@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

MANDATORY MANDATORY MANDATORY

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

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

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

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

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

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

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

MANDATORY MANDATORY MANDATORY

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

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

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

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

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

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

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

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

SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 8

5

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

MANDATORY MANDATORY MANDATORY

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

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

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

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

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

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

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

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

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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.

Condition Action Compliance Time

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.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 10

5

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

SERVICE BULLETIN

Condition Action Compliance Time

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.

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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.

Condition Action Compliance Time

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

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

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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.

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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.

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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.

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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.

Condition Action Compliance Time

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

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

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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.

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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.

Condition Action Compliance Time

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

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

SERVICE BULLETIN

Condition Action Compliance Time

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 540073-832-801-001 - Inspection Pre Repair and 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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 63

5

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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 64

5

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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 65

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 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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 66

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: 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

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-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

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

SERVICE BULLETIN

c Re-inspect the area as described in SUBTASK 540073-832-001 003 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

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

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

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

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

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

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

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

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

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

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

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 94

5

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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 95

5

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

SERVICE BULLETIN

- Re-inspect the area as described in SUBTASK 540073-832-009 001 Do

a 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

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

a 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

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

a 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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 142

5

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

a 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

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

a 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

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

a 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

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

a 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

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

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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 148

5

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

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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 150

5

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

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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 152

5

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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 153

5

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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 154

5

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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 155

5

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

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 156

5

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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 157

5

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

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

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

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

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

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

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

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

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

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

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

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

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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 170

5

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

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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-0073

REVISION No.: 03 - Oct 11/12 Page: 172

5

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

RIB6 RIB7

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

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

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

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

RIB6 RIB7

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

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

RIB6 RIB7

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

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

SERVICE BULLETIN

**CONF 001 thru 003

QUESTION

FINDING

ACTION

CRACK FINDING

CONTACT AIRBUS

BEFORE NEXT FLIGHT

YES NO

OR

NO CRACK FINDING YES

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

YES CRACK FINDING NO

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

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

SERVICE BULLETIN

**CONF 004 thru 007

QUESTION

FINDING

ACTION

CRACK FINDING

CONTACT AIRBUS

BEFORE NEXT FLIGHT

YES NO

OR

NO CRACK FINDING YES

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

YES CRACK FINDING NO

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

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

SERVICE BULLETIN

**CONF 001 thru 006

3

(3) (19) 3

(3)

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

(18)

1

(17)

(16)

(16)

1

1 (18) (18)

ITEM 18

ORIGINAL SHIMS TO BE REMOVED

AND MACHINED 3 mm (0.118 in.)

OUT OF DOUBLER AREA

X = 20 mm (0.787 in.)

LOCATION OLD ITEM NEW ITEM

BASIC PYLON EXISTING HOLES

COMMON PYLON EXISTING HOLES

NEW HOLES

NEW HOLES

(20)

TO STOP THE CRACK

X

X

X

(19)

(19) (19)

(17)

X

(3)

3

(3) (19)

(17)

RIB6 RIB7 RIB8

(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) *

X

R:10 mm

(0.393 in.)

40 mm

(1.574 in.)

MAXI

3

R: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

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@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.) 12 NAS 1726C3E

4.81 mm

(0.190 in.)

4.83 mm

(0.191 in.) 42 NAS 1153E4 NAS 1726C3E

4.15 mm

(0.163 in.)

4.17 mm

(0.164 in.) 6 NAS 1152E3 MS 21043−08

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

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

SERVICE BULLETIN

**CONF 007

TO STOP THE CRACK

X

X

(19)

(19) (19)

(13)

(3)

3

(3) (19)

(13)

RIB6 RIB7 RIB8

3

(3) (19) 3

(3)

1

1

 X = 20 mm (0.787 in.)

LOCATION OLD ITEM NEW ITEM

EXISTING HOLES

NEW HOLES

NEW HOLES

(13)

13

14 −15

OR

(13)

(14) − (15)

OR

(13) (14) (15)

13 14 OR − OR15

−

(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.)

X

X

R:10 mm

(0.393 in.)

40 mm

MAXI

R:10 mm

(0.393 in.)

(1.574 in.)

X

3

X

(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

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@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.) 12 NAS 6703U6 NAS 1726C3E

4.81 mm

(0.190 in.)

4.83 mm

(0.191 in.) 42 NAS 6703U4 NAS 1726C3E

4.81 mm

(0.190 in.)

4.83 mm

(0.191 in.) 6 NAS 6703U3 NAS 1726C3E

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

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

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

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

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

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

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

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

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

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

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