703U3 6 BOLT 11 NAS6703U4 42 BOLT 12 NAS6703U6 12 BOLT 13 NAS6703U8 9 BOLT 14 NAS6703U10 9 BOLT 15 NAS1149C0363R 9 WASHER References Non Destructive Test Manual (NTM) 51-31-11 Part 1 - Procedure A 51-32-03 Part 1 51-33-02 Part 1 51-34-04 Part 1 Structural Repair Manual (SRM) 51-30-43 Fig. A-FBHAA Installation of Doubler under Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 (a) Remove the heat shield between ribs 6 and 8 Refer to Fig. A-FBHAA Sheet 01 and Fig. A-FBHAA Sheet 02

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 208 5

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# @A300 SERVICE BULLETIN

1 Remove : 9 Blanking Bolts NSA6703U6 Item (13) Discard
or 9 Blanking Bolts NSA6703U8 Item (14) Discard and 9 Washer AN960C8 Item (15) Discard (b) Remove the rivets and plates : Refer to Fig. A-FBHAA Sheet 01 and Fig. A-FBHAA Sheet 02 1 Remove : 10 Rivet NSA5415-32 Item (3) Discard 4 Plates Item (19) Retain 1 Plate Item (20) Retain 2 Contersink at location of removed rivets Item (3) (Refer to SRM 51-30-43) to obtain a correct contact at location of doubler Item 1. (c) Drill two stop holes : 1 Drill two 6mm (0.236 in.) dia. holes at the ends of the crack. 2 Do an additional inspection after drilling of crack stop holes as specified below: Refer to NTM 51-31-11 Part 1 - Procedure A
a Calibration Standard: PN 99A53003001108 as per NTM 51-34-04 Part 1. - If crack is found, contact AIRBUS. (d) Remove the fasteners at ribs 6 and 7 : 1 Remove : 12 Rivets Item (7) Discard (e) Offer-up and position under lower spar : 1 Doubler R5460005520000 Item 1 (f) Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBHAA Sheet 01 and Fig. A-FBHAA Sheet 02

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 209 5

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# @A300 SERVICE BULLETIN

1 Drill 9 holes for the passage of the blanking bolts Item (13) or Item (14) on the doubler Item 1 to : Dia. mini. 5.0 mm (0.196 in.) Dia. mini. 5.1 mm (0.200 in.) 2 Before attaching the doubler Item 1, attach : 4 Plates Item (19) Retained at removal 1 Plate Item (20) Retained at removal with : 10 Rivet NSA5414-32-18 Item 3 3 Drill 12 holes for the Bolts Item 12 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 4 Drill 42 holes for the Bolts Item 11 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 5 Drill 6 holes for the Bolts Item 10 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 6 Attach the doubler Item 1 : 60 Nut NAS1726C3E Item 2 12 Bolt NAS6703U6 Item 12 42 Bolt NAS6703U4 Item 11 6 Bolt NAS6703U3 Item 10 (g) Installation of blanking bolts on plates Items 19 and 20 with: Refer to Fig. A-FBHAA Sheet 01 and Fig. A-FBHAA Sheet 02 9 Bolt NAS6703U8 Item 13 9 Bolt NAS6703U10 Item 14 DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 210 5

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# @A300 SERVICE BULLETIN
with : 9 Washer NAS1149C0363R Item 15 (h) Do a new inspection as described in SUBTASK 540073-832-008 002 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. (2) Subtask 540073-833-002-003 - Install the doubler on the RH Pylon Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Manhours 7.50 Minimum number of person 1 Subtask elapsed time 7.50 Skills AIRFRAME Material necessary to do the job Kit 540073A01R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 NSA5414-32-18 10 RIVET Kit 540073A02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 DOUBLER 2 NAS1726C3E 60 NUT 10 NAS6703U3 6 BOLT 11 NAS6703U4 42 BOLT 12 NAS6703U6 12 BOLT 13 NAS6703U8 9 BOLT 14 NAS6703U10 9 BOLT 15 NAS1149C0363R 9 WASHER References Non Destructive Test Manual (NTM) 51-31-11 Part 1 Procedure A 51-32-03 Part 1 51-33-02 Part 1 51-34-04 Part 1 Structural Repair Manual (SRM) 51-30-43 Fig. A-FBHAA Installation of Doubler under Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 211 5

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# @A300 SERVICE BULLETIN (a) Remove the heat shield between ribs 6 and 8 Refer to Fig. A-FBHAA Sheet 01 and Fig. A-FBHAA Sheet 02 1 Remove : 9 Blanking Bolts NSA6703U6 Item (13) Discard
or 9 Blanking Bolts NSA6703U8 Item (14) Discard 9 Washer AN960C8 Item (15) Discard (b) Remove the rivets and plates : Refer to Fig. A-FBHAA Sheet 01 and Fig. A-FBHAA Sheet 02 1 Remove : 10 Rivet NSA5415-32 Item (3) Discard 4 Plates Item (19) Retain 1 Plate Item (20) Retain 2 Contersink at location of removed rivets Item (3) (Refer to SRM 51-30-43) to obtain a correct contact at location of doubler Item 1. (c) Drill two stop holes : 1 Drill two 6mm (0.236 in.) dia. holes at the ends of the crack. 2 Do an additional inspection after drilling of crack stop holes as specified below: Refer to NTM 51-31-11 Part 1 Procedure A
a Calibration Standard: PN 99A53003001108 as per NTM 51-34-04 Part 1. - If crack is found, contact AIRBUS. (d) Remove the fasteners at ribs 6 and 7 : 1 Remove : 12 Rivets Item (7) Discard (e) Offer-up and position under lower spar : 1 Doubler R5460005520000 Item 1

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 212 5

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# @A300 SERVICE BULLETIN (f) Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBHAA Sheet 01 and Fig. A-FBHAA Sheet 02 1 Drill 9 holes for the passage of the blanking bolts Item (13) or Item (14) on the doubler Item 1 to : Dia. mini. 5.0 mm (0.196 in.) Dia. mini. 5.1 mm (0.200 in.) 2 Before attaching the doubler Item 1, attach : 4 Plates Item (19) Retained at removal 1 Plate Item (20) Retained at removal with : 10 Rivet NSA5414-32-18 Item 3 3 Drill 12 holes for the Bolts Item 12 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 4 Drill 42 holes for the Bolts Item 11 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 5 Drill 6 holes for the Bolts Item 10 : Dia. mini. 4.81 mm (0.190 in.) Dia. mini. 4.83 mm (0.191 in.) 6 Attach the doubler Item 1 : 60 Nut NAS1726C3E Item 2 12 Bolt NAS6703U6 Item 12 42 Bolt NAS6703U4 Item 11 6 Bolt NAS6703U3 Item 10 (g) Installation of blanking bolts on plates Items 19 and 20 with: Refer to Fig. A-FBHAA Sheet 01 and Fig. A-FBHAA Sheet 02
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 213 5

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# @A300 SERVICE BULLETIN

9 Bolt NAS6703U8 Item 13 9 Bolt NAS6703U10 Item 14 with : 9 Washer NAS1149C0363R Item 15 (h) Do a new inspection as described in SUBTASK 540073-832-008 002 Do a Special Detailed Inspection of the LH / RH Engine Pylon Post repair. **CONF ALL D. TEST **CONF 001 (1) Subtask 540073-700-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the engines (refer to SUBTASK 540073-942-001 001 and SUBTASK 540073-942-003 001) before accomplishment of the test below. (a) Job set-up: - Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit breaker(s) as specified after the installation of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Procedure: - Do the Test procedure as specified after the installation of the power plant (Refer to AMM 71-00-00, Page Block 401). **CONF 002 (1) Subtask 540073-700-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the engines (refer to SUBTASK 540073-942-001 001 and SUBTASK 540073-942-003 001) before accomplishment of the test below. DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 214 5

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# @A300 SERVICE BULLETIN (a) Job set-up: - Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit breaker(s) as specified after the installation of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Procedure: - Do the Test procedure as specified after the installation of the power plant (Refer to AMM 71-00-00, Page Block 401). **CONF 003 (1) Subtask 540073-700-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the engines (refer to SUBTASK 540073-942-001 001 and SUBTASK 540073-942-003 001) before accomplishment of the test below. (a) Job set-up: - Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit breaker(s) as specified after the installation of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Procedure: - Do the Test procedure as specified after the installation of the power plant (Refer to AMM 71-00-00, Page Block 401). **CONF 004 (1) Subtask 540073-700-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the engines (refer to SUBTASK 540073-942-001 001 and SUBTASK 540073-942-003 001) before accomplishment of the test below.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 215 5

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# @A300 SERVICE BULLETIN (a) Job set-up: - Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit breaker(s) as specified after the installation of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Procedure: - Do the Test procedure as specified after the installation of the power plant (Refer to AMM 71-00-00, Page Block 401). **CONF 005 (1) Subtask 540073-700-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the engines (refer to SUBTASK 540073-942-001 001 and SUBTASK 540073-942-003 001) before accomplishment of the test below. (a) Job set-up: - Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit breaker(s) as specified after the installation of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Procedure: - Do the Test procedure as specified after the installation of the power plant (Refer to AMM 71-00-00, Page Block 401). **CONF 006 (1) Subtask 540073-700-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the engines (refer to SUBTASK 540073-942-001 001 and SUBTASK 540073-942-003 001) before accomplishment of the test below.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 216 5

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# @A300 SERVICE BULLETIN (a) Job set-up: - Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit breaker(s) as specified after the installation of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Procedure: - Do the Test procedure as specified after the installation of the power plant (Refer to AMM 71-00-00, Page Block 401). **CONF 007 (1) Subtask 540073-700-001-001 - Test Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the engines (refer to SUBTASK 540073-942-001 001 and SUBTASK 540073-942-003 001) before accomplishment of the test below. (a) Job set-up: - Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit breaker(s) as specified after the installation of the power plant (Refer to AMM 71-00-00, Page Block 401). (b) Procedure: - Do the Test procedure as specified after the installation of the power plant (Refer to AMM 71-00-00, Page Block 401). **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 540073-942-001-001 - Install the LH Engine. Work Zones and Access Panels Zone Access/Work location 410 Manpower Resources Skills NON SPECIFIC

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 217 5

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# @A300 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-001 001). (a) Install the Left Engine (Refer to AMM 71-00-00, Page Block 401). (2) Subtask 540073-942-003-001 - Install the RH Engine Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-001 001). (a) Install the Right Engine (Refer to AMM 71-00-00, Page Block 401). **CONF 002 (1) Subtask 540073-942-001-001 - Install the LH Engine. Work Zones and Access Panels Zone Access/Work location 410 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-001 001). (a) Install the Left Engine (Refer to AMM 71-00-00, Page Block 401). (2) Subtask 540073-942-003-001 - Install the RH Engine Work Zones and Access Panels Zone Access/Work location 420

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 218 5

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# @A300 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-001 001). (a) Install the Right Engine (Refer to AMM 71-00-00, Page Block 401). **CONF 003 (1) Subtask 540073-942-001-001 - Install the LH Engine. Work Zones and Access Panels Zone Access/Work location 410 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-001 001). (a) Install the Left Engine (Refer to AMM 71-00-00, Page Block 401). (2) Subtask 540073-942-003-001 - Install the RH Engine Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-001 001). (a) Install the Right Engine (Refer to AMM 71-00-00, Page Block 401).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 219 5

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# @A300 SERVICE BULLETIN
**CONF 004 (1) Subtask 540073-942-001-001 - Install the LH Engine. Work Zones and Access Panels Zone Access/Work location 410 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-001 001). (a) Install the Left Engine (Refer to AMM 71-00-00, Page Block 401). (2) Subtask 540073-942-003-001 - Install the RH Engine Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-001 001). (a) Install the Right Engine (Refer to AMM 71-00-00, Page Block 401). **CONF 005 (1) Subtask 540073-942-001-001 - Install the LH Engine. Work Zones and Access Panels Zone Access/Work location 410 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 220 5

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# @A300 SERVICE BULLETIN accomplishment of the test (Refer to SUBTASK 540073-700-001 001). (a) Install the Left Engine (Refer to AMM 71-00-00, Page Block 401). (2) Subtask 540073-942-003-001 - Install the RH Engine Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-001 001). (a) Install the Right Engine (Refer to AMM 71-00-00, Page Block 401). **CONF 006 (1) Subtask 540073-942-001-001 - Install the LH Engine. Work Zones and Access Panels Zone Access/Work location 410 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-001 001). (a) Install the Left Engine (Refer to AMM 71-00-00, Page Block 401). (2) Subtask 540073-942-003-001 - Install the RH Engine Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 221 5

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

# @A300 SERVICE BULLETIN
NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-001 001). (a) Install the Right Engine (Refer to AMM 71-00-00, Page Block 401). **CONF 007 (1) Subtask 540073-942-001-001 - Install the LH Engine. Work Zones and Access Panels Zone Access/Work location 410 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-001 001). (a) Install the Left Engine (Refer to AMM 71-00-00, Page Block 401). (2) Subtask 540073-942-003-001 - Install the RH Engine Work Zones and Access Panels Zone Access/Work location 420 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 NOTE: Install the bleed air precooler cold air inlet duct and the precooler before accomplishment of the test (Refer to SUBTASK 540073-700-001 001). (a) Install the Right Engine (Refer to AMM 71-00-00, Page Block 401).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 222 5

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# @A300 SERVICE BULLETIN

**CONF 001 thru 006

RIB9 RIB8

AREAS TO BE INSPECTED **F W**  **D** LOWER SPAR 

## A RIB18

RIB12

RIB6 RIB8 RIB7 

### A **B**

**NOTE:** 

## B

A_SB_540073_5_BAAA_01_00 RIB7 RIB6

Figure A-FBAAA - Sheet 01 Areas to Be Inspected Pre Repair and Pre SB 54-0080
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 223 5

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# @A300 SERVICE BULLETIN

**CONF 001 thru 006

A_SB_540073_5_BCAA_01_00 RIB9 RIB8

AREAS TO BE INSPECTED **F W**  **D** LOWER SPAR 

## A RIB18

RIB12

RIB6 RIB8 RIB7 

### A **B**

**NOTE:** 

## B RIB7 RIB6

Figure A-FBCAA - Sheet 01 Areas to Be Inspected Post SB 54-0080
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 224 5

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# @A300 SERVICE BULLETIN

**CONF 001 thru 006

RIB8

**NOTE:** AREAS TO BE INSPECTED 01 **F W**  **D** RIB6 RIB7 RIB9

AREA 1 02 LOWER SPAR 

## A RIB18

RIB12
RIB8 RIB7 RIB6

A_SB_540073_5_BBAA_01_00 AREA 2 FASTENERS 

### A

02

02 01 

### B



## B

Figure A-FBBAA - Sheet 01 Areas to Be Inspected Post Repair
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 225 5

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# @A300 SERVICE BULLETIN

**CONF 007



## A

**B**

AREA TO BE INSPECTED **F W**  **D** RIB9 

### A

A_SB_540073_5_BDAA_01_00 LOWER SPAR RIB18

RIB12

RIB6 RIB8 RIB7 

### B

RIB8

RIB7 RIB6

**NOTE:**

Figure A-FBDAA - Sheet 01 Areas to Be Inspected Pre Repair and Pre SB 54-0080
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 226 5

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# @A300 SERVICE BULLETIN

**CONF 007



## A

**B**

AREAS TO BE INSPECTED **F W**  **D** RIB9 

### A

A_SB_540073_5_BFAA_01_00 **NOTE:** RIB8 LOWER SPAR RIB18

RIB12

RIB6 RIB8 RIB7 

### B

RIB7 RIB6

Figure A-FBFAA - Sheet 01 Areas to Be Inspected Post SB 54-0080
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 227 5

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# @A300 SERVICE BULLETIN

**CONF 007



## A

**B**

AREAS TO BE INSPECTED **F W**  **D** 02

02 01

01 02 AREA 1 AREA 2 FASTENERS **NOTE:**

A_SB_540073_5_BEAA_01_00 

### A

LOWER SPAR RIB18

RIB12

RIB6 RIB8 RIB7 

### B

RIB9 RIB8

RIB7 RIB6

Figure A-FBEAA - Sheet 01 Areas to Be Inspected Post Repair
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 228 5

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# @A300 SERVICE BULLETIN

**CONF 001 thru 003

QUESTION

FINDING ACTION CRACK FINDING

CONTACT AIRBUS BEFORE NEXT FLIGHT YES NO OR

NO YES CRACK FINDING

CONTACT AIRBUS BEFORE NEXT FLIGHT CRACK 20 mm (0.787 in.) CRACK BETWEEN 20 mm (0.787 in.) AND 25 mm (0.984 in.) CRACK 25 mm (0.984 in.)

DO A SPECIAL DETAILED EDDY CURRENT INSPECTION OR LIQUID PENETRANT INSPECTION AT THE THRESHOLD GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2) CRACK FINDING NO FROM THE INSIDE, DO A SPECIAL DETAILED EDDY CURRENT INSPECTION OR LIQUID PENETRANT INSPECTION (REFER TO SUBTASK 540073−832−001−001) IN THE LOWER SPAR AXIS BETWEEN RIBS 6 AND 7 AT THE THRESHOLD GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2)

YES CRACK FINDING NO YES

REPAIR BEFORE 500 FC DO A SPECIAL DETAILED EDDY CURRENT INSPECTION AND LIQUID PENETRANT INSPECTION (REFER TO SUBTASK 540073−832−005−001)

(REFER TO SUBTASK 540073−833−001−001 AND 540073−833−002−001) REPAIR BEFORE 250 FC (REFER TO SUBTASK 540073−833−001−001 AND 540073−833−002−001)

(REFER TO SUBTASK 540073−832−008−001)

EDDY CURRENT INSPECTION OR LIQUID PENETRANT INSPECTION AT THE INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2) (REFER TO SUBTASK 540073−832−008−001) RE−INSPECT BY A SPECIAL DETAILED EDDY CURRENT INSPECTION OR LIQUID PENETRANT INSPECTION AT THE INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2) (REFER TO SUBTASK 540073−832−009−001) RE−INSPECT BY A SPECIAL DETAILED OR
APPLY SERVICE BULLETIN No. A300−54−0080 (10335S20434) EDDY CURRENT INSPECTION OR LIQUID PENETRANT INSPECTION AT THE INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2) (REFER TO SUBTASK 540073−832−001−001) RE−INSPECT BY A SPECIAL DETAILED

DO A SPECIAL DETAILED EDDY CURRENT INSPECTION OR LIQUID PENETRANT INSPECTION AT THE THRESHOLD GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2) (REFER TO SUBTASK 540073−832−009−001)

A_SB_540073_5_FAAA_01_04 Figure A-FFAAA - Sheet 01 Flow Chart
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 229 5

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# @A300 SERVICE BULLETIN

**CONF 004 thru 007

QUESTION

FINDING ACTION CRACK FINDING

CONTACT AIRBUS BEFORE NEXT FLIGHT YES NO OR

NO YES CRACK FINDING

CONTACT AIRBUS BEFORE NEXT FLIGHT CRACK 30 mm (1.181 in.) CRACK BETWEEN 30 mm (1.181 in.) AND 35 mm (1.378 in.) CRACK 35 mm (1.378 in.)

DO A SPECIAL DETAILED EDDY CURRENT INSPECTION OR LIQUID PENETRANT INSPECTION AT THE THRESHOLD GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2) CRACK FINDING NO FROM THE INSIDE, DO A SPECIAL DETAILED EDDY CURRENT INSPECTION OR LIQUID PENETRANT INSPECTION (REFER TO SUBTASK 540073−832−001−001) IN THE LOWER SPAR AXIS BETWEEN RIBS 6 AND 7 AT THE THRESHOLD GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2)

YES CRACK FINDING NO YES

REPAIR BEFORE 500 FC DO A SPECIAL DETAILED EDDY CURRENT INSPECTION AND LIQUID PENETRANT INSPECTION (REFER TO SUBTASK 540073−832−005−001)

(REFER TO SUBTASK 540073−833−001−001 AND 540073−833−002−001) REPAIR BEFORE 250 FC (REFER TO SUBTASK 540073−833−001−001 AND 540073−833−002−001)

(REFER TO SUBTASK 540073−832−008−001)

EDDY CURRENT INSPECTION OR LIQUID PENETRANT INSPECTION AT THE INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2) (REFER TO SUBTASK 540073−832−008−001) RE−INSPECT BY A SPECIAL DETAILED EDDY CURRENT INSPECTION OR LIQUID PENETRANT INSPECTION AT THE INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2) (REFER TO SUBTASK 540073−832−009−001) RE−INSPECT BY A SPECIAL DETAILED OR
APPLY SERVICE BULLETIN No. A300−54−0080 (10335S20434) EDDY CURRENT INSPECTION OR LIQUID PENETRANT INSPECTION AT THE INTERVAL GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2) (REFER TO SUBTASK 540073−832−001−001) RE−INSPECT BY A SPECIAL DETAILED

DO A SPECIAL DETAILED EDDY CURRENT INSPECTION OR LIQUID PENETRANT INSPECTION AT THE THRESHOLD GIVEN IN PLANNING INFORMATION PARAGRAPH E.(2) (REFER TO SUBTASK 540073−832−009−001)

A_SB_540073_5_FBAA_01_03 Figure A-FFBAA - Sheet 01 Flow Chart
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 230 5

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# @A300 SERVICE BULLETIN

**CONF 001 thru 006
3 (3) (19) 3 (3)

(17) (17) (17) (16)

(18) 1

(17)

(16) (16)

1 (18) (18) 1

ITEM 18 ORIGINAL SHIMS TO BE REMOVED AND MACHINED 3 mm (0.118 in.) OUT OF DOUBLER AREA X = 20 mm (0.787 in.) NEW ITEM OLD ITEM LOCATION EXISTING HOLES BASIC PYLON COMMON PYLON EXISTING HOLES NEW HOLES NEW HOLES (20)

TO STOP THE CRACKXX

X

(19) (19) (19)

(17) X

(3)
3 (3) (19)

(17) RIB8 RIB7 RIB6

(17)

(17) 15 mm 12 mm (0.472 in.) (0.590 in.)

15 mm (0.590 in.)

12 mm (0.472 in.) **FWD** 

### B **B**

**A A** 

**C C** 

8

−2 3 (3) 3 (3) (3) 3 (3) 3 (3) 3 (3) 3



## C **C B**  **B**

**NOTE 1:**

**NOTE 2:** 

## A **A**

**B** LOWER SPAR 

### B



## A RIB6

RIB7 RIB8 RIB12 RIB18 

### A

(7) 9

−2

8

−2 7

−2

6

−5

−4 (7) 8

−2 8

−2

8

−2

* * * * (18) *XR:10 mm(0.393 in.)40 mm(1.574 in.)MAXI

3R:10 mm(0.393 in.)X HOLE

KIT N°. A01 (19)

A_SB_540073_5_BGAA_01_01 Figure A-FBGAA - Sheet 01 Installation of Doubler under Lower Spar between Ribs 6 and 7
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 231 5

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# @A300 SERVICE BULLETIN

**CONF 001 thru 006

FINAL REAMING
MINI MAXI H O L E Q T Y I T E M I T E M NUT

4.81 mm (0.190 in.) 4.83 mm (0.191 in.) NAS 1726C3E 12

4.81 mm (0.190 in.) 4.83 mm (0.191 in.) NAS 1153E4 NAS 1726C3E 42

4.15 mm (0.163 in.) 4.17 mm (0.164 in.) NAS 1152E3 MS 21043−08 6 BOLT

A_SB_540073_5_BGAA_02_00 I T E M

AN 960C8 QTY: 6+6 WASHER

OR NAS 1153E6 OR NAS 1153E7 7 9

8

6 2

2

5 4

Figure A-FBGAA - Sheet 02 Installation of Doubler under Lower Spar between Ribs 6 and 7
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 232 5

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# @A300 SERVICE BULLETIN

**CONF 007

TO STOP THE CRACKXX

(19) (19) (19)

(13)

(3)
3 (3) (19)

(13) RIB8 RIB7 RIB6 3 (3) (19) 3 (3)

1 1

X = 20 mm (0.787 in.) NEW ITEM OLD ITEM LOCATION EXISTING HOLES NEW HOLES NEW HOLES (13)

13 14

−15

OR (13) (14)

−(15) OR (13) (14) (15) 13 14

− OR OR 15

− (20)

(13) 3 (3)

15 mm (0.590 in.)

15 mm (0.590 in.) **FWD** 

## A **A**

**B B** 

**C C**  (7) 12

−2

10

−2 11

−2 

### B **B**

**A A** 

**C C** 

**NOTE:** 11

−2 11

−2 3 (3) 3 (3) (3) 3 (3) 3 11

−2 (3) 3 (3) 3 11

−2

LOWER SPAR 

### B



## A RIB6

RIB7 RIB8 RIB12 RIB18 

### A



## B 12 mm (0.472 in.)

XXR:10 mm(0.393 in.)40 mmMAXIR:10 mm(0.393 in.)(1.574 in.)

X
3X

(19)
12 mm (0.472 in.) HOLE

1

KIT N°. A02

A_SB_540073_5_BHAA_01_01 Figure A-FBHAA - Sheet 01 Installation of Doubler under Lower Spar between Ribs 6 and 7
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 233 5

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# @A300 SERVICE BULLETIN

**CONF 007

A_SB_540073_5_BHAA_02_00 FINAL REAMING
MINI MAXI H O L E Q T Y I T E M I T E M NUT

4.81 mm (0.190 in.) 4.83 mm (0.191 in.) NAS 6703U6 NAS 1726C3E 12

4.81 mm (0.190 in.) 4.83 mm (0.191 in.) NAS 6703U4 NAS 1726C3E 42

4.81 mm (0.190 in.) 4.83 mm (0.191 in.) NAS 6703U3 NAS 1726C3E 6 BOLT

12

11

10 2

2

2

Figure A-FBHAA - Sheet 02 Installation of Doubler under Lower Spar between Ribs 6 and 7
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 234 5

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# @A300 SERVICE BULLETIN Appendix 01- Inspection Report **CONF ALL The results of the inspection, including no findings, replacement or action to be done, must be forwarded to AIRBUS Departement SEES2, on the attached inspection report sheet.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 1 5

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# @A300 SERVICE BULLETIN Appendix 01- Inspection Report

**CONF 001 thru 006

**INSPECTION REPORT** SERVICE BULLETIN N° : A300−54−0073 A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : DATE OF INSPECTION :

CRACK NO CRACK INSPECTION LENGTH PYLON LEFT

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: INSPECTION METHOD : EDDY CURRENT

PYLON RIGHT

A_SB_540073_5_RAAA_01_00 LIQUID PENETRANT RIB9 RIB8

RIB7 **F W**  **D**

AREA REPAIRED IN ACCORDANCE WITH : SERVICE BULLETIN A300−54−0073 AREA TO BE INSPECTED **NOTE:** LENGTH RIB6 RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES2 WING FIX STRUCTURE − ENGINE PYLON 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX + 33 (0)5 61 93 36 14

CONFIG. 1 CONFIG. 2 CONFIG. 3 CONFIG. 4 CONFIG. 5 CONFIG. 6

Figure A-FRAAA - Sheet 01 Inspection Report
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 2 5

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# @A300 SERVICE BULLETIN Appendix 01- Inspection Report

**CONF 001 thru 006

**INSPECTION REPORT**

SERVICE BULLETIN N° : A300−54−0073 A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : DATE OF INSPECTION :

CRACK NO CRACK INSPECTION CONFIG. 1 LENGTH PYLON LEFT

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: INSPECTION METHOD : LIQUID PENETRANT RETURN TO : AIRBUS

EDDY CURRENT

CONFIG. 2 CONFIG. 3 AREA 1 AREA 2 PYLON RIGHT AREA 1 AREA 2 AFTER REPAIR IN ACCORDANCE WITH SB 54−0073

RIB8

**NOTE:** AREAS TO BE INSPECTED 01 **F W**  **D** RIB6 RIB7 RIB9

AREA 1 02 AREA 2 FASTENERS 02

02 01

A_SB_540073_5_RAAA_02_00 CONFIG. 4 CONFIG. 5 CONFIG. 6 CUSTOMER SERVICES ENGINEERING − SEES2 WING FIX STRUCTURE − ENGINE PYLON 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX + 33 (0)5 61 93 36 14

Figure A-FRAAA - Sheet 02 Inspection Report
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 3 5

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# @A300 SERVICE BULLETIN Appendix 01- Inspection Report

**CONF 001 thru 006

**INSPECTION REPORT**

SERVICE BULLETIN N° : A300−54−0073 A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : DATE OF INSPECTION :

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: INSPECTION METHOD : LIQUID PENETRANT EDDY CURRENT RIB8

AREAS TO BE INSPECTED **F W**  **D** RIB6 RIB7 RIB9 AFTER EMBODIMENT OF THE SEVICE BULLETIN A300−54−0080 (MOD. NO. 10335S20434)

A_SB_540073_5_RAAA_03_00 **NOTE:** CRACK NO CRACK INSPECTION LENGTH PYLON LEFT
PYLON RIGHTRETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES2 WING FIX STRUCTURE − ENGINE PYLON 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX + 33 (0)5 61 93 36 14

CONFIG. 1 CONFIG. 2 CONFIG. 3 CONFIG. 4 CONFIG. 5 CONFIG. 6 AREA 1
AREA 1

Figure A-FRAAA - Sheet 03 Inspection Report
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 4 5

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# @A300 SERVICE BULLETIN Appendix 01- Inspection Report

**CONF 007

**INSPECTION REPORT** SERVICE BULLETIN N° : A300−54−0073 A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : DATE OF INSPECTION :

CRACK NO CRACK INSPECTION

CONFIG. 7 LENGTH PYLON LEFT

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: INSPECTION METHOD : LIQUID PENETRANT EDDY CURRENT

PYLON RIGHT

AREA TO BE INSPECTED **F W**  **D** RIB9

AREA REPAIRED IN ACCORDANCE WITH : SERVICE BULLETIN A300−54−0073
A_SB_540073_5_RBAA_01_00 LENGTH **NOTE:** RIB8

RIB7 RIB6 RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES2 WING FIX STRUCTURE − ENGINE PYLON 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX + 33 (0)5 61 93 36 14

Figure A-FRBAA - Sheet 01 Inspection Report
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 5 5

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

# @A300 SERVICE BULLETIN Appendix 01- Inspection Report

**CONF 007

CRACK NO CRACK INSPECTION

CONFIG. 7 LENGTH PYLON LEFT

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: AREA 1 AREA 2 PYLON RIGHT AREA 1 AREA 2

AREAS TO BE INSPECTED **F W**  **D** RIB9

02

02 01

01 02 AREA 1 AREA 2 FASTENERS **NOTE: INSPECTION REPORT**  AFTER REPAIR IN ACCORDANCE WITH SB 54−0073 SERVICE BULLETIN N° : A300−54−0073 A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : DATE OF INSPECTION : INSPECTION METHOD : LIQUID PENETRANT EDDY CURRENT

A_SB_540073_5_RBAA_02_00 RIB8

RIB7 RIB6 RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES2 WING FIX STRUCTURE − ENGINE PYLON 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX + 33 (0)5 61 93 36 14

Figure A-FRBAA - Sheet 02 Inspection Report
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 6 5

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

# @A300 SERVICE BULLETIN Appendix 01- Inspection Report

**CONF 007

PLEASE PRECISE OTHER FINDINGS THAN CORROSION: AREAS TO BE INSPECTED **F W**  **D** RIB9

02

02 01

01 02 AREA 1 AREA 2 FASTENERS **NOTE: INSPECTION REPORT** 

SERVICE BULLETIN N° : A300−54−0073 A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : DATE OF INSPECTION : INSPECTION METHOD : LIQUID PENETRANT EDDY CURRENT AFTER EMBODIMENT OF THE SEVICE BULLETIN A300−54−0080 (MOD. NO. 10335S20434)

A_SB_540073_5_RBAA_03_00 CRACK NO CRACK INSPECTION

CONFIG. 7 LENGTH PYLON LEFT AREA 1 AREA 2 PYLON RIGHT AREA 1 AREA 2 RIB8

RIB7 RIB6 RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES2 WING FIX STRUCTURE − ENGINE PYLON 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX + 33 (0)5 61 93 36 14

Figure A-FRBAA - Sheet 03 Inspection Report
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 7 5

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# @A300 SERVICE BULLETIN REPORTING SHEET 

### TITLE: NACELLES/PYLON - INSPECT PYLON LOWER SPAR BETWEEN RIBS 6 AND 7 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: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 1 5

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# @A300 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: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073 REVISION No.: 03 - Oct 11/12 Page: 1 5

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