# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 54 

### TITLE: NACELLES/PYLON - INSPECT PYLON LOWER SPAR BETWEEN RIBS 6 AND 7. MODIFICATION No.: None This page transmits Revision No.07 of Service Bulletin No.A300-54-6014 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision 07 issued to correct a discrepancy between kit revision in this Service Bulletin and current LOC. CHANGES SUMMARY MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE UPDATED R MATERIAL PRICE INFORMATION TABLE UPDATED R MATERIAL PRICE INFORMATION TABLE UPDATED R MATERIAL PRICE INFORMATION TABLE UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Material Effectivity MATERIAL EFFECTIVITY UPDATED MATERIAL SET UPDATED R MATERIAL EFFECTIVITY UPDATED MATERIAL SET UPDATED R

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 1 5

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
MATERIAL EFFECTIVITY UPDATED MATERIAL SET UPDATED R MATERIAL EFFECTIVITY UPDATED MATERIAL SET UPDATED R REFERENCES REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Procurement Addresses PROCUREMENT ADDRESSES UPDATED MATERIAL SET UPDATED R Price and Availability PRICE AND AVAILABILITY UPDATED MATERIAL PRICE UPDATED MATERIAL SET UPDATED R
LIST OF COMPONENTS Kit 546014A01R05 PART MATERIAL SET UPDATED MATERIAL SET LABEL UPDATED R Kit 546014A02R01 PART MATERIAL SET UPDATED MATERIAL SET LABEL UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 546014- 833-802-001-Repair Subtask 546014-833-003-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED NOTE UPDATED R

Subtask 546014-833-004-002 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED NOTE UPDATED R

Subtask 546014-833-004-003 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED NOTE UPDATED R

Subtask 546014-833-004-004 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED NOTE UPDATED R

Fig. A-FFAAA Fig. A-FFAAA Sheet 01 SHEET UPDATED R FILLING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 2 5

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS Revision No.01 issued to inform the operators of the effectivity updating and to specify the number of the Consigne de Navigabilite and NTM. Revision No.02 issued to inform the operators of the modification of Figure 2 (Detail A after Mod. No.6966 added) and incorporates Changes Notices 1.A. and 1.B. Revision No.03 issued to update the effectivity, add a note which specifies this Service Bulletin is applicable on right pylon only for MSN 717, add the PROPRIETARY RIGHTS statement and specify the number of holes to be drilled into the doubler. Revision No.04 issued to add a Liquid penetrant inspection as an alternative to the eddy current inspection. Revision 05 issued to inform operators that revised inspection thresholds, repeat intervals and grace periods have been introduced to support aircraft operations to Extended Service Goal 2 (ESG2). Revision 06 issued to add MSN 0722 in Config. 03 and MSN 0724 in new Config. 04, replace the tool PN 99A53003001001 by PN 99A53003001105 and update the manhours. REVISION SEQUENCE ORIGINAL: Oct 15/93 REVISION No.: 01 - Mar 28/94 REVISION No.: 02 - Mar 22/07 REVISION No.: 03 - Mar 04/98 REVISION No.: 04 - Mar 09/02 REVISION No. : 05 - Sep 01/11 REVISION No. : 06 - May 24/12 REVISION No. : 07 - Sep 05/12

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 3 5

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

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DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 4 5

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# @A300-600 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft. 

# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 54 

### TITLE: NACELLES/PYLON - INSPECT PYLON LOWER SPAR BETWEEN RIBS 6 AND 7. **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES On aircraft fitted with General Electric (GE) pylon, 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. The aim of this Service Bulletin is to call for an eddy current inspection or a 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 an extensive repair and reduction of the structural capacity. 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 YES VENDOR SB INVOLVED NO NOTE (1): Service Bulletin must be accomplished.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 1 5

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# @A300-600 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 Kit546014A01R05 2 3,680.00 Bolt, nut **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit546014A02R01 2 3,640.00 Bolt, nut **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit546014A02R01 1 1,820.00 Bolt, nut **CONF 004 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit546014A02R01 1 1,820.00 Bolt, nut EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

34Z 83V AAL ABD AIB BCS CES F2I FDX G8E GBG IRA IRM KAC KAL MON MSR OHY QTR RUN SUD TAR THA UZB CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 54.51.41.002 OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 2 5

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# @A300-600 SERVICE BULLETIN SUMMARY OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 546014-832-801-001: Inspection TOTAL MANHOURS 12.00 ELAPSED TIME (HOURS) 6.00 Task 546014-833-802-001: Repair TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 30.00 **CONF 002 Task 546014-832-801-001: Inspection TOTAL MANHOURS 12.00 ELAPSED TIME (HOURS) 6.00 Task 546014-833-802-001: Repair TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 30.00 **CONF 003 Task 546014-832-801-001: Inspection TOTAL MANHOURS 6.00 ELAPSED TIME (HOURS) 6.00 Task 546014-833-802-001: Repair TOTAL MANHOURS 30.00 ELAPSED TIME (HOURS) 15.00 **CONF 004 Task 546014-832-801-001: Inspection TOTAL MANHOURS 6.00 ELAPSED TIME (HOURS) 6.00

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 3 5

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# @A300-600 SERVICE BULLETIN SUMMARY Task 546014-833-802-001: Repair TOTAL MANHOURS 30.00 ELAPSED TIME (HOURS) 15.00 APPENDICES **CONF ALL Appendix 01 - Inspection Report Appendix 02 - Elapsed Time Assumptions

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 4 5

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# @A300-600 SERVICE BULLETIN SUMMARY

**CONF ALL

D_SB_546014_5_SUAA_01_00 Figure A-FSUAA - Sheet 01

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 5 5

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# @A300-600 SERVICE BULLETIN SUMMARY

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# @A300-600 SERVICE BULLETIN
AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 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 (1) Models B4-603 B4-605R B4-620 B4-622 B4-622R C4-620 (2) Effectivity by MSN 0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0423 0459-0466 0469-0470 0474 0477 0479 0505-0518 0521 0525 0529-0530 0532 0536 0540 0543 0546 0553-0561 0563 0566 0569 0572 0575 0577 0579 0581-0582 0584 0602-0615 0617-0618 0621 0623 0625-0633 0635 0637 0639 0641 0643 0645 0657 0659 0662 0664 0666 0668 0670 0673 0675 0677 0679 0681 0683 0685 0688 0692 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721-0722 0724 (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.
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 1 5

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# @A300-600 SERVICE BULLETIN

OPERATOR MSN 34Z 0685 0692 83V 0423 0459 0460 0463 0466 0470 0474 0510 0511 0512 0615 0639 0675 AAL 0517 0612 ABD 0529 0557 AIB 0507 0508 0515 BCS 0602 0617 0621 0637 0641 0670 0679 0683 0703 0711 0724 CES 0521 0525 0532 0707 F2I 0284 0294 0301 0307 0312 0317 0321 0336 0348 0351 0461 0518 0606 0610 0645 FDX 0358 0361 0365 0388 0417 0477 0479 0530 0536 0543 0555 0559 0572 0575 0579 0581 0611 0613 0625 0630 0633 0657 0659 0664 0668 0688 0709 0713 0715 G8E 0462 0465 0469 0506 0509 0513 0514 0516 GBG 0626 0643 IRA 0632 0696 IRM 0380 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701 KAC 0344 0673 0694 0699 0719 0721 KAL 0582 0609 0627 0631 0662 MON 0540 0556 0604 0605 MSR 0561 0607 OHY 0584 0603 QTR 0554 0560 0614 RUN 0677 SUD 0666 TAR 0505 0558 0563 THA 0464 0566 0569 0577 0628 0629 0635 0681 0705 UZB 0717 0722 (4) Configuration by MSN MSN CONFIGURATION 0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 0358 0361 0365 0388 0417 0477 0479 0529 0530 0536 0543 0554 0555 0557 0559 0560 0561 0566 0569 0572 0575 0577 0579 0581 0582 0602 0607 0609 0611 0613 0614 0617 0621 0625 0627 0628 0629 0630 0631 0633 0635 0637 0641 0657 0659 0662 0664 0666 0668 0670 0677 0679 0681 0683 0685 0688 0692 0703 0705 0711 002

0380 0401 0405 0408 0411 0414 0423 0459 0460 0461 0462 0463 0464 0465 0466 0469 0470 0474 0505 0506 0507 0508 0509 0510 0511 0512 0513 0514 0515 0516 0517 0518 0521 0525 0532 0540 0546 0553 0556 0558 0563 0584 0603 0604 0605 0606 0608 0610 0612 0615 0618 0623 0626 0632 0639 0643 0645 0673 0675 0694 0696 0699 0701 0707 0709 0713 0715 0719 0721 001

0717 0722 003 0724 004 DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 2 5

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# @A300-600 SERVICE BULLETIN (5) Configuration definition NOTE: This inspection is applicable by Service Bulletin only on aircraft not having modification No. 10149S20315 embodied (production scheme). NOTE: The modification No. 10149S20315 (production scheme) is embodied prior to delivery on A/C MSN 0723, 0725 and subsequent. **CONF 001 Config. 01 concerns aircraft equipped with General Electric engines. **CONF 002 Config. 02 concerns aircraft equipped with Pratt and Whitney engines. **CONF 003 Config. 03 is valid for Aircraft MSN 0717 , MSN 0722 and concerns only the RH pylon of the aircraft. **CONF 004 Config. 04 is valid for Aircraft MSN 0724 and concerns only the LH pylon of the aircraft. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit546014A01R05 2 Consumable CMLA01 1 NOTE: Kit A01R00 is applicable for General Electric engines and for one pylon. **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit546014A02R01 2 Consumable CMLA01 1 NOTE: Kit A02R00 is applicable for Pratt and Whitney engines and for one pylon. **CONF 003 MATERIAL QTY PER A/C SEE NOTES Kit546014A02R01 1 Consumable CMLA01 1 NOTE: Kit A02R00 is applicable for Pratt and Whitney engines and for one pylon. NOTE: Only one kit A02R00 is necessary for the config. 03.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 3 5

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# @A300-600 SERVICE BULLETIN
**CONF 004 MATERIAL QTY PER A/C SEE NOTES Kit546014A02R01 1 Consumable CMLA01 1 NOTE: Kit A02R00 is applicable for Pratt and Whitney engines and for one pylon. NOTE: Only one kit A02R00 is necessary for the config. 04. **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON (1) History On aircraft fitted with General Electric (GE) pylon, 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. (2) Objective/Action The aim of this Service Bulletin is to call for an eddy current inspection or a 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 an extensive repair and reduction of the structural capacity. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 546014-832-801-001: Inspection (1) Inspection Task 546014-833-802-001: Repair (1) Repair for General Electric engines DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 4 5

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# @A300-600 SERVICE BULLETIN
**CONF 002 Task 546014-832-801-001: Inspection (1) Inspection Task 546014-833-802-001: Repair (1) Repair for Pratt and Whitney Engines **CONF 003 Task 546014-832-801-001: Inspection (1) Inspection (RH Pylon Only) Task 546014-833-802-001: Repair (1) Repair for Pratt and Whitney Engines (RH Pylon Only) **CONF 004 Task 546014-832-801-001: Inspection (1) Inspection (LH Pylon Only) Task 546014-833-802-001: Repair (1) Repair for Pratt and Whitney Engines (LH Pylon Only) **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale **CONF 001 New Inspection Program pre-repair THRESHOLD INTERVAL AFT > 1.5FH/FC AFT =<1.5FH/FC AFT > 1.5FH/FC AFT =<1.5FH/FC CONDITION
FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS Config. 01 A300-600 GE Pre SB 54-6020 pre repair 9,400 9,400 6,100 6,100

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 5 5

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# @A300-600 SERVICE BULLETIN New Inspection Program after repair THRESHOLD INTERVAL AFT > 1.5FH/FC AFT =<1.5FH/FC AFT > 1.5FH/FC AFT =<1.5FH/FC CONDITION
FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS Config. 01 A300-600 GE post repair 9,100 19,500 10,200 15,200 4,700 10,000 5,200 7,800 Inspection program after embodiment of A300-54-6020. THRESHOLD INTERVAL AFT > 1.5FH/FC AFT =<1.5FH/FC AFT > 1.5FH/FC AFT =<1.5FH/FC CONDITION
FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS Config. 01 A300-600 GE Post SB 54-6020 18,600 39,500 20,700 30,900 11,000 23,300 12,200 18,200 AFT : Average Flight Time NOTE: FC or FH applicable values is the one that occurs first. NOTE: Threshold post repair is to be counted from repair embodiment. Grace Period - For post SB 54-6020 A300-600 GE with less than 25,100FC (27,900FC for AFT<1.5) : . For aircraft that have already exceeded or are close to exceed the threshold or scheduled interval, the inspection is to be accomplished within 2,000FC after receipt of this Inspection Service Bulletin without exceeding the requirement of previous issue of this SB. - For repaired A300-600 GE with less than 31,700FC (35,300FC for AFT<1.5) or post SB 54-6020 A300-600 GE with more than 25,100FC (27,900FC or AFT<1.5) : . For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 1,000FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this SB. - For repaired A300-600 GE with more than 31,700FC (35,300FC for AFT<1.5) : . For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 500FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this SB.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 6 5

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# @A300-600 SERVICE BULLETIN
**CONF 002 thru 004 New Inspection Program pre-repair THRESHOLD INTERVAL AFT > 1.5FH/FC AFT =<1.5FH/FC AFT > 1.5FH/FC AFT =<1.5FH/FC CONDITION
FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS Config. 02, 03 and 04 A300-600 PW Pre SB 54-6020 pre repair 5,700 5,700 4,400 4,400

New Inspection Program after repair THRESHOLD INTERVAL AFT > 1.5FH/FC AFT =<1.5FH/FC AFT > 1.5FH/FC AFT =<1.5FH/FC CONDITION
FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS Config. 02, 03 and 04 A300-600 PW post repair 6,500 13,900 7,200 10,800 3,300 7,100 3,700 5,600
Inspection program after embodiment of A300-54-6020. THRESHOLD INTERVAL AFT > 1.5FH/FC AFT =<1.5FH/FC AFT > 1.5FH/FC AFT =<1.5FH/FC CONDITION
FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS FLIGHT CYCLESFLIGHT HOURS Config. 02, 03 and 04 A300-600 PW Post SB 54-6020 12,100 25,700 13,400 20,100 7,800 16,600 8,700 13,000
AFT : Average Flight Time NOTE: FC or FH applicable values is the one that occurs first. NOTE: Threshold post SB 54-6020 is to be counted from SB 54-6020 embodiment. NOTE: Threshold post repair is to be counted from repair embodiment. Grace Period - For post SB 54-6020 A300-600 PW with less than 25,100FC (27,900FC for AFT<1.5) :

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 7 5

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# @A300-600 SERVICE BULLETIN . For aircraft that have already exceeded or are close to exceed the threshold or scheduled interval, the inspection is to be accomplished within 2,000FC after receipt of this Inspection Service Bulletin without exceeding the requirement of previous issue of this SB. - For repaired A300-600 PW with less than 15,500FC (17,300FC for AFT<1.5) or post SB 54-6020 A300-600 PW with more than 25,100FC (27,900FC for AFT<1.5) : . For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 1,000FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this SB. - For repaired A300-600PW with more than 15,500FC (17,300FC for AFT<1.5) : . For aircraft that have already exceeded or are close to exceed the threshold or the scheduled interval, the inspection is to be accomplished within 500FC after receipt of this Inspection Service Bulletin without exceeding the requirements of previous issue of this SB. **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. 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 546014-832-801-001: Inspection Get Access 5.00 On Aircraft Inspection 2.00 Tests 0.00 Close-Up 5.00 TOTAL MANHOURS 12.00 ELAPSED TIME (HOURS) 6.00

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 8 5

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# @A300-600 SERVICE BULLETIN
NOTE: For detail concerning the elapsed time assumption, refer to Appendix 02 - Elapsed Time Assumptions . Task 546014-833-802-001: Repair Get Access 5.00 On Aircraft Repair for General Electric engines 100.0 Tests 0.00 Close-Up 5.00 TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 30.00 NOTE: For detail concerning the elapsed time assumption, refer to Appendix 02 - Elapsed Time Assumptions . **CONF 002 Task 546014-832-801-001: Inspection Get Access 5.00 On Aircraft Inspection 2.00 Tests 0.00 Close-Up 5.00 TOTAL MANHOURS 12.00 ELAPSED TIME (HOURS) 6.00 NOTE: For detail concerning the elapsed time assumption, refer to Appendix 02 - Elapsed Time Assumptions . Task 546014-833-802-001: Repair Get Access 5.00 On Aircraft Repair for Pratt and Whitney Engines 100.0 Tests 0.00 Close-Up 5.00 TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 30.00 NOTE: For detail concerning the elapsed time assumption, refer to Appendix 02 - Elapsed Time Assumptions . **CONF 003 Task 546014-832-801-001: Inspection Get Access 2.50 On Aircraft Inspection (RH Pylon Only) 1.00 Tests 0.00
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 9 5

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# @A300-600 SERVICE BULLETIN
Task 546014-832-801-001: Inspection Close-Up 2.50 TOTAL MANHOURS 6.00 ELAPSED TIME (HOURS) 6.00 Task 546014-833-802-001: Repair Get Access 2.50 On Aircraft Repair for Pratt and Whitney Engines (RH Pylon Only) 25.00 Tests 0.00 Close-Up 2.50 TOTAL MANHOURS 30.00 ELAPSED TIME (HOURS) 15.00 NOTE: For detail concerning the elapsed time assumption, refer to Appendix 02 - Elapsed Time Assumptions . **CONF 004 Task 546014-832-801-001: Inspection Get Access 2.50 On Aircraft Inspection (LH Pylon Only) 1.00 Tests 0.00 Close-Up 2.50 TOTAL MANHOURS 6.00 ELAPSED TIME (HOURS) 6.00 Task 546014-833-802-001: Repair Get Access 2.50 On Aircraft Repair for Pratt and Whitney Engines (LH Pylon Only) 25.00 Tests 0.00 Close-Up 2.50 TOTAL MANHOURS 30.00 ELAPSED TIME (HOURS) 15.00 NOTE: For detail concerning the elapsed time assumption, refer to Appendix 02 - Elapsed Time Assumptions . **CONF ALL H. WEIGHT AND BALANCE If repair : Manufacturers Empty Weight +2 KG (+4.4092 LB) Effect on Balance 55.22 KGM (+399.406 LB.FT ) DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 10 5

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# @A300-600 SERVICE BULLETIN
I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-41-54 24-00-00 24-41-00 26-12-12 36-11-00 36-11-15 54-51-43 71-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-20 51-61-03 51-62-02 51-63-05 54-50-41 Service Bulletin (SB) A300-54-6020 Standards Manual (SM) Structural Repair Manual (SRM) 51-71-70 **CONF 002 Aircraft Maintenance Manual (AMM) 06-41-54 24-00-00 24-41-00 36-11-00 36-11-15 54-51-43 71-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-20 51-61-03 51-62-02 51-63-05 54-50-41 Service Bulletin (SB) A300-54-6020 Standards Manual (SM) Structural Repair Manual (SRM) 51-71-70 **CONF 003 Aircraft Maintenance Manual (AMM) 06-41-54 24-00-00 24-41-00 36-11-00 36-11-15 54-51-43 71-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-20 51-61-03 51-62-02 51-63-05 54-50-41 Service Bulletin (SB) A300-54-6020 Standards Manual (SM) Structural Repair Manual (SRM) 51-71-70 **CONF 004 Aircraft Maintenance Manual (AMM) 06-41-54 24-00-00 24-41-00 36-11-00 36-11-15 54-51-43 71-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 11 5

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# @A300-600 SERVICE BULLETIN
Non Destructive Test Manual (NTM) 51-10-20 51-61-03 51-62-02 51-63-05 54-50-41 Service Bulletin (SB) A300-54-6020 Standards Manual (SM) Structural Repair Manual (SRM) 51-71-70 **CONF ALL K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 54-50-08 Non Destructive Test Manual (NTM) 54-50-41 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 12 5

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# @A300-600 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses 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: Kit546014A01R05 AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 Hamburg Germany For ordering by internet: http://spares.airbus.com For ordering modification kits by fax: +49 40 50 76 25 90 For ordering of single spares by fax: +49 40 50 76 40 13 Kit546014A02R01 AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 Hamburg Germany For ordering by internet: http://spares.airbus.com For ordering modification kits by fax: +49 40 50 76 25 90 For ordering of single spares by fax: +49 40 50 76 40 13 (2) Price and Availability

Kit546014A01R05 Cost 1,840.00 USD Availability 90 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 13 5

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# @A300-600 SERVICE BULLETIN

Kit546014A02R01 Cost 1,820.00 USD Availability 90 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. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS Kit 546014A01R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 R5460005520000 1 Doubler 3 R5460007120100 6 Washer 4 R5460007120300 2 Washer 5 R5460007120400 4 Washer 6 R5460007120500 2 Washer 8 NAS1149C0363R 9 Washer 10 MS21062-3K 2 Nut 15 NAS1726C3E 60 Nut 16 NAS6703U3 6 Bolt 17 NAS6703U4 46 Bolt 18 NAS6703U5 2 Bolt 19 NAS6703U6 12 Bolt 20 NAS6703U7 10 Bolt 22 NAS6703U9 3 Bolt 24 NAS6703U12 2 Bolt 26 NSA5414-24-10 8 Rivet 27 NSA5414-32-18 10 Rivet 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 546014A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 R5460005520000 1 Doubler DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 14 5

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 3 R5460007120100 2 Washer 4 R5460007120300 5 Washer 8 NAS1149C0363R 5 Washer 15 NAS1726C3E 60 Nut 16 NAS6703U3 6 Bolt 17 NAS6703U4 42 Bolt 19 NAS6703U6 12 Bolt 20 NAS6703U7 1 Bolt 21 NAS6703U8 1 Bolt 22 NAS6703U9 5 Bolt 23 NAS6703U10 5 Bolt 24 NAS6703U12 3 Bolt 25 NAS6703U17 1 Bolt 27 NSA5414-32-18 10 Rivet 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 None

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 15 5

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# @A300-600 SERVICE BULLETIN (2) Tools To accomplish this service Bulletin it is necessary to use the equipment and materials: - For control by eddy current as per NTM 54-50-41 Part 6. - For liquid penetrant as per NTM 54-50-41 Part 9. (3) Special Tools None

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 16 5

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# @A300-600 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 546014-832-801-001 - Inspection WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC. AS NECESSARY ON WIRING AND COMPONENTS - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. Task Associated Data **CONF 001 Zone 410 420 Access Door 413BL 423BL Manpower TOTAL MANHOURS 12.00 ELAPSED TIME (HOURS) 6.00 **CONF 002 Zone 410 420 Access Door 413BL 423BL Manpower TOTAL MANHOURS 12.00 ELAPSED TIME (HOURS) 6.00 **CONF 003 Zone 420 DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 17 5

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# @A300-600 SERVICE BULLETIN

Access Door 423BL Manpower TOTAL MANHOURS 6.00 ELAPSED TIME (HOURS) 6.00 **CONF 004 Zone 410 Access Door 413BL Manpower TOTAL MANHOURS 6.00 ELAPSED TIME (HOURS) 6.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 546014-910-001-001 - 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 As required References Consumable Material List (CML) (a) For the specification of the material number (Mat No.), refer to Consumable Material List (CML). (b) Clean the surface to seal with Solvent General Purpose 11-026 As required (2) Subtask 546014-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 18 5

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# @A300-600 SERVICE BULLETIN (a) Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 002 (1) Subtask 546014-910-001-001 - 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 As required References Consumable Material List (CML) (a) For the specification of the material number (Mat No.), refer to Consumable Material List (CML). (b) Clean the surface to seal with Solvent General Purpose 11-026 As required (2) Subtask 546014-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 003 (1) Subtask 546014-910-001-001 - 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 As required

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 19 5

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# @A300-600 SERVICE BULLETIN

References Consumable Material List (CML) (a) For the specification of the material number (Mat No.), refer to Consumable Material List (CML). (b) Clean the surface to seal with Solvent General Purpose 11-026 As required (2) Subtask 546014-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 004 (1) Subtask 546014-910-001-001 - 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 As required References Consumable Material List (CML) (a) For the specification of the material number (Mat No.), refer to Consumable Material List (CML). (b) Clean the surface to seal with Solvent General Purpose 11-026 As required (2) Subtask 546014-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 20 5

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# @A300-600 SERVICE BULLETIN
**CONF ALL B. PREPARATION **CONF 001 (1) Subtask 546014-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 24-00-00, Page Block 301 24-41-00, Page Block 301 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401 (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) De-energize the aircraft electrical circuits, refer to AMM 24-41-00, Page Block 301. (c) Put access platform(s) in position. (d) Open the access door 413BL on the LH pylon, (Refer to AMM 06-41-54, Page Block 001). (e) Open the access door 423BL on the RH pylon, (Refer to AMM 06-41-54, Page Block 001). (f) Remove the pre cooler, (Refer to AMM 36-11-15, Page Block 401). (g) Remove the upper panel rods between rib 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (h) Remove the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401). **CONF 002 (1) Subtask 546014-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 21 5

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# @A300-600 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 24-00-00, Page Block 301 24-41-00, Page Block 301 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401 (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) De-energize the aircraft electrical circuits, refer to AMM 24-41-00, Page Block 301. (c) Put access platform(s) in position. (d) Open the access door 413BL on the LH pylon, (Refer to AMM 06-41-54, Page Block 001). (e) Open the access door 423BL on the RH pylon, (Refer to AMM 06-41-54, Page Block 001). (f) Remove the pre cooler, (Refer to AMM 36-11-15, Page Block 401). (g) Remove the upper panel rods between rib 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (h) Remove the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401). **CONF 003 (1) Subtask 546014-941-001-002 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 24-00-00, Page Block 301 24-41-00, Page Block 301 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401 (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) De-energize the aircraft electrical circuits, refer to AMM 24-41-00, Page Block 301. (c) Put access platform(s) in position. (d) Open the access door 423BL on the RH pylon, (Refer to AMM 06-41-54, Page Block 001). DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 22 5

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# @A300-600 SERVICE BULLETIN (e) Remove the pre cooler, (Refer to AMM 36-11-15, Page Block 401). (f) Remove the upper panel rods between rib 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (g) Remove the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401). **CONF 004 (1) Subtask 546014-941-001-003 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 24-00-00, Page Block 301 24-41-00, Page Block 301 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401 (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) De-energize the aircraft electrical circuits, refer to AMM 24-41-00, Page Block 301. (c) Put access platform(s) in position. (d) Open the access door 413BL on the LH pylon, (Refer to AMM 06-41-54, Page Block 001). (e) Remove the pre cooler, (Refer to AMM 36-11-15, Page Block 401). (f) Remove the upper panel rods between rib 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (g) Remove the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401). **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 546014-832-001-001 - Inspection Work Zones and Access Panels Zone Access/Work location 410 Access Door 413BL 420 Access Door 423BL DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 23 5

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# @A300-600 SERVICE BULLETIN
Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-50-41 Part 6 54-50-41 Part 9 Service Bulletin (SB) A300-54-6020 Fig. A-FBBAA Inspection of the Lower Spar between Ribs 6 and 7 Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01
NOTE: Inspection results must be reported to AIRBUS (SEES2) after completion, send Appendix 01 - Inspection Report . (a) From inside, on pylons 1 and 2, do an eddy current inspection, (Refer to NTM 54-50-41 Part 6) or a liquid penetrant inspection (Refer to NTM 54-50-41 Part 9) in the lower spar axis between ribs 6 and 7 at the threshold given in para 1.E.(2) Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FFAAA Sheet 01 (b) If no crack is detected, two solutions are possible : 1 Do a subsequent inspection at the intervals given in Paragraph 1.E.(2).
or 2 Accomplish the Service Bulletin No. A300-54-6020 (Mod No. 10335S20434).
a Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <1> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2). <2> If crack is detected, contact Airbus before next flight. (c) If a crack is detected. - Smooth blend out the area to remove the aluminium spray protection (theoretical thickness 0.17mm (0.007in) ). - Do again an eddy current inspection, (Refer to NTM 54-50-41 Part 6) and a liquid penetrant inspection (Refer to NTM 54-50-41 Part 9). - Re-protect the area by pad cadmium plating.
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 24 5

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# @A300-600 SERVICE BULLETIN

1 If no crack is detected, two solutions are possible :
a Do a subsequent inspection at the intervals given in Paragraph 1.E.(2).
or b Accomplish the Service Bulletin No. A300-54-6020 (Mod No. 10335S20434). <1> Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <a> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2). <b> If crack is detected, contact Airbus before next flight. 2 If crack is detected.
a Crack <= 30mm (1.181 in.) : <1> Before 500 flights, perform the SUBTASK 546014-833-003 001 Repair for General Electric engines . <2> Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <a> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2). <b> If crack is detected, contact Airbus before next flight. b Crack between 30mm (1.181 in.) and 35mm (1.378 in.) : <1> Before 250 flights, perform the SUBTASK 546014-833-003 001 Repair for General Electric engines . <2> Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <a> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2). <b> If crack is detected, contact Airbus before next flight.
c Crack > 35mm (1.378 in.) <1> Contact AIRBUS before next flight.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 25 5

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# @A300-600 SERVICE BULLETIN
**CONF 002 (1) Subtask 546014-832-001-002 - Inspection Work Zones and Access Panels Zone Access/Work location 410 Access Door 413BL 420 Access Door 423BL Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 54-50-41 Part 6 54-50-41 Part 9 Service Bulletin (SB) A300-54-6020 Fig. A-FBBAA Inspection of the Lower Spar between Ribs 6 and 7 Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01
NOTE: Inspection results must be reported to AIRBUS (SEES2) after completion, send Appendix 01 - Inspection Report . (a) From inside, on pylons 1 and 2, do an eddy current inspection, (Refer to NTM 54-50-41 Part 6) or a liquid penetrant inspection (Refer to NTM 54-50-41 Part 9) in the lower spar axis between ribs 6 and 7 at the threshold given in para 1.E.(2) Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FFAAA Sheet 01 (b) If no crack is detected, two solutions are possible : 1 Do a subsequent inspection at the intervals given in Paragraph 1.E.(2).
or 2 Accomplish the Service Bulletin No. A300-54-6020 (Mod No. 10335S20434).
a Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <1> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2). <2> If crack is detected, contact Airbus before next flight.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 26 5

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# @A300-600 SERVICE BULLETIN (c) If a crack is detected. - Smooth blend out the area to remove the aluminium spray protection (theoretical thickness 0.17mm (0.007in) ). - Do again an eddy current inspection, (Refer to NTM 54-50-41 Part 6) and a liquid penetrant inspection (Refer to NTM 54-50-41 Part 9). - Re-protect the area by pad cadmium plating. 1 If no crack is detected, two solutions are possible :
a Do a subsequent inspection at the intervals given in Paragraph 1.E.(2).
or b Accomplish the Service Bulletin No. A300-54-6020 (Mod No. 10335S20434). <1> Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <a> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2). <b> If crack is detected, contact Airbus before next flight. 2 If crack is detected.
a Crack <= 30mm (1.181 in.) : <1> Before 500 flights, perform the SUBTASK 546014-833-004 002 Repair for Pratt and Whitney Engines . <2> Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <a> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2). <b> If crack is detected, contact Airbus before next flight. b Crack between 30mm (1.181 in.) and 35mm (1.378 in.) : <1> Before 250 flights, perform the SUBTASK 546014-833-004 002 Repair for Pratt and Whitney Engines . <2> Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <a> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2). <b> If crack is detected, contact Airbus before next flight. DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 27 5

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# @A300-600 SERVICE BULLETIN

c Crack > 35mm (1.378 in.) <1> Contact AIRBUS before next flight. **CONF 003 (1) Subtask 546014-832-001-003 - Inspection (RH Pylon Only) Work Zones and Access Panels Zone Access/Work location 420 Access Door 423BL 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) 54-50-41 Part 6 54-50-41 Part 9 Service Bulletin (SB) A300-54-6020 Fig. A-FBBAA Inspection of the Lower Spar between Ribs 6 and 7 Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01
NOTE: Inspection results must be reported to AIRBUS (SEES2) after completion, send Appendix 01 - Inspection Report . (a) From inside, on pylon 2, do an eddy current inspection, (Refer to NTM 54-50-41 Part 6) or a liquid penetrant inspection (Refer to NTM 54-50-41 Part 9) in the lower spar axis between ribs 6 and 7 at the threshold given in para 1.E.(2) Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FFAAA Sheet 01 (b) If no crack is detected, two solutions are possible : 1 Do a subsequent inspection at the intervals given in Paragraph 1.E.(2).
or 2 Accomplish the Service Bulletin No. A300-54-6020 (Mod No. 10335S20434).
a Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <1> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2).
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 28 5

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# @A300-600 SERVICE BULLETIN <2> If crack is detected, contact Airbus before next flight. (c) If a crack is detected. - Smooth blend out the area to remove the aluminium spray protection (theoretical thickness 0.17mm (0.007in) ). - Do again an eddy current inspection, (Refer to NTM 54-50-41 Part 6) and a liquid penetrant inspection (Refer to NTM 54-50-41 Part 9). - Re-protect the area by pad cadmium plating. 1 If no crack is detected, two solutions are possible :
a Do a subsequent inspection at the intervals given in Paragraph 1.E.(2).
or b Accomplish the Service Bulletin No. A300-54-6020 (Mod No. 10335S20434). <1> Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <a> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2). <b> If crack is detected, contact Airbus before next flight. 2 If crack is detected.
a Crack <= 30mm (1.181 in.) : <1> Before 500 flights, perform the SUBTASK 546014-833-004 003 Repair for Pratt and Whitney Engines (RH Pylon Only) . <2> Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <a> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2). <b> If crack is detected, contact Airbus before next flight. b Crack between 30mm (1.181 in.) and 35mm (1.378 in.) : <1> Before 250 flights, perform the SUBTASK 546014-833-004 003 Repair for Pratt and Whitney Engines (RH Pylon Only) . <2> Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <a> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2). DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 29 5

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# @A300-600 SERVICE BULLETIN <b> If crack is detected, contact Airbus before next flight.
c Crack > 35mm (1.378 in.) <1> Contact AIRBUS before next flight. **CONF 004 (1) Subtask 546014-832-001-004 - Inspection (LH Pylon Only) Work Zones and Access Panels Zone Access/Work location 410 Access Door 413BL 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) 54-50-41 Part 6 54-50-41 Part 9 Service Bulletin (SB) A300-54-6020 Fig. A-FBBAA Inspection of the Lower Spar between Ribs 6 and 7 Sheet 01 Fig. A-FFAAA Flow Chart Sheet 01
NOTE: Inspection results must be reported to AIRBUS (SEES2) after completion, send Appendix 01 - Inspection Report . (a) From inside, on pylon 1, do an eddy current inspection, (Refer to NTM 54-50-41 Part 6) or a liquid penetrant inspection (Refer to NTM 54-50-41 Part 9) in the lower spar axis between ribs 6 and 7 at the threshold given in para 1.E.(2) Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FFAAA Sheet 01 (b) If no crack is detected, two solutions are possible : 1 Do a subsequent inspection at the intervals given in Paragraph 1.E.(2).
or

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 30 5

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# @A300-600 SERVICE BULLETIN

2 Accomplish the Service Bulletin No. A300-54-6020 (Mod No. 10335S20434).
a Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <1> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2). <2> If crack is detected, contact Airbus before next flight. (c) If a crack is detected. - Smooth blend out the area to remove the aluminium spray protection (theoretical thickness 0.17mm (0.007in) ). - Do again an eddy current inspection, (Refer to NTM 54-50-41 Part 6) and a liquid penetrant inspection (Refer to NTM 54-50-41 Part 9). - Re-protect the area by pad cadmium plating. 1 If no crack is detected, two solutions are possible :
a Do a subsequent inspection at the intervals given in Paragraph 1.E.(2).
or b Accomplish the Service Bulletin No. A300-54-6020 (Mod No. 10335S20434). <1> Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <a> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2). <b> If crack is detected, contact Airbus before next flight. 2 If crack is detected.
a Crack <= 30mm (1.181 in.) : <1> Before 500 flights, perform the SUBTASK 546014-833-004 004 Repair for Pratt and Whitney Engines (LH Pylon Only) . <2> Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <a> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2). <b> If crack is detected, contact Airbus before next flight.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 31 5

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# @A300-600 SERVICE BULLETIN
b Crack between 30mm (1.181 in.) and 35mm (1.378 in.) : <1> Before 250 flights, perform the SUBTASK 546014-833-004 004 Repair for Pratt and Whitney Engines (LH Pylon Only) . <2> Do the new inspection program at the threshold given in the Paragraph 1.E.(2). <a> If no crack is detected, do a subsequent inspection at the intervals given in Paragraph 1.E.(2). <b> If crack is detected, contact Airbus before next flight.
c Crack > 35mm (1.378 in.) <1> Contact AIRBUS before next flight. **CONF ALL D. TEST **CONF 001 None **CONF 002 None **CONF 003 None **CONF 004 None **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 546014-942-003-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 32 5

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# @A300-600 SERVICE BULLETIN (a) Make sure that the work areas are clean and clear of tools and other items of equipment (b) Install the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (d) Install the pre cooler, (Refer to AMM 36-11-15, Page Block 401). (e) Install the access doors (413BL for LH pylon, 423BL for RH pylon), (Refer to AMM 06-41-54, Page Block 001). (f) Remove the access platform(s). **CONF 002 (1) Subtask 546014-942-003-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment (b) Install the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (d) Install the pre cooler, (Refer to AMM 36-11-15, Page Block 401). (e) Install the access doors (413BL for LH pylon, 423BL for RH pylon), (Refer to AMM 06-41-54, Page Block 001). (f) Remove the access platform(s). **CONF 003 (1) Subtask 546014-942-003-002 - Close-up Manpower Resources Skills NON SPECIFIC

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# @A300-600 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment (b) Install the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (d) Install the pre cooler, (Refer to AMM 36-11-15, Page Block 401). (e) Install the access door 423BL, (Refer to AMM 06-41-54, Page Block 001). (f) Remove the access platform(s). **CONF 004 (1) Subtask 546014-942-003-003 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (d) Install the pre cooler, (Refer to AMM 36-11-15, Page Block 401). (e) Install the access door 413BL, (Refer to AMM 06-41-54, Page Block 001). (f) Remove the access platform(s).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 34 5

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# @A300-600 SERVICE BULLETIN Task 546014-833-802-001 - 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 Access Door 413BL 423BL Manpower TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 30.00 **CONF 002 Zone 410 420 Access Door 413BL 423BL Manpower TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 30.00 **CONF 003 Zone 420 DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 35 5

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# @A300-600 SERVICE BULLETIN

Access Door 423BL Manpower TOTAL MANHOURS 30.00 ELAPSED TIME (HOURS) 15.00 **CONF 004 Zone 410 Access Door 413BL Manpower TOTAL MANHOURS 30.00 ELAPSED TIME (HOURS) 15.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 546014-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 002 (1) Subtask 546014-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 003 (1) Subtask 546014-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 36 5

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# @A300-600 SERVICE BULLETIN
**CONF 004 (1) Subtask 546014-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 546014-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 24-00-00, Page Block 301 24-41-00, Page Block 301 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401 (a) Make sure that the aircraft is electrically grounded, (Refer to AMM 24-00-00, Page Block 301). (b) De-energize the aircraft electrical circuits, (Refer to AMM 24-41-00, Page Block 301). (c) Put access platform(s) in position. (d) Open the access door 413BL on the LH pylon, (Refer to AMM 06-41-54, Page Block 001). (e) Open the access door 423BL on the RH pylon, (Refer to AMM 06-41-54, Page Block 001). (f) Remove the pre cooler, (Refer to AMM 36-11-15, Page Block 401). (g) Remove the upper panel rods between rib 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (h) Remove the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 37 5

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# @A300-600 SERVICE BULLETIN
**CONF 002 (1) Subtask 546014-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 24-00-00, Page Block 301 24-41-00, Page Block 301 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401 (a) Make sure that the aircraft is electrically grounded, (Refer to AMM 24-00-00, Page Block 301). (b) De-energize the aircraft electrical circuits, (Refer to AMM 24-41-00, Page Block 301). (c) Put access platform(s) in position. (d) Open the access door 413BL on the LH pylon, (Refer to AMM 06-41-54, Page Block 001). (e) Open the access door 423BL on the RH pylon, (Refer to AMM 06-41-54, Page Block 001). (f) Remove the pre cooler, (Refer to AMM 36-11-15, Page Block 401). (g) Remove the upper panel rods between rib 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (h) Remove the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401). **CONF 003 (1) Subtask 546014-941-003-002 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 24-00-00, Page Block 301 24-41-00, Page Block 301 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 38 5

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# @A300-600 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded, (Refer to AMM 24-00-00, Page Block 301). (b) De-energize the aircraft electrical circuits, (Refer to AMM 24-41-00, Page Block 301). (c) Put access platform(s) in position. (d) Open the access door 423BL on the RH pylon, (Refer to AMM 06-41-54, Page Block 001). (e) Remove the pre cooler, (Refer to AMM 36-11-15, Page Block 401). (f) Remove the upper panel rods between rib 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (g) Remove the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401). **CONF 004 (1) Subtask 546014-941-003-003 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 24-00-00, Page Block 301 24-41-00, Page Block 301 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401 (a) Make sure that the aircraft is electrically grounded, (Refer to AMM 24-00-00, Page Block 301). (b) De-energize the aircraft electrical circuits, (Refer to AMM 24-41-00, Page Block 301). (c) Put access platform(s) in position. (d) Open the access door 413BL on the LH pylon, (Refer to AMM 06-41-54, Page Block 001). (e) Remove the pre cooler, (Refer to AMM 36-11-15, Page Block 401). (f) Remove the upper panel rods between rib 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (g) Remove the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 39 5

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# @A300-600 SERVICE BULLETIN
**CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 546014-833-003-001 - Repair for General Electric engines Work Zones and Access Panels Zone Access/Work location 410 Access Door 413BL 420 Access Door 423BL Manpower Resources Manhours 100.0 Minimum number of person 4 Subtask elapsed time 25.00 Skills AIRFRAME Material necessary to do the job Kit 546014A01R05 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 Doubler 3 R5460007120100 6 Washer 4 R5460007120300 2 Washer 5 R5460007120400 4 Washer 6 R5460007120500 2 Washer 8 NAS1149C0363R 9 Washer 10 MS21062-3K 2 Nut 15 NAS1726C3E 60 Nut 16 NAS6703U3 6 Bolt 17 NAS6703U4 46 Bolt 18 NAS6703U5 2 Bolt 19 NAS6703U6 12 Bolt 20 NAS6703U7 10 Bolt 22 NAS6703U9 3 Bolt 24 NAS6703U12 2 Bolt 26 NSA5414-24-10 8 Rivet 27 NSA5414-32-18 10 Rivet References Aircraft Maintenance Manual (AMM) 26-12-12, Page Block 401 71-00-00, Page Block 401

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# @A300-600 SERVICE BULLETIN

References Non Destructive Test Manual (NTM) 51-10-20 Part 6 51-61-03 Part 6 51-62-02 Part 6 51-63-05 Part 6 54-50-41 Part 6 54-50-41 Part 9 Structural Repair Manual (SRM) 51-71-70 Fig. A-FBCAA Removal/Installation and Modification of Parts to gain access to Ribs 6 and 7 of Lower Spar Sheet 01

Fig. A-FBDAA Installation of Doubler under the Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 (a) Remove engine (Refer to AMM 71-00-00, Page Block 401). (b) Installation of the doubler under the lower spar between ribs 6 and 7 on General Electric CF6-80C2 left engine pylon, zone 410 and/or on General Electric CF6-80C2 right pylon, zone 420. Fig. A-FBCAA Sheet 01 and Fig. A-FBDAA Sheet 01 and Fig. A-FBDAA Sheet 02 1 Between ribs 4 and 9, remove for access : 1 Systron loop Item (32) Retain (Refer to AMM 26-12-12, Page Block 401). 1 Firewall Item (33) Retain 1 Firewall support Item (34) Retain 1 Firewall Item (35) Retain 1 metal sheet Item (31) Retain
a Remove brackets of the hydraulic line routing Item 31 (view C before). <1> Remove 2 bracket Item (36) Discard NOTE: The hardware will be re-used. Only the fasteners attaching the metal sheet Item 31 to the lower spar will not be re-used.

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# @A300-600 SERVICE BULLETIN

2 Removal of the rivets and plates.
a Remove : 10 rivets Item (27) Discard 4 plates Item (37) Retain 1 plate Item (38) Retain b Countersink at location of removed rivet Item (27), (Refer to SRM 51-71-70) to obtain a correct contact at location of doubler Item 1. 3 Drill stop holes.
a Drill two 6 mm (0.236 in.) diameter holes at the ends of the crack. NOTE: Do an additional inspection after drilling of crack stop holes as per : - NTM 51-10-20 Part 6 - Calibration standard : 99A53003001105 Item 108, (NTM 51-63-05 Part 6). If crack is found, contact AIRBUS. 4 Removal of fasteners at ribs 6 and 7.
a Remove : 12 rivets Item (19) Discard 5 Offer-up and position under lower spar : 1 Doubler R5460005520000 Item 1 6 Drill, ream, deburr and attach the doubler Item 1. Fig. A-FBDAA Sheet 01 and Fig. A-FBDAA Sheet 02 NOTE: Drill 9 holes (if before Mod No. 06966) or 4 holes (if after Mod No. 06966) in the doubler Item 1 for the passage of bolts Item 20 and 22, to : Min. dia. 5.00mm (0.196 in.) Max. dia. 5.1mm (0.200in.) NOTE: Before attaching the doubler Item 1, attach : 4 plates Item (37) Retained at removal
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# @A300-600 SERVICE BULLETIN
1 plate Item (38) Retained at removal with : 10 Rivet NSA5414-32-18 Item 27 attach the doubler Item 1 with : 12 Bolt NAS6703U6 Item 19 6 Bolt NAS6703U3 Item 16 42 Bolt NAS6703U4 Item 17 60 Nut NAS1726C3E Item 15 7 Install : 7 Blanking Bolts NAS6703U7 Item 20 7 Washer NAS1149C0363R Item 8 on the plates Item 37 and 38. 8 Modify and install the sensing elements and firewall assy.
a Install the brackets of hydraulic routing on metal sheet Item 31. Fig. A-FBCAA Sheet 01 View C AFTER Offer-up metal sheet Item 31 on pylon Item 31. Mark the location of the anchor nuts Item 10. Blank off the holes of the removed brackets Item (36) with : 4 Rivet NSA5414-24-10 Item 26 attach : 2 Nut MS21062-3K Item 10 with : 4 Rivet NSA5414-24-10 Item 26 2 Washer R5460007120500 Item 6 2 Bolt NAS6703U5 Item 18

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# @A300-600 SERVICE BULLETIN
b Machining of the brackets. In order to lower the sensing elements Item 32, 33, 34 and 35 and the firewall assy Item 31, the holes on the 2 supports A5461249750000, Item 41 (view D) and the support A2611012420000, Item 42 (view L) will be enlarged by 3mm (0.118in.). NOTE: Item 41 for post Mod. No. 07431 or post SIL 54-018 only.
c Attach : 1 Firewall Item (33) 1 Firewall Item (35) 1 Firewall Support Item (34) 1 Metal Sheet Item (31) with : Section EE (Rib 9) 4 Bolt NAS6703U4 Item 17 4 Washer R5460007120100 Item 3 Section GG 2 Bolt NAS6703U12 Item 24 2 Washer R5460007120100 Item 3 Section FF 2 Blanking Bolts NAS6703U9 Item 22 2 Washer R5460007120300 Item 4 2 Washer NAS1149C0363R Item 8 Section KK 3 Blanking Bolts NAS6703U7 Item 20 3 Washer R5460007120400 Item 5 Section HH 1 Blanking Bolts NAS6703U9 Item 22 1 Washer R5460007120400 Item 5

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# @A300-600 SERVICE BULLETIN
d Install fire sensing elements (Refer to AMM 26-12-12, Page Block 401). 1 Systron loop Item (32) Retained at removal (c) Install engine, (Refer to AMM 71-00-00, Page Block 401). **CONF 002 (1) Subtask 546014-833-004-002 - Repair for Pratt and Whitney Engines Work Zones and Access Panels Zone Access/Work location 410 Access Door 413BL 420 Access Door 423BL Manpower Resources Manhours 100.0 Minimum number of person 4 Subtask elapsed time 25.00 Skills NON SPECIFIC Material necessary to do the job Kit 546014A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 Doubler 3 R5460007120100 2 Washer 4 R5460007120300 5 Washer 8 NAS1149C0363R 5 Washer 15 NAS1726C3E 60 Nut 16 NAS6703U3 6 Bolt 17 NAS6703U4 42 Bolt 19 NAS6703U6 12 Bolt 20 NAS6703U7 1 Bolt 21 NAS6703U8 1 Bolt 22 NAS6703U9 5 Bolt 23 NAS6703U10 5 Bolt 24 NAS6703U12 3 Bolt 25 NAS6703U17 1 Bolt 27 NSA5414-32-18 10 Rivet References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 Non Destructive Test Manual (NTM) 51-10-20 Part 6 51-61-03 Part 6 51-62-02 Part 6 51-63-05 Part 6
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# @A300-600 SERVICE BULLETIN

References Structural Repair Manual (SRM) 51-71-70 Fig. A-FBDAB Installation of Doubler under the Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 Fig. A-FBCAB Removal/Installation and Modification of Parts to gain access to Ribs 6 and 7 of Lower Spar Sheet 01

(a) Remove engine, (Refer to AMM 71-00-00, Page Block 401). (b) Installation of the doubler under the lower spar between ribs 6 and 7 on PW JT9D-7R4 and PW 4000 left engine pylon, zone 410 and/or on PW JT9D-7R4 and PW 4000 right pylon, zone 420. Refer to Fig. A-FBCAB Sheet 01 and Fig. A-FBDAB Sheet 01 and Fig. A-FBDAB Sheet 02 1 Between ribs 5 and 8, remove for access : 1 Heat shield Item (39) Retain 1 folded metal sheet Item (40) Retain NOTE: Hardware will not be re-used. 2 Removal of rivets and plates
a Remove : 10 rivets Item (27) Discard 4 plates Item (37) Retain 1 plate Item (38) Retain b Countersink at location of removed rivets Item (27), (Refer to SRM 51-71-70) to obtain a correct contact at location of doubler Item 1. 3 Drill stop holes. Drill two 6mm (0.236in.) dia. holes at the ends of the crack. NOTE: Do an additional inspection after drilling of crack stop holes as per : - NTM 51-10-20 Part 6 - Calibration standard : 99A53003001105 Item 108, (NTM 51-63-05 Part 6).

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# @A300-600 SERVICE BULLETIN
If crack is found, contact AIRBUS. 4 Removal of the fasteners at ribs 6 and 7. Remove 12 Rivet Item (19) Discard 5 Offer-up and put in position under the lower spar : 1 Doubler R5460005520000 Item 1 6 Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBDAB Sheet 01 and Fig. A-FBDAB Sheet 02 NOTE: Drill 9 holes (if before Mod. No. 6966) or 5 holes (if after Mod. No. 6966) in the doubler Item 1 for the passage of bolts at location of Item 20, 22 and 23 to : Min. dia. : 5.0mm (0.196in.) Max dia. : 5.1mm (0.200in.) Before attaching the doubler Item 1, attach : 4 plates Item (37) Retained at removal 1 plate Item (38) Retained at removal with : 10 Rivet NSA5414-32-18 Item 27 attach the doubler Item 1 with : 12 Bolt NAS6703U6 Item 19 6 Bolt NAS6703U3 Item 16 42 Bolt NAS6703U4 Item 17 60 Nut NAS1726C3E Item 15 7 Install : 4 Blanking Bolts NAS6703U9 Item 22 1 Blanking Bolts NAS6703U7 Item 20 5 Washer NAS1149C0363R Item 8
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# @A300-600 SERVICE BULLETIN on plates Item 37 and 38. 8 Modification of the folded metal sheet A5461087400000, Item 40 Refer to Fig. A-FBCAB Sheet 01 In order to lower the assy Item 39, the hole on the folded metal sheet Item 40, will be enlarged by 3mm (0.118in.). 9 Installation of the heat shield Item 39.
a Attach : 1 Heat Shield Item (39) Retained at removal with : SECTION CC 2 Bolt NAS6703U12 Item 24 2 Washer R5460007120100 Item 3 SECTION DD Attach the heat shield Item 39 with the hydraulic line with : 1 Bolt NAS6703U12 Item 24 1 Washer R5460007120300 Item 4 SECTION EE 5 Bolt NAS6703U10 Item 23 1 Washer R5460007120300 Item 4 SECTION FF 1 Blanking Bolts NAS6703U9 Item 22 1 Washer R5460007120300 Item 4 SECTION GG and SECTION HH Attach the heat shield Item 39 to the folded metal sheet Item 40 with : 1 Bolt NAS6703U8 Item 21 1 Bolt NAS6703U17 Item 25 2 Washer R5460007120300 Item 4 (c) Install engine, (Refer to AMM 71-00-00, Page Block 401). DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 48 5

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# @A300-600 SERVICE BULLETIN
**CONF 003 (1) Subtask 546014-833-004-003 - Repair for Pratt and Whitney Engines (RH Pylon Only) Work Zones and Access Panels Zone Access/Work location 420 Access Door 423BL Manpower Resources Manhours 25.00 Minimum number of person 2 Subtask elapsed time 12.50 Skills NON SPECIFIC Material necessary to do the job Kit 546014A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 Doubler 3 R5460007120100 2 Washer 4 R5460007120300 5 Washer 8 NAS1149C0363R 5 Washer 15 NAS1726C3E 60 Nut 16 NAS6703U3 6 Bolt 17 NAS6703U4 42 Bolt 19 NAS6703U6 12 Bolt 20 NAS6703U7 1 Bolt 21 NAS6703U8 1 Bolt 22 NAS6703U9 5 Bolt 23 NAS6703U10 5 Bolt 24 NAS6703U12 3 Bolt 25 NAS6703U17 1 Bolt 27 NSA5414-32-18 10 Rivet References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 Non Destructive Test Manual (NTM) 51-10-20 Part 6 51-61-03 Part 6 51-62-02 Part 6 51-63-05 Part 6 54-50-41 Part 6 Structural Repair Manual (SRM) 51-71-70 Fig. A-FBCAB Removal/Installation and Modification of Parts to gain access to Ribs 6 and 7 of Lower Spar Sheet 01

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 49 5

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# @A300-600 SERVICE BULLETIN

References Fig. A-FBDAB Installation of Doubler under the Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 (a) Remove engine, (Refer to AMM 71-00-00, Page Block 401). (b) Installation of the doubler under the lower spar between ribs 6 and 7 on PW 4000 right pylon, zone 420. Refer to Fig. A-FBCAB Sheet 01 and Fig. A-FBDAB Sheet 01 and Fig. A-FBDAB Sheet 02 1 Between ribs 5 and 8, remove for access : 1 Heat shield Item (39) Retain 1 folded metal sheet Item (40) Retain NOTE: Hardware will not be re-used. 2 Removal of rivets and plates
a Remove : 10 rivets Item (27) Discard 4 plates Item (37) Retain 1 plate Item (38) Retain b Countersink at location of removed rivets Item (27), (Refer to SRM 51-71-70) to obtain a correct contact at location of doubler Item 1. 3 Drill stop holes. Drill two 6mm (0.236in.) dia. holes at the ends of the crack. NOTE: Do an additional inspection after drilling of crack stop holes as per : - NTM 51-10-20 Part 6 - Calibration standard : 99A53003001105 Item 108, (NTM 51-63-05 Part 6). If crack is found, contact AIRBUS. 4 Removal of the fasteners at ribs 6 and 7. Remove 12 Rivet Item (19) Discard DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 50 5

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# @A300-600 SERVICE BULLETIN
5 Offer-up and put in position under the lower spar : 1 Doubler R5460005520000 Item 1 6 Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBDAB Sheet 01 and Fig. A-FBDAB Sheet 02 NOTE: Drill 9 holes (if before Mod. No. 6966) or 5 holes (if after Mod. No. 6966) in the doubler Item 1 for the passage of bolts at location of Item 20, 22 and 23 to : Min. dia. : 5.0mm (0.196in.) Max dia. : 5.1mm (0.200in.) Before attaching the doubler Item 1, attach : 4 plates Item (37) Retained at removal 1 plate Item (38) Retained at removal with : 10 Rivet NSA5414-32-18 Item 27 attach the doubler Item 1 with : 12 Bolt NAS6703U6 Item 19 6 Bolt NAS6703U3 Item 16 42 Bolt NAS6703U4 Item 17 60 Nut NAS1726C3E Item 15 7 Install : 4 Blanking Bolts NAS6703U9 Item 22 1 Blanking Bolts NAS6703U7 Item 20 5 Washer NAS1149C0363R Item 8 on plates Item 37 and 38. 8 Modification of the folded metal sheet A54610847400000 Item 40. Refer to Fig. A-FBCAB Sheet 01 In order to lower the assy Item 39, the hole on the folded metal sheet Item 40, will be enlarged by 3mm (0.118in.). DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 51 5

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# @A300-600 SERVICE BULLETIN
9 Installation of the heat shield Item 39.
a Attach : 1 Heat Shield Item (39) Retained at removal with : SECTION CC 2 Bolt NAS6703U12 Item 24 2 Washer R5460007120100 Item 3 SECTION DD Attach the heat shield Item 39 with the hydraulic line with : 1 Bolt NAS6703U12 Item 24 1 Washer R5460007120300 Item 4 SECTION EE 5 Bolt NAS6703U10 Item 23 1 Washer R5460007120300 Item 4 SECTION FF 1 Blanking Bolts NAS6703U9 Item 22 1 Washer R5460007120300 Item 4 SECTION GG and HH Attach the heat shield Item 39 to the folded metal sheet Item 40 with : 1 Bolt NAS6703U8 Item 21 1 Bolt NAS6703U17 Item 25 2 Washer R5460007120300 Item 4 (c) Install engine, (Refer to AMM 71-00-00, Page Block 401).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 52 5

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# @A300-600 SERVICE BULLETIN
**CONF 004 (1) Subtask 546014-833-004-004 - Repair for Pratt and Whitney Engines (LH Pylon Only) Work Zones and Access Panels Zone Access/Work location 410 Access Door 413BL Manpower Resources Manhours 25.00 Minimum number of person 2 Subtask elapsed time 12.50 Skills NON SPECIFIC Material necessary to do the job Kit 546014A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 R5460005520000 1 Doubler 3 R5460007120100 2 Washer 4 R5460007120300 5 Washer 8 NAS1149C0363R 5 Washer 15 NAS1726C3E 60 Nut 16 NAS6703U3 6 Bolt 17 NAS6703U4 42 Bolt 19 NAS6703U6 12 Bolt 20 NAS6703U7 1 Bolt 21 NAS6703U8 1 Bolt 22 NAS6703U9 5 Bolt 23 NAS6703U10 5 Bolt 24 NAS6703U12 3 Bolt 25 NAS6703U17 1 Bolt 27 NSA5414-32-18 10 Rivet References Aircraft Maintenance Manual (AMM) 71-00-00, Page Block 401 Non Destructive Test Manual (NTM) 51-10-20 Part 6 51-61-03 Part 6 51-62-02 Part 6 51-63-05 Part 6 54-50-41 Part 6 Structural Repair Manual (SRM) 51-71-70 Fig. A-FBCAB Removal/Installation and Modification of Parts to gain access to Ribs 6 and 7 of Lower Spar Sheet 01

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 53 5

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# @A300-600 SERVICE BULLETIN

References Fig. A-FBDAB Installation of Doubler under the Lower Spar between Ribs 6 and 7 Sheet 01 Sheet 02 (a) Remove engine, (Refer to AMM 71-00-00, Page Block 401). (b) Installation of the doubler under the lower spar between ribs 6 and 7 on PW 4000 left engine pylon, zone 410. Refer to Fig. A-FBCAB Sheet 01 and Fig. A-FBDAB Sheet 01 and Fig. A-FBDAB Sheet 02 1 Between ribs 5 and 8, remove for access : 1 Heat shield Item (39) Retain 1 folded metal sheet Item (40) Retain NOTE: Hardware will not be re-used. 2 Removal of rivets and plates
a Remove : 10 rivets Item (27) Discard 4 plates Item (37) Retain 1 plate Item (38) Retain b Countersink at location of removed rivets Item (27), (Refer to SRM 51-71-70) to obtain a correct contact at location of doubler Item 1. 3 Drill stop holes. Drill two 6mm (0.236in.) dia. holes at the ends of the crack. NOTE: Do an additional inspection after drilling of crack stop holes as per : - NTM 51-10-20 Part 6 - Calibration standard : 99A53003001105 Item 108, (NTM 51-63-05 Part 6). If crack is found, contact AIRBUS. 4 Removal of the fasteners at ribs 6 and 7. Remove 12 Rivet Item (19) Discard DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 54 5

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# @A300-600 SERVICE BULLETIN
5 Offer-up and put in position under the lower spar : 1 Doubler R5460005520000 Item 1 6 Drill, ream, deburr and attach the doubler Item 1. Refer to Fig. A-FBDAB Sheet 01 and Fig. A-FBDAB Sheet 02 NOTE: Drill 9 holes (if before Mod. No. 6966) or 5 holes (if after Mod. No. 6966) in the doubler Item 1 for the passage of bolts at location of Item 20, 22 and 23 to : Min. dia. : 5.0mm (0.196in.) Max dia. : 5.1mm (0.200in.) Before attaching the doubler Item 1, attach : 4 plates Item (37) Retained at removal 1 plate Item (38) Retained at removal with : 10 Rivet NSA5414-32-18 Item 27 attach the doubler Item 1 with : 12 Bolt NAS6703U6 Item 19 6 Bolt NAS6703U3 Item 16 42 Bolt NAS6703U4 Item 17 60 Nut NAS1726C3E Item 15 7 Install : 4 Blanking Bolts NAS6703U9 Item 22 1 Blanking Bolts NAS6703U7 Item 20 5 Washer NAS1149C0363R Item 8 on plates Item 37 and 38. 8 Modification of the folded metal sheet A54610847400000 Item 40. Refer to Fig. A-FBCAB Sheet 01 In order to lower the assy Item 39, the hole on the folded metal sheet Item 40, will be enlarged by 3mm (0.118in.). DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 55 5

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# @A300-600 SERVICE BULLETIN
9 Installation of the heat shield Item 39.
a Attach : 1 Heat Shield Item (39) Retained at removal with : SECTION CC 2 Bolt NAS6703U12 Item 24 2 Washer R5460007120100 Item 3 SECTION DD Attach the heat shield Item 39 with the hydraulic line with : 1 Bolt NAS6703U12 Item 24 1 Washer R5460007120300 Item 4 SECTION EE 5 Bolt NAS6703U10 Item 23 1 Washer R5460007120300 Item 4 SECTION FF 1 Blanking Bolts NAS6703U9 Item 22 1 Washer R5460007120300 Item 4 SECTION GG and HH Attach the heat shield Item 39 to the folded metal sheet Item 40 with : 1 Bolt NAS6703U8 Item 21 1 Bolt NAS6703U17 Item 25 2 Washer R5460007120300 Item 4 (c) Install engine, (Refer to AMM 71-00-00, Page Block 401). **CONF ALL D. TEST **CONF 001 None
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 56 5

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# @A300-600 SERVICE BULLETIN
**CONF 002 None **CONF 003 None **CONF 004 None **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 546014-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 24-00-00 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (d) Install the precooler, (Refer to AMM 36-11-15, Page Block 401). (e) Install the access doors (413BL for LH pylon, 423BL for RH pylon), (Refer to AMM 06-41-54, Page Block 001). (f) Remove the access platform(s). **CONF 002 (1) Subtask 546014-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 57 5

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# @A300-600 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 24-00-00 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (d) Install the precooler, (Refer to AMM 36-11-15, Page Block 401). (e) Install the access doors (413BL for LH pylon, 423BL for RH pylon), (Refer to AMM 06-41-54, Page Block 001). (f) Remove the access platform(s). **CONF 003 (1) Subtask 546014-942-002-002 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 24-00-00 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (d) Install the precooler, (Refer to AMM 36-11-15, Page Block 401). (e) Install the access doors 423BL, (Refer to AMM 06-41-54, Page Block 001). (f) Remove the access platform(s).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 58 5

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# @A300-600 SERVICE BULLETIN
**CONF 004 (1) Subtask 546014-942-002-003 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-54, Page Block 001 24-00-00 36-11-00, Page Block 401 36-11-15, Page Block 401 54-51-43, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the cold air inlet duct of the bleed air supply system, (Refer to AMM 36-11-00, Page Block 401). (c) Install the upper panel rods between ribs 4 and 8, (Refer to AMM 54-51-43, Page Block 401). (d) Install the precooler, (Refer to AMM 36-11-15, Page Block 401). (e) Install the access doors 413BL , (Refer to AMM 06-41-54, Page Block 001). (f) Remove the access platform(s).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 59 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

CRACK FINDING FROM THE INSIDE, DO AN EDDY CURRENT INSPECTION or A LIQUID PENETRANT INSPECTION IN THE LOWER SPAR axis BETWEEN RIB6 AND 7 AS PER THRESHOLD GIVEN IN PARA 1.E.(2).

QUESTION
ACTION
FINDING NO

DO SUBSEQUENT INSPECTION AT INTERVAL GIVEN IN PARA 1.E.(2). ACCOMPLISHMENT SERVICE BULLETIN No. A300−54−6020

NEW INSPECTION PROGRAM AT THRESHOLD GIVEN IN PARA 1.E.(2). (MOD No. 10335S20434)

NO YES

DO SUBSEQUENT INSPECTION AT INTERVAL GIVEN IN PARA 1.E.(2). CONTACT AIRBUS BEFORE NEXT FLIGHT CRACK BETWEEN 30 mm AND 35 mm (1.181 in) AND (1.378 in) CRACK OR = 30 mm (1.181 in) CRACK 35 mm (1.378 in)

500 FLIGHTS REPAIR BEFORE 250 FLIGHTS REPAIR BEFORE CONTACT AIRBUS BEFORE NEXT FLIGHT

NEW INSPECTION PROGRAM AT THRESHOLD GIVEN IN PARA 1.E.(2).

NO YES

DO SUBSEQUENT INSPECTION AT INTERVAL GIVEN IN PARA 1.E.(2). CONTACT AIRBUS BEFORE NEXT FLIGHT SMOOTH BLEND OUT THE AREA TO REMOVE THE ALUMINIUM SPRAY PROTECTION

REPROTECT THE AREA BY PAD CADMIUM PLATING (0.17 mm (0.007 in) THEORETICAL THICKNESS)

NO YES CRACK FINDING YES

CRACK FINDING CRACK FINDING OR RE INSPECT IMMEDIATELY WITH BOTH: HFEC NTM 54−40−10 PART 6 AND A LIQUID PENETRANT INSPECTION NTM 54−40−10 PART 9.

D_SB_546014_5_FAAA_01_06 Figure A-FFAAA - Sheet 01 Flow Chart
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 60 5

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# @A300-600 SERVICE BULLETIN

**CONF ALL

D_SB_546014_5_BBAA_01_01 Figure A-FBBAA - Sheet 01 Inspection of the Lower Spar between Ribs 6 and 7
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 61 5

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# @A300-600 SERVICE BULLETIN

**CONF 001

D_SB_546014_5_BCAA_01_00 Figure A-FBCAA - Sheet 01 Removal/Installation and Modification of Parts to gain access to Ribs 6 and 7 of Lower Spar
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 62 5

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# @A300-600 SERVICE BULLETIN

**CONF 002 thru 004

D_SB_546014_5_BCAB_01_01 Figure A-FBCAB - Sheet 01 Removal/Installation and Modification of Parts to gain access to Ribs 6 and 7 of Lower Spar
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 63 5

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# @A300-600 SERVICE BULLETIN

**CONF 001

NOTE: X = 20mm (0.787in.) LEFT SIDE SHOWN RIGHT SIDE SYMMETRICAL 

### A 

## A

D_SB_546014_5_BDAA_01_01RIB 7RIB 6RIB 6RIB 7RIB 8 

### 31

Figure A-FBDAA - Sheet 01 Installation of Doubler under the Lower Spar between Ribs 6 and 7
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 64 5

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# @A300-600 SERVICE BULLETIN

**CONF 001

D_SB_546014_5_BDAA_02_00 BOLT

NAS6703U6 NUT

NAS1726C3E T Y Q L E O H FINAL REAMING
MINI MAXI E M T I E M T I

12 4.81 mm (0.190 in.) 4.83 mm (0.191 in.) 19 15

NAS6703U4 NAS1726C3E 42 4.81 mm (0.190 in.) 4.83 mm (0.191 in.) 17 15

NAS6703U3 NAS1726C3E 6 4.81 mm (0.190 in.) 4.83 mm (0.191 in.) 16 15

Figure A-FBDAA - Sheet 02 Installation of Doubler under the Lower Spar between Ribs 6 and 7
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 65 5

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# @A300-600 SERVICE BULLETIN

**CONF 002 thru 004

NOTE: X = 20mm (0.787in.) LEFT SIDE SHOWN RIGHT SIDE SYMMETRICAL 

### A

D_SB_546014_5_BDAB_01_00 Figure A-FBDAB - Sheet 01 Installation of Doubler under the Lower Spar between Ribs 6 and 7
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 66 5

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# @A300-600 SERVICE BULLETIN

**CONF 002 thru 004

BOLT

NAS6703U6 NUT

NAS1726C3E T Y Q L E O H FINAL REAMING
MINI MAXI E M T I E M T I

12 4.81 mm (0.190 in.) 4.83 mm (0.191 in.) 19 15

NAS6703U4 NAS1726C3E 42 4.81 mm (0.190 in.) 4.83 mm (0.191 in.) 17 15

NAS6703U3 NAS1726C3E 6 4.81 mm (0.190 in.) 4.83 mm (0.191 in.) 16 15

D_SB_546014_5_BDAB_02_00 Figure A-FBDAB - Sheet 02 Installation of Doubler under the Lower Spar between Ribs 6 and 7
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 67 5

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# @A300-600 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 68 5

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# @A300-600 SERVICE BULLETIN Appendix 01 - Inspection Report **CONF ALL

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 1 5

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# @A300-600 SERVICE BULLETIN Appendix 01 - Inspection Report

**CONF ALL

D_SB_546014_5_RAAA_01_00 **INSPECTION REPORT**

PLEASE PRECISE OTHER FINDINGS THAN CRACK: AREA REPAIRED IN ACCORDANCE WITH: EDDY CURRENT A300−54−6014 A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : DATE OF THE INSPECTION : INSPECTION METHOD : SERVICE BULLETIN No. :

FINDING : YES NO LIQUID PENETRANT

B.S. A300−54−6014 PARA 2.C.
Figure A-FRAAA - Sheet 01 Inspection Report
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 2 5

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# @A300-600 SERVICE BULLETIN Appendix 01 - Inspection Report

**CONF ALL
**INSPECTION REPORT AFTER**

PLEASE PRECISE OTHER FINDINGS THAN CRACK: EDDY CURRENT A300−54−6014 A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : DATE OF THE INSPECTION : INSPECTION METHOD : SERVICE BULLETIN No. :

FINDING : YES NO LIQUID PENETRANT YES YES NO NO **REPAIR IN ACCORDANCE VITH PARA 2.C.(4).**

D_SB_546014_5_RAAA_02_00 Figure A-FRAAA - Sheet 02 Inspection Report
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 3 5

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# @A300-600 SERVICE BULLETIN Appendix 01 - Inspection Report

**CONF ALL
**INSPECTION REPORT AFTER**

PLEASE PRECISE OTHER FINDINGS THAN CRACK: EDDY CURRENT A300−54−6014 A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : DATE OF THE INSPECTION : INSPECTION METHOD : SERVICE BULLETIN No. :

FINDING : YES NO LIQUID PENETRANT YES YES NO NO **ACCOMPLISHMENT OF THE SERVICE BULLETIN A300−54−6020**  **(MOD. No. 10335S20434)**

D_SB_546014_5_RAAA_03_01 Figure A-FRAAA - Sheet 03 Inspection Report
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 4 5

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# @A300-600 SERVICE BULLETIN Appendix 02 - Elapsed Time Assumptions **CONF ALL (1) Refer to the subsequent Gantt Charts for the detail concerning the elapsed time assumptions.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 1 5

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# @A300-600 SERVICE BULLETIN Appendix 02 - Elapsed Time Assumptions

**CONF 001 thru 002

**ELAPSED TIME ASSUMPTION SERVICE BULLETIN No. A300−54−6014**

JOB SET−UP MH ET/S

TOTAL MANHOURS SB ELAPSED TIME 12.00 6.00 STEPS

5.00 2.50

5 0 INSPECTION 2.00 1.00

CLOSE−UP 5.00 2.50

MH ET/S: PER MANHOURS ELAPSED TIME PER STEP NUMBER OF PERSONS 01 02

THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. 01
02 **NOTES:** PER

2

2

2

: : SB ELAPSED TIME (HOURS) 1 2 3 4 6

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS ARE NOT REFLECTED IN THIS GANTT CHART. D_SB_546014_5_AAAA_01_00 Figure A-FAAAA - Sheet 01 Inspection Gantt Chart
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 2 5

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# @A300-600 SERVICE BULLETIN Appendix 02 - Elapsed Time Assumptions

**CONF 001 thru 002
**ELAPSED TIME ASSUMPTION SERVICE BULLETIN No. A300−54−6014**

SB ELAPSED TIME (HOURS) JOB SET−UP MH ET/S

TOTAL MANHOURS SB ELAPSED TIME 110.00 30.00 STEPS

5.00 2.50

5 10 15 20 0 REPAIR OF LH PYLON 50.00 25.00

MH ET/S: PER MANHOURS ELAPSED TIME PER STEP NUMBER OF PERSONS 01 02

PER

2

2

: : 25 30 CLOSE−UP 5.00 2.50 2

THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. 01
02 **NOTES:**

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS ARE NOT REFLECTED IN THIS GANTT CHART. REPAIR OF RH PYLON 50.00 25.00 2

D_SB_546014_5_ABAA_01_01 Figure A-FABAA - Sheet 01 Repair Gantt Chart
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 3 5

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# @A300-600 SERVICE BULLETIN Appendix 02 - Elapsed Time Assumptions

**CONF 003 thru 004
**ELAPSED TIME ASSUMPTION SERVICE BULLETIN No. A300−54−6014**

SB ELAPSED TIME (HOURS) JOB SET−UP MH ET/S

TOTAL MANHOURS SB ELAPSED TIME 55.00 30.00 STEPS

2.50 2.50

5 10 15 20 0 REPAIR OF ONE PYLON 50.00 25.00

MH ET/S: PER MANHOURS ELAPSED TIME PER STEP NUMBER OF PERSONS 01 02

PER

1

2

: : 25 30 CLOSE−UP 2.50 2.50 1

THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. 01
02 **NOTES:**

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS ARE NOT REFLECTED IN THIS GANTT CHART. D_SB_546014_5_ABAB_01_00 Figure A-FABAB - Sheet 01 Repair Gantt Chart
DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 4 5

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# @A300-600 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.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 1 5

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

# @A300-600 SERVICE BULLETIN QUALITY PERCEPTION FORM Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4321 - Quality rating of the Accomplishment Instructions 4321 - Quality rating of the Illustrations 4321 - Is this SB easy to understand ? Y/N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials Operator Supplied X Mod/Inspection X Manpower X Industry support X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments:

Operator: Date: Name/Title: Please return this form to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014 REVISION No.: 07 - Sep 05/12 Page: 1 5

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