@A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 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

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

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

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

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014

REVISION No.: 07 - Sep 05/12 Page: 4

5

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

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 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

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

Kit 546014A01R05 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

Kit 546014A02R01 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

Kit 546014A02R01 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

Kit 546014A02R01 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

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

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

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

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

SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014

REVISION No.: 07 - Sep 05/12 Page: 6

5

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

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 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

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

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

Kit 546014A01R05 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

Kit 546014A02R01 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

Kit 546014A02R01 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

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

SERVICE BULLETIN

**CONF 004

MATERIAL QTY PER A/C SEE NOTES

Kit 546014A02R01 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

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

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

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

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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

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

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

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

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

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

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

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

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

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

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

HOURS

FLIGHT

CYCLES

FLIGHT

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

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

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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

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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

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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

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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

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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:

Kit 546014A01R05 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

Kit 546014A02R01 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

Kit 546014A01R05

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

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SERVICE BULLETIN

Kit 546014A02R01

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

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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

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(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

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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

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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

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(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

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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.

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**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

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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

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(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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014

REVISION No.: 07 - Sep 05/12 Page: 33

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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

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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

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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

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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

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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

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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

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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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014

REVISION No.: 07 - Sep 05/12 Page: 40

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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.

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014

REVISION No.: 07 - Sep 05/12 Page: 41

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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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014

REVISION No.: 07 - Sep 05/12 Page: 42

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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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014

REVISION No.: 07 - Sep 05/12 Page: 43

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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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014

REVISION No.: 07 - Sep 05/12 Page: 44

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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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014

REVISION No.: 07 - Sep 05/12 Page: 45

5

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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).

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014

REVISION No.: 07 - Sep 05/12 Page: 46

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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

DATE: Oct 15/93 SERVICE BULLETIN No.: A300-54-6014

REVISION No.: 07 - Sep 05/12 Page: 47

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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**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

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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

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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

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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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SERVICE BULLETIN

**CONF 001

NOTE: X = 20mm (0.787in.)

LEFT SIDE SHOWN

RIGHT SIDE SYMMETRICAL

A

A

D_SB_546014_5_BDAA_01_01

RIB 7

RIB 6

RIB 6

RIB 7

RIB 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

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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

42 NAS6703U4 NAS1726C3E 4.81 mm

(0.190 in.)

4.83 mm

(0.191 in.)

17 15

6 NAS6703U3 NAS1726C3E 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

42 NAS6703U4 NAS1726C3E 4.81 mm

(0.190 in.)

4.83 mm

(0.191 in.)

17 15

6 NAS6703U3 NAS1726C3E 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

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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

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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

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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

0 5

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

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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

0 5 10 15 20

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

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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

0 5 10 15 20

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

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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

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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

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