@A340

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: 57

TITLE: WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM

FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT).

MODIFICATION No.: None

This page transmits Revision No.05 of Service Bulletin No.A340-57-4089

ADDITIONAL WORK

**CONF ALL

NOTE: No additional work is required by this revision for aircraft modified by any previous

issue.

REASON

The equivalent of this Service Bulletin has been validated on A330 aircraft MSN 0649.

Revision No. 05 issued to update the threshold and intervals and to add the grace period value.

CHANGES

SUMMARY

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

REASON UPDATED R

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

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

EFFECTIVITY OPERATOR LIST UPDATED R

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 1

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE

UPDATED

R

MANPOWER MANPOWER UPDATED R

MANPOWER UPDATED R

MANPOWER UPDATED R

Fig. A-FSAAA

Fig. A-FSAAA Sheet 01 SHEET UPDATED R

Fig. A-FSAAB

Fig. A-FSAAB Sheet 01 SHEET UPDATED R

Fig. A-FSAAC

Fig. A-FSAAC Sheet 01 SHEET UPDATED R

Fig. A-FSAAD

Fig. A-FSAAD Sheet 01 SHEET UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED

CONFIGURATION DESCRIPTION UPDATED

R

CONF 002 CONFIGURATION DEFINITION UPDATED

CONFIGURATION DESCRIPTION UPDATED

R

CONF 003 CONFIGURATION DEFINITION UPDATED

CONFIGURATION DESCRIPTION UPDATED

R

CONF 005 CONFIGURATION DEFINITION UPDATED

CONFIGURATION DESCRIPTION UPDATED

R

CONF 007 CONFIGURATION DEFINITION UPDATED

CONFIGURATION DESCRIPTION UPDATED

R

CONF 008 CONFIGURATION DEFINITION UPDATED

CONFIGURATION DESCRIPTION UPDATED

R

REASON

Objective/Action OBJECTIVE/ACTION UPDATED R

Advantages ADVANTAGES UPDATED R

COMPLIANCE

Accomplishment Timescale Table title, values and sentence modified. R

Accomplishment Timescale Table title, values and sentence modified. R

Accomplishment Timescale Table title, values and sentence modified. R

Accomplishment Timescale Table title, values and sentence modified. R

Accomplishment Timescale Table title, values and sentence modified. R

Accomplishment Timescale Table title, values and sentence modified. R

MANPOWER MANPOWER UPDATED R

MANPOWER UPDATED R

MANPOWER UPDATED R

MANPOWER UPDATED R

MANPOWER UPDATED R

MANPOWER UPDATED R

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 2

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

REFERENCES REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Price and Availability Kits price and availability updated. R

TOOLING TOOLING UPDATED R

Tooling - Price and Availability TOOLING - PRICE AND AVAILABILITY

PARAGRAPH ADDED

N

Tools TOOLS PARAGRAPH ADDED N

Special Tools SPECIAL TOOLS PARAGRAPH ADDED N

ACCOMPLISHMENT INSTRUCTIONS

TASK 574089- 832-801-001-INSPECTION TASK SOLUTION UPDATED

NOTE UPDATED

R

Task associated data - 003 MAN HOURS UPDATED R

Task associated data - 007 MAN HOURS UPDATED R

Task associated data - 008 MAN HOURS UPDATED R

Subtask 574089-941-001-001 The paragraphs concerning the job set-up of the

FWD cargo are deleted. Config. 004 deleted.

R

Subtask 574089-941-001-001 The paragraphs concerning the job set-up of the

FWD cargo are deleted. Config. 004 deleted.

R

Subtask 574089-941-001-001 The paragraphs concerning the job set-up of the

FWD cargo are deleted. Config. 004 deleted.

R

Subtask 574089-941-001-002 The paragraphs concerning the job set-up of the

FWD cargo are deleted. Config. 004 deleted.

R

Subtask 574089-941-001-001 The paragraphs concerning the job set-up of the

FWD cargo are deleted. Config. 004 deleted.

R

Subtask 574089-941-001-001 The paragraphs concerning the job set-up of the

FWD cargo are deleted. Config. 004 deleted.

R

Subtask 574089-010-001-001 Config. 004 deleted.

Removal procedure of the air conditioning duct

deleted.

R

Subtask 574089-010-002-001 Config. 004 deleted.

Removal procedure of the air conditioning duct

deleted.

R

Subtask 574089-832-007-001 Config. 004 deleted.

Reference to NTM 51-10-01 Part 6 added.

R

Subtask 574089-832-008-001 Config. 004 deleted.

Reference to NTM 51-10-01 Part 6 added.

R

Subtask 574089-410-001-001 Config. 004 deleted.

Installation procedure of the air conditioning duct

deleted. Sealing sentence added.

R

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 3

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 574089-410-002-001 Config. 004 deleted.

Installation procedure of the air conditioning duct

deleted. Sealing sentence added.

R

Subtask 574089-010-001-002 Config. 004 deleted.

Removal procedure of the air conditioning duct

deleted.

R

Subtask 574089-010-002-002 Config. 004 deleted.

Removal procedure of the air conditioning duct

deleted.

R

Subtask 574089-832-007-002 Config. 004 deleted.

Reference to NTM 51-10-01 Part 6 added.

R

Subtask 574089-832-008-002 Config. 004 deleted.

Reference to NTM 51-10-01 Part 6 added.

R

Subtask 574089-410-001-002 Config. 004 deleted.

Installation procedure of the air conditioning duct

deleted. Sealing sentence added.

R

Subtask 574089-410-002-002 Config. 004 deleted.

Installation procedure of the air conditioning duct

deleted. Sealing sentence added.

R

Subtask 574089-010-001-004 Config. 004 deleted.

Removal procedure of the air conditioning duct

deleted.

R

Subtask 574089-010-002-004 Config. 004 deleted.

Removal procedure of the air conditioning duct

deleted.

R

Subtask 574089-832-007-004 Config. 004 deleted.

Reference to NTM 51-10-01 Part 6 added.

R

Subtask 574089-832-008-004 Config. 004 deleted.

Reference to NTM 51-10-01 Part 6 added.

R

Subtask 574089-410-001-004 Config. 004 deleted.

Installation procedure of the air conditioning duct

deleted. Sealing sentence added.

R

Subtask 574089-410-002-004 Config. 004 deleted.

Installation procedure of the air conditioning duct

deleted. Sealing sentence added.

R

Subtask 574089-010-002-003 Config. 004 deleted.

Removal procedure of the air conditioning duct

deleted.

R

Subtask 574089-832-008-003 Config. 004 deleted.

Reference to NTM 51-10-01 Part 6 added.

R

Subtask 574089-410-002-003 Config. 004 deleted.

Installation procedure of the air conditioning duct

deleted. Sealing sentence added.

R

Subtask 574089-010-001-004 Config. 004 deleted.

Removal procedure of the air conditioning duct

deleted.

R

Subtask 574089-010-002-004 Config. 004 deleted.

Removal procedure of the air conditioning duct

deleted.

R

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 4

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 574089-832-007-004 Config. 004 deleted.

Reference to NTM 51-10-01 Part 6 added.

R

Subtask 574089-832-008-004 Config. 004 deleted.

Reference to NTM 51-10-01 Part 6 added.

R

Subtask 574089-410-001-004 Config. 004 deleted.

Installation procedure of the air conditioning duct

deleted. Sealing sentence added.

R

Subtask 574089-410-002-004 Config. 004 deleted.

Installation procedure of the air conditioning duct

deleted. Sealing sentence added.

R

Subtask 574089-010-001-004 Config. 004 deleted.

Removal procedure of the air conditioning duct

deleted.

R

Subtask 574089-010-002-004 Config. 004 deleted.

Removal procedure of the air conditioning duct

deleted.

R

Subtask 574089-832-007-004 Config. 004 deleted.

Reference to NTM 51-10-01 Part 6 added.

R

Subtask 574089-832-008-004 Config. 004 deleted.

Reference to NTM 51-10-01 Part 6 added.

R

Subtask 574089-410-001-004 Config. 004 deleted.

Installation procedure of the air conditioning duct

deleted. Sealing sentence added.

R

Subtask 574089-410-002-004 Config. 004 deleted.

Installation procedure of the air conditioning duct

deleted. Sealing sentence added.

R

Fig. A-FBAAA

Fig. A-FBAAA Sheet 01 SHEET UPDATED R

Fig. A-FBAAB

Fig. A-FBAAB Sheet 01 SHEET UPDATED R

Fig. A-FBAAC

Fig. A-FBAAC Sheet 01 SHEET UPDATED R

Fig. A-FBAAD

Fig. A-FBAAD Sheet 01 SHEET UPDATED R

Fig. A-FFAAA

Fig. A-FFAAA Sheet 01 SHEET UPDATED R

Fig. A-FFAAA Sheet 02 SRM 51-41-11 becomes 51-44-11. R

Fig. A-FFAAB

Fig. A-FFAAB Sheet 01 SHEET UPDATED R

Fig. A-FFAAB Sheet 02 SRM 51-41-11 becomes 51-44-11. R

Fig. A-FFAAB Sheet 03 SRM 51-41-11 becomes 51-44-11. R

Fig. A-FFAAC

Fig. A-FFAAC Sheet 01 SHEET UPDATED R

Fig. A-FFAAC Sheet 02 SHEET UPDATED R

Fig. A-FFAAD

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 5

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Fig. A-FFAAD Sheet 01 SHEET UPDATED R

Fig. A-FFAAD Sheet 02 SRM 51-41-11 becomes 51-44-11. R

Fig. A-FFAAD Sheet 03 SRM 51-41-11 becomes 51-44-11. R

Fig. A-FCAAA

Fig. A-FCAAA Sheet 01 SHEET UPDATED R

Fig. A-FCAAB

Fig. A-FCAAB Sheet 01 SHEET UPDATED R

Fig. A-FCAAC

Fig. A-FCAAC Sheet 01 SHEET UPDATED R

Fig. A-FCAAD

Fig. A-FCAAD Sheet 01 SHEET UPDATED R

Fig. A-FCAAD Sheet 02 SHEET UPDATED R

Appendix 01 - Inspection Report

Fig. A-FRAAA FIGURE SOLUTION ADDED N

Fig. A-FRAAA Sheet 01 SHEET ADDED N

Fig. A-FRAAB FIGURE SOLUTION ADDED N

Fig. A-FRAAB Sheet 01 SHEET ADDED N

Fig. A-FRAAC FIGURE SOLUTION ADDED N

Fig. A-FRAAC Sheet 01 SHEET ADDED N

Fig. A-FAA FIGURE DELETED FOR APPLICABLE MSN D

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

Revision No. 01 issued to add aircraft MSN 0007 for operator AFR, to add aircraft MSN 0008 for

operator SAA, to add aircraft MSN 0024 for operator DLH and to add MSN 0204 for operator B3R.

Revision No. 02 issued to inform the operators that this Service Bulletin is rendered mandatory. The

inspection requirements of this Service Bulletin are cancelled by accomplishment of Service Bulletin No.

A340-57-4098 (FUSELAGE - CENTER FUSELAGE - MODIFY FASTENING SYSTEM IN FR40 / KEEL

BEAM JUNCTION AREA) which is scheduled early 2006 on A340 aircraft PRE MOD 41652S11819.

Revision No. 03 issued to extend the effectivity of this Service Bulletin and propose modification Service

Bulletin to cancel repetitive inspection requirements.

The equivalent of this Service Bulletin has been validated on A330 aircraft MSN 0649.

Revision No. 04 issued to include minor improvements after validation : to update the flow chart for the

Config. 003, 007 and 008, to delete the access procedure of the FWD cargo compartment, to delete the

removal/installation procedures of the air conditioning duct, to delete the Config. 004 (MSN 0007

scrapped).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 6

5

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

REVISION SEQUENCE

ORIGINAL: Oct 30/03

REVISION No.: 01 - Mar 02/04

REVISION No.: 02 - Jan 24/06

REVISION No.: 03 - Jul 31/09

REVISION No.: 04 - May 31/11

REVISION No. : 05 - Nov 13/12

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 7

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 8

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

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: 57

TITLE: WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM

FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT).

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During a structural A340 aircraft fatigue test, cracks appeared in the keel beam fitting at Frame FR40,

initiating at the first fastener hole aft of Frame FR40 datum, in POST MOD No. 41652S12091 (serial

Mod.) (WINGS - SECTION 15/21 - MODIFY KEEL FITTING BEAM/FORWARD LOWER FUSELAGE

JOINT) configuration.

Results for this configuration have been extended to POST MOD No. 43577S12677 (retrofit Mod.)

(FUSELAGE - CENTER FUSELAGE - MODIFY LOWER KEEL FITTING AND FORWARD LOWER

SHELL CONNECTION) configuration which is similar.

This Service Bulletin requires a special detailed inspection on A340 aircraft PRE MOD 55306S18660

and PRE MOD 55792S18775.

Inspection area is on the keel beam horizontal flange in area of first fastener hole aft of FR40 datum

after fastener removal (Rotating Probe Inspection following NTM 51-10-01 Part 6) and subsequent

action.

For the Config. 1 and 5 accomplishment of Service Bulletin No. A340-57-4098 (Mod No. 54459S18477)

cancels the Inspection requirements of this Service Bulletin No. A340-57-4089.

For the Config. 2,3,7 and 8, accomplishment of Service Bulletin No. A340-57-4106 (Mod No.

56467S18944) cancels the Inspection requirements of this Service Bulletin No. A340-57-4089.

Accomplishment of this Service Bulletin will permit early detection of cracking in the keel beam and will

avoid extensive repair and aircraft down time.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 1

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

SUMMARY

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 LROPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

DE-FUELLING/VENTILATING YES

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 574089A01R00 2 534.00 Screw, Washer, Nut

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 574089A01R00 2 534.00 Screw, Washer, Nut

**CONF 003

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 574089A02R01 2 414.00 Screw, Washer, Nut

**CONF 005

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 574089A01R00 1 267.00 Screw, Washer, Nut

**CONF 007

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 574089A02R01 2 414.00 Screw, Washer, Nut

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 2

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

SUMMARY

**CONF 008

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 574089A02R01 2 414.00 Screw, Washer, Nut

EFFECTIVITY

**CONF ALL

This Service Bulletin is applicable to this (these) operator(s) :

47W 56W 83V AAW ABQ AFR AIB ALK ARG CAL CCA CES CPA

DGA DLH FIN GAF GFA HFY I2L IBE IRC KAC KNE LAN M3R

MAU MDG MSR NMB PAL QAF RJA S3R SAA SAS SFB SWR TAP

THT THY UAE VCV VIR XAX

NOTE: This Service Bulletin has been validated on A340 aircraft 0402.

NOTE: A booklet including photographs taken during the validation of this Service Bulletin

is available on AIRBUS World - Maintenance and Engineering - Service Bulletin

Information.

NOTE: The equivalent of this Service Bulletin has been validated on A330 aircraft MSN 0649.

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU 57.11.00.005

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHERS Operator Information Telex(OIT) No. 999.0083/03

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 3

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

SUMMARY

MANPOWER

**CONF 001

Task 574089-832-801-001: INSPECTION

TOTAL MANHOURS 35.00

ELAPSED TIME (HOURS) 30.00

**CONF 002

Task 574089-832-801-001: INSPECTION

TOTAL MANHOURS 35.00

ELAPSED TIME (HOURS) 30.00

**CONF 003

Task 574089-832-801-001: INSPECTION

TOTAL MANHOURS 43.00

ELAPSED TIME (HOURS) 35.00

**CONF 005

Task 574089-832-801-001: INSPECTION

TOTAL MANHOURS 27.00

ELAPSED TIME (HOURS) 25.00

**CONF 007

Task 574089-832-801-001: INSPECTION

TOTAL MANHOURS 43.00

ELAPSED TIME (HOURS) 35.00

**CONF 008

Task 574089-832-801-001: INSPECTION

TOTAL MANHOURS 43.00

ELAPSED TIME (HOURS) 35.00

APPENDICES

**CONF ALL

Appendix 01 - Inspection Report

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 4

5

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@A340

SERVICE BULLETIN

SUMMARY

**CONF 001

AREA TO INSPECT

LH SIDE SHOWN

RH SIDE SYMMETRICAL

Y1959

STGR1

FR40DATUM

FR40

FR47

A Z141 Z142 − 

B

B

A

B

F_SB_574089_5_SAAA_01_02

Figure A-FSAAA - Sheet 01

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 5

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

SUMMARY

**CONF 002

AREA TO INSPECT

LH SIDE SHOWN

RH SIDE SYMMETRICAL

Y1959

STGR1

FR40DATUM

FR40

FR47

B

B

A

B

VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40

A Z141 Z142 − 

F_SB_574089_5_SAAB_01_01

Figure A-FSAAB - Sheet 01

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 6

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

SUMMARY

**CONF 005

RH SIDE SHOWN

FR40

FR47

A Z141 Z142 − 

B

A

AREA TO INSPECT

Y1959

STGR1

FR40 DATUM

B

F_SB_574089_5_SAAC_01_01

Figure A-FSAAC - Sheet 01

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 7

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

SUMMARY

**CONF 003, 007 thru 008

LH SIDE SHOWN

RH SIDE SYMMETRICAL

FR40

FR47

B

B

A

DATUM

Y2390 Y1959

AREA TO INSPECT

STGR1

FR40

F

W

D

VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40

A Z141 Z142 − 

LH SIDE SHOWN

RH SIDE SYMMETRICAL

Y1959

FR40DATUM

B

STGR1

C

C

F_SB_574089_5_SAAD_01_01

Figure A-FSAAD - Sheet 01

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 8

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

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: 57

TITLE: WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM

FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT).

MODIFICATION No.: None

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

NOTE: This Service Bulletin has been validated on A340 aircraft MSN 0402.

NOTE: A booklet including photographs taken during the validation of this Service

Bulletin is available on AIRBUS World - Maintenance and Engineering -

Service Bulletin Information.

NOTE: This Service Bulletin is only applicable to aircraft on which modification No.

55306S18660 (REPLACE THE ONE-PIECE FITTING BY A SPLICE AND

AN ANGLE AT FR.40 (ADAPTATION SOLUTION)) and modification No.

55792S18775 (REINFORCE FUSELAGE AT FR40 (SERIAL SOLUTION)) is

not embodied.

(1) Models

340-211 340-212 340-213 340-311 340-312 340-313

(2) Effectivity by MSN

0002-0005 0009 0011 0014-0015 0018-0019 0021-0026 0032 0034 0041 0044 0046

0048 0051 0053 0056-0058 0061 0063 0074-0076 0078-0081 0084-0085 0088-0091

0093-0094 0101 0104 0114-0115 0117 0123 0125-0126 0128-0129 0131 0133-0137

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 1

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

0139 0141-0142 0145-0147 0149-0152 0154 0156-0161 0163-0164 0166-0170

0173-0176 0178-0180 0182 0185-0187 0190 0192-0194 0196-0197 0199 0201-0202

0204 0207-0208 0210 0212-0218 0220-0221 0225 0227-0228 0233 0235-0237 0239

0242-0243 0245-0246 0252 0257 0260 0263-0264 0268 0270 0273-0274 0278 0280

0282 0292 0297 0302 0304 0307 0310 0318-0319 0321 0325 0327 0329 0331-0332

0335 0347 0352 0354-0355 0359 0363 0367 0373-0374 0377-0379 0381 0385 0387

0390 0395 0399 0402 0406 0411 0413-0415 0424 0429-0430 0433-0435 0438 0442

0446-0447 0450 0459 0467 0470 0474 0483 0528 0538 0541 0544-0546 0554 0556

0559 0561-0562 0582 0585 0590 0598 0643 0646 0651 0668 0793 0800

(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the time

of issue in accordance with the information available to AIRBUS. Any future changes

resulting from transfer of an aircraft from one operator to another will not be reflected in

this list unless the Service Bulletin is revised for another reason.

OPERATOR MSN

47W 0009

56W 0003 0011 0015 0018 0019 0021

83V 0235 0239 0280 0292

AAW 0151

ABQ 0257

AFR 0078 0084 0186 0207 0237 0245 0246 0260 0307 0310 0377 0399

AIB 0332

ALK 0032 0034 0367 0374 0381

ARG 0048 0063 0074 0080 0085 0093 0094 0123 0126 0128 0373

CAL 0402 0406 0411 0415 0433 0541

CCA 0192 0199 0201 0242 0243 0264

CES 0129 0131 0141 0161 0182

CPA 0136 0137 0142 0147 0157 0160 0208 0218 0220 0227 0228

DGA 0075 0081

DLH 0024 0053 0056 0135 0158 0213 0233 0252 0297 0304 0321 0325

0327 0335 0347 0352 0354 0379 0390 0434 0447

FIN 0058 0168 0174

GAF 0274 0355

GFA 0212 0215 0282 0554

HFY 0117 0133

I2L 0216

IBE 0005 0088 0125 0134 0145 0146 0170 0193 0217 0221 0318 0329

0387 0414 0459 0474 0483

IRC 0002

KAC 0089 0090 0101 0104

KNE 0004

LAN 0167 0359 0363 0429 0442

M3R 0061

MAU 0076 0152 0194 0268 0793 0800

MDG 0210 0319

MSR 0156 0159 0178

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

OPERATOR MSN

NMB 0051

PAL 0173 0176 0187 0196

QAF 0026 0528

RJA 0014 0022

S3R 0204

SAA 0197 0378 0544 0582 0590 0643 0646 0651

SAS 0413 0424 0430 0435 0450 0467 0470

SFB 0046

SWR 0150 0154 0169 0175 0179 0263 0538 0545 0546 0556 0559 0561

0562 0585 0598

TAP 0041 0044 0079 0091

THT 0385 0395 0438 0446 0668

THY 0023 0025 0057 0115 0180 0270 0331

UAE 0139 0149 0163 0166 0185 0190 0202 0236

VCV 0302

VIR 0114 0164 0214 0225

XAX 0273 0278

(4) Configuration by MSN

MSN CONFIGURATION

0002 0003 0004 0005 0009 0011 0014 0015 0018 0019 0021

0022 0023 0025 0026 0032 0034 0041 0044 0046 0048 0051

0053 0056 0057 0058 0061 0063 0074 0075 0076 0078 0079

0080 0081 0084 0085 0088 0089 0090 0091 0093 0094 0101

0104

001

0024 005

0114 0115 0117 0123 0125 0126 0128 0129 0131 0133 0134

0135 0136 0137 0139 0141 0142 0145 0146 0147 0149 0150

0151 0152 0154 0156 0157 0158 0159 0160 0161 0163 0164

0166 0167 0168 0169 0170 0173 0174 0175

002

0176 0178 0179 0180 0182 0185 0186 0187 0190 0192 0193

0194 0196 0197 0199 0201 0202 0204 0207 0208 0210 0212

0213 0214 0215 0216 0217 0218 0220 0221 0225 0227 0228

0233 0235 0236 0237 0239 0245 0246 0252 0257 0260 0263

0268 0270 0273 0274 0278 0280 0282 0292 0297 0302 0304

0307 0310 0318 0319 0321 0325 0327 0329 0331 0332 0335

0347 0352 0354 0355 0359 0363 0367 0373 0374 0377 0378

0379 0381 0385 0387 0390 0395 0399 0402 0406 0411 0413

0414 0415 0424 0429 0430 0433 0434 0435 0438 0442 0446

0447 0450 0459 0467 0470 0474 0483

003

0242 0243 0264 007

0528 0538 0541 0544 0545 0546 0554 0556 0559 0561 0562

0582 0585 0590 0598 0643 0646 0651 0668 0793 0800

008

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SERVICE BULLETIN

(5) Configuration definition

**CONF 001

Config. 001 is valid for aircraft model A340-200 and A340-300 on which Service Bulletin

No. A340-57-4036 or Mod. No. 43577S12677 has been accomplished and on which

Service Bulletin No.A340-57-4098 (Mod. No.54459S18477) has not been accomplished

and Mod. No. 41652S12091 is not embodied.

**CONF 002

Config. 002 is valid for aircraft model A340-200 and A340-300 on which Mod. No.

41652S12091 is embodied and on which Service Bulletin No. A340-57-4106 (Mod.

No.56467S18944) has not been accomplished and Mod. No. 44360S13013 or Mod. No.

44360S13482 are not embodied.

**CONF 003

Config. 003 is valid for aircraft model A340-200 and A340-300 on which Mod. No.

44360S13013 or Mod. No. 44360S13482 is embodied and Service Bulletin No.

A340-57-4106 (Mod. No.56467S18944) has not been accomplished and Mod. No.

46650H13983 and Mod. No. 49202S16307 are not embodied.

**CONF 005

Config. 005 is valid for aircraft model A340-300 on RH side only and on which a

specific repair with titanium repair (Refer to Repair drawing R57115053 or R57115051 or

R57115047) has been embodied on the LH side only and on which Service Bulletin No.

A340-57-4036 (Mod. No.43577S12677) has been accomplished and on which Service

Bulletin No. A340-57-4098 (Mod. No.54459S18477) has not been accomplished and

Mod. No. 41652S12091 is not embodied.

**CONF 007

Config. 007 is valid for aircraft model A340-300 on which Mod. No. 44360S13013 or

Mod. No. 44360S13482 and Mod. No. 46650H13983 are embodied and Service Bulletin

No. A340-57-4106 (Mod. No.56467S18944) has not been accomplished and Mod. No.

49202S16307 is not embodied.

**CONF 008

Config. 008 is valid for aircraft model A340-300 on which Mod. No. 49202S16307 is

embodied and on which Service Bulletin No. A340-57-4106 (Mod. No.56467S18944) has

not been accomplished.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 574089A01R00 2

Consumable CMLA01 1

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 574089A01R00 2

Consumable CMLA01 1

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

**CONF 003

MATERIAL QTY PER A/C SEE NOTES

Kit 574089A02R01 2

Consumable CMLA01 1

**CONF 005

MATERIAL QTY PER A/C SEE NOTES

Kit 574089A01R00 1

Consumable CMLA01 1

**CONF 007

MATERIAL QTY PER A/C SEE NOTES

Kit 574089A02R01 2

Consumable CMLA01 1

**CONF 008

MATERIAL QTY PER A/C SEE NOTES

Kit 574089A02R01 2

Consumable CMLA01 1

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During a structural A340 aircraft fatigue test, cracks appeared in the keel beam fitting at

Frame FR40, initiating at the first fastener hole aft of Frame FR40 datum, in POST MOD

No. 41652S12091 (serial Mod.) (WINGS - SECTION 15/21 - MODIFY KEEL FITTING

BEAM/FORWARD LOWER FUSELAGE JOINT) configuration.

Results for this configuration have been extended to POST MOD No. 43577S12677

(retrofit Mod.) (FUSELAGE - CENTER FUSELAGE - MODIFY LOWER KEEL FITTING

AND FORWARD LOWER SHELL CONNECTION) configuration which is similar.

(2) Objective/Action

This Service Bulletin requires a special detailed inspection on A340 aircraft PRE MOD

55306S18660 and PRE MOD 55792S18775.

Inspection area is on the keel beam horizontal flange in area of first fastener hole aft of

FR40 datum after fastener removal (Rotating Probe Inspection following NTM 51-10-01

Part 6) and subsequent action.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

(3) Advantages

For the Config. 1 and 5 accomplishment of Service Bulletin No. A340-57-4098 (Mod

No. 54459S18477) cancels the Inspection requirements of this Service Bulletin No.

A340-57-4089.

For the Config. 2,3,7 and 8, accomplishment of Service Bulletin No. A340-57-4106 (Mod

No. 56467S18944) cancels the Inspection requirements of this Service Bulletin No.

A340-57-4089.

Accomplishment of this Service Bulletin will permit early detection of cracking in the keel

beam and will avoid extensive repair and aircraft down time.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 574089-832-801-001: INSPECTION

(1) Remove the Fastener on the LH Side

(2) Remove the Fastener on the RH Side

(3) Do a special detailed inspection of the hole at FR40, on the LH Side

(4) Do a special detailed inspection of the hole at FR40, on the RH Side

(5) Install the Fastener on the LH Side

(6) Install the Fastener on the RH Side

**CONF 002

Task 574089-832-801-001: INSPECTION

(1) Remove the Fastener on the LH Side

(2) Remove the Fastener on the RH Side

(3) Do a special detailed inspection of the hole at FR40, on the LH Side

(4) Do a special detailed inspection of the hole at FR40, on the RH Side

(5) Install the Fastener on the LH Side

(6) Install the Fastener on the RH Side

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

**CONF 003

Task 574089-832-801-001: INSPECTION

(1) Remove the Fasteners on the LH Side

(2) Remove the Fasteners on the RH Side

(3) Do a special detailed inspection of the holes at FR40, on the LH Side

(4) Do a special detailed inspection of the holes at FR40, on the RH Side

(5) Install the Fasteners on the LH Side

(6) Install the Fasteners on the RH Side

**CONF 005

Task 574089-832-801-001: INSPECTION

(1) Remove the Fastener on the RH Side

(2) Do a special detailed inspection of the hole at FR40, on the RH Side

(3) Install the Fastener on the RH Side

**CONF 007

Task 574089-832-801-001: INSPECTION

(1) Remove the Fasteners on the LH Side

(2) Remove the Fasteners on the RH Side

(3) Do a special detailed inspection of the holes at FR40, on the LH Side

(4) Do a special detailed inspection of the holes at FR40, on the RH Side

(5) Install the Fasteners on the LH Side

(6) Install the Fasteners on the RH Side

**CONF 008

Task 574089-832-801-001: INSPECTION

(1) Remove the Fasteners on the LH Side

(2) Remove the Fasteners on the RH Side

(3) Do a special detailed inspection of the holes at FR40, on the LH Side

(4) Do a special detailed inspection of the holes at FR40, on the RH Side

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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@A340

SERVICE BULLETIN

(5) Install the Fasteners on the LH Side

(6) Install the Fasteners on the RH Side

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

**CONF 001

Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long

Range, Threshold/Interval (LR)) have been established. Both sets ensure continued

airworthiness and could be used to cover any type of A/C utilization. This approach

is an equivalent damage approach corresponding to a trade off between FC/FH to

better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued

airworthiness and could be used to cover any type of utilization, for the 1st inspection

and the repetitive ones, operators may select either SR (Threshold or Interval) or LR

(Threshold or Interval) (depending of the A/C utilization evolution). If a non optimal

set of threshold / interval is selected, airworthiness will be ensured, but will penalize

the operator because the inspection will be performed sooner than necessary. As a

consequence, the selection of SR or LR threshold and subsequent intervals can be

changed whenever. Threshold and Interval are whichever occurs first between FC and

FH for a selected set of threshold/interval between SR and LR. This means that the set

FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa).

Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or

582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection

which is requested at the inspection threshold of this Service Bulletin.

Accomplishment of this Service Bulletin is required within the following thresholds and

intervals, whichever occurs first :

CONFIG. MANDATORY

THRESHOLD

MANDATORY

INTERVAL

RECOMMENDED

THRESHOLD (02)

RECOMMENDED

INTERVAL (02)

001 Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

SR:

11,400

(01)

SR:

43,100

(01)

SR:

9,650

SR:

36,500

SR:

2,900

(01)

SR:

10,900

(01)

SR:

1,900

SR:

7,250

LR:

10,400

(01)

LR:

67,800

(01)

LR:

8,800

LR:

57,400

LR:

2,600

(01)

LR:

17,200

(01)

LR:

1,750

LR:

11,400

Table 1 : Accomplishment Timescale table

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

NOTE: Grace Period for the threshold (whichever occurs first) :

- 24 months from the Service Bulletin Revision No. 05 issuance

- 10,350 FC

- 69,870 FH

NOTE: Grace Period for the interval (whichever occurs first) :

- 24 months from the Service Bulletin Revision No. 05 issuance

- 8,760 FC

- 59,160 FH

NOTE (01): On aircraft pre Mod. No. 41652S12091, the threshold is only valid from

accomplishment of Service Bulletin No. A340-57-4036 or embodiment of

the Mod. No. 43577S12677.

NOTE (02): Mandatory inspection is based on airworthiness considerations but

we recommend to perform the inspection according to recommended

thresholds and intervals to prevent large repairs.

CONFIG. SB MOD No.

PROPOSED COMPLIANCE

RECOMMENDED NOT BEFORE WHICHEVER

OCCURS LATEST :

Flight Cycles (FC) Flight Hours (FH)

001 A340-57-4098 9,900 61,800

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever

occurs latest.

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

**CONF 002

Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long

Range, Threshold/Interval (LR)) have been established. Both sets ensure continued

airworthiness and could be used to cover any type of A/C utilization. This approach

is an equivalent damage approach corresponding to a trade off between FC/FH to

better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued

airworthiness and could be used to cover any type of utilization, for the 1st inspection

and the repetitive ones, operators may select either SR (Threshold or Interval) or LR

(Threshold or Interval) (depending of the A/C utilization evolution). If a non optimal

set of threshold / interval is selected, airworthiness will be ensured, but will penalize

the operator because the inspection will be performed sooner than necessary. As a

consequence, the selection of SR or LR threshold and subsequent intervals can be

changed whenever. Threshold and Interval are whichever occurs first between FC and

FH for a selected set of threshold/interval between SR and LR. This means that the set

FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa).

Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or

582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection

which is requested at the inspection threshold of this Service Bulletin.

Accomplishment of this Service Bulletin is required within the following thresholds and

intervals, whichever occurs first :

CONFIG. MANDATORY

THRESHOLD

MANDATORY

INTERVAL

RECOMMENDED

THRESHOLD (02)

RECOMMENDED

INTERVAL (02)

002 Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

SR:

12,100

SR:

45,600

SR:

8,600

SR:

32,400

SR:

3,550

SR:

14,300

SR:

1,800

SR:

7,150

LR:

11,000

LR:

71,800

LR:

7,800

LR:

50,900

LR:

2,950

LR:

20,200

LR:

1,450

LR:

10,100

Table 1 : Accomplishment Timescale table

NOTE: Grace Period for the threshold (whichever occurs first) :

- 24 months from the Service Bulletin Revision No. 05 issuance

- 10,960 FC

- 74,040 FH

NOTE: Grace Period for the interval (whichever occurs first) :

- 24 months from the Service Bulletin Revision No. 05 issuance

- 7,780 FC

- 52,510 FH

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

NOTE (02): Mandatory inspection is based on airworthiness considerations but

we recommend to perform the inspection according to recommended

thresholds and intervals to prevent large repairs.

CONFIG. SB MOD No. PROPOSED COMPLIANCE

RECOMMENDED NOT BEFORE WHICHEVER

OCCURS LATEST :

Flight Cycles (FC) Flight Hours (FH)

002 A340-57-4106 10,250 63,200

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever

occurs latest.

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

**CONF 003

Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long

Range, Threshold/Interval (LR)) have been established. Both sets ensure continued

airworthiness and could be used to cover any type of A/C utilization. This approach

is an equivalent damage approach corresponding to a trade off between FC/FH to

better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued

airworthiness and could be used to cover any type of utilization, for the 1st inspection

and the repetitive ones, operators may select either SR (Threshold or Interval) or LR

(Threshold or Interval) (depending of the A/C utilization evolution). If a non optimal

set of threshold / interval is selected, airworthiness will be ensured, but will penalize

the operator because the inspection will be performed sooner than necessary. As a

consequence, the selection of SR or LR threshold and subsequent intervals can be

changed whenever. Threshold and Interval are whichever occurs first between FC and

FH for a selected set of threshold/interval between SR and LR. This means that the set

FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa).

Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or

582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection

which is requested at the inspection threshold of this Service Bulletin.

Accomplishment of this Service Bulletin is required within the following thresholds and

intervals, whichever occurs first :

CONFIG. MANDATORY

THRESHOLD

MANDATORY

INTERVAL

RECOMMENDED

THRESHOLD (02)

RECOMMENDED

INTERVAL (02)

003 Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

SR:

12,100

SR:

45,600

SR:

8,600

SR:

32,400

SR:

5,050

SR:

19,000

SR:

2,150

SR:

8,250

LR:

11,000

LR:

71,800

LR:

7,800

LR:

50,900

LR:

4,550

LR:

29,900

LR:

1,950

LR:

12,900

Table 1 : Accomplishment Timescale table

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

NOTE: Grace Period for the threshold (whichever occurs first) :

- 24 months from the Service Bulletin Revision No. 05 issuance

- 10,960 FC

- 74,040 FH

NOTE: Grace Period for the interval (whichever occurs first) :

- 24 months from the Service Bulletin Revision No. 05 issuance

- 7,780 FC

- 52,510 FH

NOTE (02): Mandatory inspection is based on airworthiness considerations but

we recommend to perform the inspection according to recommended

thresholds and intervals to prevent large repairs.

CONFIG. SB MOD No. PROPOSED COMPLIANCE

RECOMMENDED NOT BEFORE WHICHEVER

OCCURS LATEST :

Flight Cycles (FC) Flight Hours (FH)

003 A340-57-4106 10,250 63,200

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever

occurs latest.

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

**CONF 005

Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long

Range, Threshold/Interval (LR)) have been established. Both sets ensure continued

airworthiness and could be used to cover any type of A/C utilization. This approach

is an equivalent damage approach corresponding to a trade off between FC/FH to

better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued

airworthiness and could be used to cover any type of utilization, for the 1st inspection

and the repetitive ones, operators may select either SR (Threshold or Interval) or LR

(Threshold or Interval) (depending of the A/C utilization evolution). If a non optimal

set of threshold / interval is selected, airworthiness will be ensured, but will penalize

the operator because the inspection will be performed sooner than necessary. As a

consequence, the selection of SR or LR threshold and subsequent intervals can be

changed whenever. Threshold and Interval are whichever occurs first between FC and

FH for a selected set of threshold/interval between SR and LR. This means that the set

FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 12

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@A340

SERVICE BULLETIN

Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or

582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection

which is requested at the inspection threshold of this Service Bulletin.

Accomplishment of this Service Bulletin is required within the following thresholds and

intervals, whichever occurs first :

CONFIG. MANDATORY

THRESHOLD

MANDATORY

INTERVAL

RECOMMENDED

THRESHOLD (02)

RECOMMENDED

INTERVAL (02)

005 Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

SR:

11,400

(01)

SR:

43,100

(01)

SR:

9,650

SR:

36,500

SR:

2,900

(01)

SR:

10,900

(01)

SR:

1,900

SR:

7,250

LR:

10,400

(01)

LR:

67,800

(01)

LR:

8,800

LR:

57,400

LR:

2,600

(01)

LR:

17,200

(01)

LR:

1,750

LR:

11,400

Table 1 : Accomplishment Timescale table

NOTE: Grace Period for the threshold (whichever occurs first) :

- 24 months from the Service Bulletin Revision No. 05 issuance

- 10,350 FC

- 69,870 FH

NOTE: Grace Period for the interval (whichever occurs first) :

- 24 months from the Service Bulletin Revision No. 05 issuance

- 8,760 FC

- 59,160 FH

NOTE (01): On aircraft pre Mod. No. 41652S12091, the threshold is only valid from

accomplishment of Service Bulletin No. A340-57-4036 or embodiment of

the Mod. No. 43577S12677.

NOTE (02): Mandatory inspection is based on airworthiness considerations but

we recommend to perform the inspection according to recommended

thresholds and intervals to prevent large repairs.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 13

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SERVICE BULLETIN

CONFIG. SB MOD No. PROPOSED COMPLIANCE

RECOMMENDED NOT BEFORE WHICHEVER

OCCURS LATEST :

Flight Cycles (FC) Flight Hours (FH)

005 A340-57-4098 9,900 61,800

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever

occurs latest.

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

**CONF 007

Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long

Range, Threshold/Interval (LR)) have been established. Both sets ensure continued

airworthiness and could be used to cover any type of A/C utilization. This approach

is an equivalent damage approach corresponding to a trade off between FC/FH to

better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued

airworthiness and could be used to cover any type of utilization, for the 1st inspection

and the repetitive ones, operators may select either SR (Threshold or Interval) or LR

(Threshold or Interval) (depending of the A/C utilization evolution). If a non optimal

set of threshold / interval is selected, airworthiness will be ensured, but will penalize

the operator because the inspection will be performed sooner than necessary. As a

consequence, the selection of SR or LR threshold and subsequent intervals can be

changed whenever. Threshold and Interval are whichever occurs first between FC and

FH for a selected set of threshold/interval between SR and LR. This means that the set

FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa).

Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or

582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection

which is requested at the inspection threshold of this Service Bulletin.

Accomplishment of this Service Bulletin is required within the following thresholds and

intervals, whichever occurs first :

CONFIG. MANDATORY

THRESHOLD

MANDATORY

INTERVAL

RECOMMENDED

THRESHOLD (02)

RECOMMENDED

INTERVAL (02)

007 Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

SR:

12,100

SR:

45,600

SR:

8,600

SR:

32,400

SR:

5,050

SR:

19,000

SR:

2,150

SR:

8,250

LR:

11,000

LR:

71,800

LR:

7,800

LR:

50,900

LR:

4,550

LR:

29,900

LR: 1,950 LR:

12,900

Table 1 : Accomplishment Timescale table

NOTE: Grace Period for the threshold (whichever occurs first) :

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 14

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SERVICE BULLETIN

- 24 months from the Service Bulletin Revision No. 05 issuance

- 16,950 FC

- 33,900 FH

NOTE: Grace Period for the interval (whichever occurs first) :

- 24 months from the Service Bulletin Revision No. 05 issuance

- 12,020 FC

- 24,040 FH

NOTE (02): Mandatory inspection is based on airworthiness considerations but

we recommend to perform the inspection according to recommended

thresholds and intervals to prevent large repairs.

CONFIG. SB MOD No. PROPOSED COMPLIANCE

RECOMMENDED NOT BEFORE WHICHEVER

OCCURS LATEST :

Flight Cycles (FC) Flight Hours (FH)

007 A340-57-4106 10,250 63,200

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever

occurs latest.

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

**CONF 008

Two sets of thresholds/intervals (Short Range, Threshold/Interval (SR) and Long

Range, Threshold/Interval (LR)) have been established. Both sets ensure continued

airworthiness and could be used to cover any type of A/C utilization. This approach

is an equivalent damage approach corresponding to a trade off between FC/FH to

better suit the fleet utilization. As the both sets of thresholds/intervals ensure continued

airworthiness and could be used to cover any type of utilization, for the 1st inspection

and the repetitive ones, operators may select either SR (Threshold or Interval) or LR

(Threshold or Interval) (depending of the A/C utilization evolution). If a non optimal

set of threshold / interval is selected, airworthiness will be ensured, but will penalize

the operator because the inspection will be performed sooner than necessary. As a

consequence, the selection of SR or LR threshold and subsequent intervals can be

changed whenever. Threshold and Interval are whichever occurs first between FC and

FH for a selected set of threshold/interval between SR and LR. This means that the set

FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa).

Inspection in accordance with AIRBUS Technical Disposition Ref F57D03012810 or

582.0651/2002 satisfies the inspection requirements for the first rotating probe inspection

which is requested at the inspection threshold of this Service Bulletin.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 15

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@A340

SERVICE BULLETIN

Accomplishment of this Service Bulletin is required within the following thresholds and

intervals, whichever occurs first :

CONFIG. MANDATORY

THRESHOLD

MANDATORY

INTERVAL

RECOMMENDED

THRESHOLD (02)

RECOMMENDED

INTERVAL (02)

008 Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

Flight

Cycles

(FC)

Flight

Hours

(FH)

SR:

16,600

SR:

62,600

SR:

8,600

SR:

32,400

SR:

10,000

SR:

40,200

SR:

2,150

SR:

8,250

LR:

15,100

LR:

98,400

LR:

7,800

LR:

50,900

LR:

8,350

LR:

56,600

LR:

1,950

LR:

12,900

Table 1 : Accomplishment Timescale table

NOTE: Grace Period for the threshold (whichever occurs first) :

- 24 months from the Service Bulletin Revision No. 05 issuance

- 15,020 FC

- 101,410 FH

NOTE: Grace Period for the interval (whichever occurs first) :

- 24 months from the Service Bulletin Revision No. 05 issuance

- 7,780 FC

- 52,510 FH

NOTE (02): Mandatory inspection is based on airworthiness considerations but

we recommend to perform the inspection according to recommended

thresholds and intervals to prevent large repairs.

CONFIG. SB MOD No. PROPOSED COMPLIANCE

RECOMMENDED NOT BEFORE WHICHEVER

OCCURS LATEST :

Flight Cycles (FC) Flight Hours (FH)

008 A340-57-4106 10,250 63,200

Table 2 : SB Mod. are recommended NOT to be applied before the following thresholds whichever

occurs latest.

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 16

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SERVICE BULLETIN

**CONF ALL

F. APPROVAL

The technical content of this document is approved under authority of Design Organization

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 574089-832-801-001: INSPECTION

Get Access 12.00

On Aircraft

Remove the Fastener on the LH Side 1.00

Remove the Fastener on the RH Side 1.00

Do a special detailed inspection of the hole at FR40,

on the LH Side

1.00

Do a special detailed inspection of the hole at FR40,

on the RH Side

1.00

Install the Fastener on the LH Side 1.00

Install the Fastener on the RH Side 1.00

Tests 2.00

Close-Up 15.00

TOTAL MANHOURS 35.00

ELAPSED TIME (HOURS) 30.00

**CONF 002

Task 574089-832-801-001: INSPECTION

Get Access 12.00

On Aircraft

Remove the Fastener on the LH Side 1.00

Remove the Fastener on the RH Side 1.00

Do a special detailed inspection of the hole at FR40,

on the LH Side

1.00

Do a special detailed inspection of the hole at FR40,

on the RH Side

1.00

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 17

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SERVICE BULLETIN

Task 574089-832-801-001: INSPECTION

Install the Fastener on the LH Side 1.00

Install the Fastener on the RH Side 1.00

Tests 2.00

Close-Up 15.00

TOTAL MANHOURS 35.00

ELAPSED TIME (HOURS) 30.00

**CONF 003

Task 574089-832-801-001: INSPECTION

Get Access 12.00

On Aircraft

Remove the Fasteners on the LH Side 2.00

Remove the Fasteners on the RH Side 2.00

Do a special detailed inspection of the holes at FR40,

on the LH Side

3.00

Do a special detailed inspection of the holes at FR40,

on the RH Side

3.00

Install the Fasteners on the LH Side 2.00

Install the Fasteners on the RH Side 2.00

Tests 2.00

Close-Up 15.00

TOTAL MANHOURS 43.00

ELAPSED TIME (HOURS) 35.00

**CONF 005

Task 574089-832-801-001: INSPECTION

Get Access 10.00

On Aircraft

Remove the Fastener on the RH Side 1.00

Do a special detailed inspection of the hole at FR40,

on the RH Side

1.00

Install the Fastener on the RH Side 1.00

Tests 2.00

Close-Up 12.00

TOTAL MANHOURS 27.00

ELAPSED TIME (HOURS) 25.00

**CONF 007

Task 574089-832-801-001: INSPECTION

Get Access 12.00

On Aircraft

Remove the Fasteners on the LH Side 2.00

Remove the Fasteners on the RH Side 2.00

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 18

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@A340

SERVICE BULLETIN

Task 574089-832-801-001: INSPECTION

Do a special detailed inspection of the holes at FR40,

on the LH Side

3.00

Do a special detailed inspection of the holes at FR40,

on the RH Side

3.00

Install the Fasteners on the LH Side 2.00

Install the Fasteners on the RH Side 2.00

Tests 2.00

Close-Up 15.00

TOTAL MANHOURS 43.00

ELAPSED TIME (HOURS) 35.00

**CONF 008

Task 574089-832-801-001: INSPECTION

Get Access 12.00

On Aircraft

Remove the Fasteners on the LH Side 2.00

Remove the Fasteners on the RH Side 2.00

Do a special detailed inspection of the holes at FR40,

on the LH Side

3.00

Do a special detailed inspection of the holes at FR40,

on the RH Side

3.00

Install the Fasteners on the LH Side 2.00

Install the Fasteners on the RH Side 2.00

Tests 2.00

Close-Up 15.00

TOTAL MANHOURS 43.00

ELAPSED TIME (HOURS) 35.00

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-00-00

28-10-00 28-11-00 28-25-00

32-12-00 53-35-13 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01 51-10-06

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 19

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@A340

SERVICE BULLETIN

Service Bulletin (SB) A340-57-4036

A340-57-4098

A340-57-4106

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11

51-76-12

**CONF 002

Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-00-00

28-10-00 28-11-00 28-25-00

32-12-00 53-35-13 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01 51-10-06

Service Bulletin (SB) A340-57-4098

A340-57-4106

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11

51-76-12

**CONF 003

Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-00-00

28-10-00 28-11-00 28-25-00

32-12-00 53-35-13 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01 51-10-06

Service Bulletin (SB) A340-57-4098

A340-57-4106

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11

51-76-12

**CONF 005

Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-00-00

28-10-00 28-11-00 28-25-00

32-12-00 53-35-13 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01 51-10-06

Service Bulletin (SB) A340-57-4036

A340-57-4098

A340-57-4106

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11

51-76-12

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 20

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SERVICE BULLETIN

**CONF 007

Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-00-00

28-10-00 28-11-00 28-25-00

32-12-00 53-35-13 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01 51-10-06

Service Bulletin (SB) A340-57-4098

A340-57-4106

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11

51-76-12

**CONF 008

Aircraft Maintenance Manual (AMM) 12-34-24 20-21-11 28-00-00

28-10-00 28-11-00 28-25-00

32-12-00 53-35-13 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01 51-10-06

Service Bulletin (SB) A340-57-4098

A340-57-4106

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-11 51-44-11

51-76-12

**CONF ALL

K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 571150

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 21

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SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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@A340

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 574089A01R00

Kit 574089A02R01

AIRBUS Material logistics and Suppliers

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 25 90

For ordering by E-mail :airbus.kit@airbus.com

(2) Price and Availability

Kit 574089A01R00

Cost 267.00 USD

Availability 60 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 the Kit(s) before this time, please include a retrofit planning

schedule with your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

Kit 574089A02R01

Cost 207.00 USD

Availability 60 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 the Kit(s) before this time, please include a retrofit planning

schedule with your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

B. INDUSTRY SUPPORT INFORMATION

This Service Bulletin is subject to the Fatigue Test Integration Program. Refer to the FTIP

policy.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 23

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@A340

SERVICE BULLETIN

C. LIST OF COMPONENTS

Kit 574089A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

7 NSA5359-5-18 1 Screw

8 NSA5368PD516B 1 Washer

9 NAS1726-5E 1 Nut

10 NSA5357-5-18 1 Screw

11 EN6115V5-18 1 Screw

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 574089A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

8 NSA5368PD516B 2 Washer

9 NAS1726-5E 3 Nut

13 EN6115V5-14 1 Screw

14 EN6115V5-9 1 Screw

15 NSA5357-5-14 1 Screw

16 NSA5357-5-9 1 Screw

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

Fuel Tank Sealant Polysulfide 09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

(2) Components

None

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 24

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@A340

SERVICE BULLETIN

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

To accomplish this Service Bulletin, it is necessary to use the following tools and

equipment.

Equipment and materials for the check of the holes as per NTM 51-10-01 Part 6.

Tools necessary to do the check by ROTOTEST :

Instrument :

Rototest B588 and rotor standard.

Probe RS35 dia. 6.2 mm (0.244 in.).

Probe RS50 dia. 7.8 mm (0.307 in.).

Calibration standard :

99A53003001001-103 and 99A53003001001-106.

Supplier :

ROHMANN Gmbh

Rudolf Diesel Str.13

67227 FRANKENTHAL

Tel.0 62 33 - 7881

Telex 468602 esro d

GERMANY

(2) Tools

None

(3) Special Tools

None

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 25

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SERVICE BULLETIN

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 574089-832-801-001 - INSPECTION

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: MAKE SURE THE AREA AROUND THE AIRCRAFT IS SAFE BEFORE YOU

START A REFUEL/DEFUEL PROCEDURE. IN THIS SAFE AREA, DO NOT LET

PERSONS: - SMOKE - MAKE SPARKS OR FIRE - USE ANY EQUIPMENT

WHICH IS NOT APPROVED FOR THE TASK. AIRCRAFT FUEL IS FLAMMABLE.

WARNING: OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A FUEL TANK.

THIS WILL PREVENT INJURY OR DAMAGE.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE, TO DO

THIS :

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00.

NOTE: The purpose of flow charts are for information only to show the various

Inspection/Repair phases described in this Service Bulletin.

Task Associated Data

**CONF 001

Zone

141 142

Access

Panel 147AZ 148AZ

Manpower

TOTAL MANHOURS 35.00

ELAPSED TIME (HOURS) 30.00

**CONF 002

Zone

141 142

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

Access

Panel 147AZ 148AZ

Manpower

TOTAL MANHOURS 35.00

ELAPSED TIME (HOURS) 30.00

**CONF 003

Zone

141 142

Access

Panel 147AZ 148AZ

Manpower

TOTAL MANHOURS 43.00

ELAPSED TIME (HOURS) 35.00

**CONF 005

Zone

142

Access

Panel 148AZ

Manpower

TOTAL MANHOURS 27.00

ELAPSED TIME (HOURS) 25.00

**CONF 007

Zone

141 142

Access

Panel 147AZ 148AZ

Manpower

TOTAL MANHOURS 43.00

ELAPSED TIME (HOURS) 35.00

**CONF 008

Zone

141 142

Access

Panel 147AZ 148AZ

Manpower

TOTAL MANHOURS 43.00

ELAPSED TIME (HOURS) 35.00

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 28

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SERVICE BULLETIN

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 574089-910-001-001 - 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

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 20-21-11

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-42-11

51-44-11

51-76-12

1 For the specification of the material numbers (Mat. No.) refer to the CML.

2 Clean the surfaces to be sealed with :

Solvent General

Purpose

11-026 As required

3 Use a non-metallic spatula to remove the sealant and clean the areas with :

Solvent General

Purpose

11-026 As required

4 Drill and deburr the holes (Refer to SRM 51-44-11).

5 Remove and install the fasteners (Refer to SRM 51-42-11).

6 Torque the standard threaded fasteners (Refer to AMM 20-21-11).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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7 If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

8 Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12).

9 On all the fasteners to be installed (wet assembly), apply :

Fuel Tank Sealant

Polysulfide

09-001 As required

10 Install all the fasteners with :

Corrosion Inhibiting

fillet Consistency

09-016 As required

(2) Subtask 574089-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

**CONF 002

(1) Subtask 574089-910-001-001 - 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

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 20-21-11

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-42-11

51-44-11

51-76-12

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

1 For the specification of the material numbers (Mat. No.) refer to the CML.

2 Clean the surfaces to be sealed with :

Solvent General

Purpose

11-026 As required

3 Use a non-metallic spatula to remove the sealant and clean the areas with :

Solvent General

Purpose

11-026 As required

4 Drill and deburr the holes (Refer to SRM 51-44-11).

5 Remove and install the fasteners (Refer to SRM 51-42-11).

6 Torque the standard threaded fasteners (Refer to AMM 20-21-11).

7 If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

8 Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12).

9 On all the fasteners to be installed (wet assembly), apply :

Fuel Tank Sealant

Polysulfide

09-001 As required

10 Install all the fasteners with :

Corrosion Inhibiting

fillet Consistency

09-016 As required

(2) Subtask 574089-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

**CONF 003

(1) Subtask 574089-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 20-21-11

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-42-11

51-44-11

51-76-12

1 For the specification of the material numbers (Mat. No.) refer to the CML.

2 Clean the surfaces to be sealed with :

Solvent General

Purpose

11-026 As required

3 Use a non-metallic spatula to remove the sealant and clean the areas with :

Solvent General

Purpose

11-026 As required

4 Drill and deburr the holes (Refer to SRM 51-44-11).

5 Remove and install the fasteners (Refer to SRM 51-42-11).

6 Torque the standard threaded fasteners (Refer to AMM 20-21-11).

7 If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

8 Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12).

9 On all the fasteners to be installed (wet assembly), apply :

Fuel Tank Sealant

Polysulfide

09-001 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

10 Install all the fasteners with :

Corrosion Inhibiting

fillet Consistency

09-016 As required

(2) Subtask 574089-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

**CONF 005

(1) Subtask 574089-910-001-001 - 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

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 20-21-11

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-42-11

51-44-11

51-76-12

1 For the specification of the material numbers (Mat. No.) refer to the CML.

2 Clean the surfaces to be sealed with :

Solvent General

Purpose

11-026 As required

3 Use a non-metallic spatula to remove the sealant and clean the areas with :

Solvent General

Purpose

11-026 As required

4 Drill and deburr the holes (Refer to SRM 51-44-11).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

5 Remove and install the fasteners (Refer to SRM 51-42-11).

6 Torque the standard threaded fasteners (Refer to AMM 20-21-11).

7 If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

8 Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12).

9 On all the fasteners to be installed (wet assembly), apply :

Fuel Tank Sealant

Polysulfide

09-001 As required

10 Install all the fasteners with :

Corrosion Inhibiting

fillet Consistency

09-016 As required

(2) Subtask 574089-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

**CONF 007

(1) Subtask 574089-910-001-001 - 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

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 20-21-11

Consumable Material List (CML)

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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References

Structural Repair Manual (SRM) 51-24-00

51-42-11

51-44-11

51-76-12

1 For the specification of the material numbers (Mat. No.) refer to the CML.

2 Clean the surfaces to be sealed with :

Solvent General

Purpose

11-026 As required

3 Use a non-metallic spatula to remove the sealant and clean the areas with :

Solvent General

Purpose

11-026 As required

4 Drill and deburr the holes (Refer to SRM 51-44-11).

5 Remove and install the fasteners (Refer to SRM 51-42-11).

6 Torque the standard threaded fasteners (Refer to AMM 20-21-11).

7 If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

8 Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12).

9 On all the fasteners to be installed (wet assembly), apply :

Fuel Tank Sealant

Polysulfide

09-001 As required

10 Install all the fasteners with :

Corrosion Inhibiting

fillet Consistency

09-016 As required

(2) Subtask 574089-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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**CONF 008

(1) Subtask 574089-910-001-001 - 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

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Aircraft Maintenance Manual (AMM) 20-21-11

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-42-11

51-44-11

51-76-12

1 For the specification of the material numbers (Mat. No.) refer to the CML.

2 Clean the surfaces to be sealed with :

Solvent General

Purpose

11-026 As required

3 Use a non-metallic spatula to remove the sealant and clean the areas with :

Solvent General

Purpose

11-026 As required

4 Drill and deburr the holes (Refer to SRM 51-44-11).

5 Remove and install the fasteners (Refer to SRM 51-42-11).

6 Torque the standard threaded fasteners (Refer to AMM 20-21-11).

7 If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

8 Apply the sealant (Refer to SRM 51-24-00) and (Refer to SRM 51-76-12).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

9 On all the fasteners to be installed (wet assembly), apply :

Fuel Tank Sealant

Polysulfide

09-001 As required

10 Install all the fasteners with :

Corrosion Inhibiting

fillet Consistency

09-016 As required

(2) Subtask 574089-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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 574089-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201

28-00-00, Page Block 301

28-10-00, Page Block 301

28-25-00, Page Block 301

32-12-00, Page Block 201

53-35-13, Page Block 401

57-17-11, Page Block 401

(a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201).

(b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block

201).

(c) Put the access platform(s) in position.

(d) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301).

(e) Degas and ventilate the center tank (Refer to AMM 28-00-00 Page Block 301) and

(Refer to AMM 28-10-00 Page Block 301).

(f) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block

401).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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(g) Remove the access panels 191FB for the LH side and 192GB and 192JB for the

RH side (Refer to AMM 53-35-13 Page Block 401).

**CONF 002

(1) Subtask 574089-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201

28-00-00, Page Block 301

28-10-00, Page Block 301

28-25-00, Page Block 301

32-12-00, Page Block 201

53-35-13, Page Block 401

57-17-11, Page Block 401

(a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201).

(b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block

201).

(c) Put the access platform(s) in position.

(d) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301).

(e) Degas and ventilate the center tank (Refer to AMM 28-00-00 Page Block 301) and

(Refer to AMM 28-10-00 Page Block 301).

(f) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block

401).

(g) Remove the access panels 191FB for the LH side and 192GB and 192JB for the

RH side (Refer to AMM 53-35-13 Page Block 401).

**CONF 003

(1) Subtask 574089-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201

28-00-00, Page Block 301

28-10-00, Page Block 301

28-25-00, Page Block 301

32-12-00, Page Block 201

53-35-13, Page Block 401

57-17-11, Page Block 401

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SERVICE BULLETIN

(a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201).

(b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block

201).

(c) Put the access platform(s) in position.

(d) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301).

(e) Degas and ventilate the center tank (Refer to AMM 28-00-00 Page Block 301) and

(Refer to AMM 28-10-00 Page Block 301).

(f) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block

401).

(g) Remove the access panels 191FB for the LH side and 192GB and 192JB for the

RH side (Refer to AMM 53-35-13 Page Block 401).

**CONF 005

(1) Subtask 574089-941-001-002 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201

28-00-00, Page Block 301

28-10-00, Page Block 301

28-25-00, Page Block 301

32-12-00, Page Block 201

53-35-13, Page Block 401

57-17-11, Page Block 401

(a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201).

(b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block

201).

(c) Put the access platform(s) in position.

(d) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301).

(e) Degas and ventilate the center tank (Refer to AMM 28-00-00 Page Block 301) and

(Refer to AMM 28-10-00 Page Block 301).

(f) Remove the access cover 148AZ (Refer to AMM 57-17-11 Page Block 401).

(g) Remove the access panels 192GB and 192JB (Refer to AMM 53-35-13 Page Block

401).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

**CONF 007

(1) Subtask 574089-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201

28-00-00, Page Block 301

28-10-00, Page Block 301

28-25-00, Page Block 301

32-12-00, Page Block 201

53-35-13, Page Block 401

57-17-11, Page Block 401

(a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201).

(b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block

201).

(c) Put the access platform(s) in position.

(d) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301).

(e) Degas and ventilate the center tank (Refer to AMM 28-00-00 Page Block 301) and

(Refer to AMM 28-10-00 Page Block 301).

(f) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block

401).

(g) Remove the access panels 191FB for the LH side and 192GB and 192JB for the

RH side (Refer to AMM 53-35-13 Page Block 401).

**CONF 008

(1) Subtask 574089-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 12-34-24, Page Block 201

28-00-00, Page Block 301

28-10-00, Page Block 301

28-25-00, Page Block 301

32-12-00, Page Block 201

53-35-13, Page Block 401

57-17-11, Page Block 401

(a) Make sure that the aircraft is grounded (Refer to AMM 12-34-24 Page Block 201).

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SERVICE BULLETIN

(b) Open the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00 Page Block

201).

(c) Put the access platform(s) in position.

(d) Defuel the center tank (Refer to AMM 28-25-00 Page Block 301).

(e) Degas and ventilate the center tank (Refer to AMM 28-00-00 Page Block 301) and

(Refer to AMM 28-10-00 Page Block 301).

(f) Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block

401).

(g) Remove the access panels 191FB for the LH side and 192GB and 192JB for the

RH side (Refer to AMM 53-35-13 Page Block 401).

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 574089-010-001-001 - Remove the Fastener on the LH Side

Work Zones and Access Panels

Zone Access/Work location

141 Access Panel 147AZ

Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 2

Subtask elapsed time 0.50

Skills AIRFRAME

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

Fig. A-FCAAA

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Depending on fasteners installed, remove :

Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02

1 screw Item (7) Discard

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SERVICE BULLETIN

or

1 screw Item (10) Discard

1 nut Item (9) Discard

and if installed

1 washer Item (8) Discard

(b) Remove the sealant and clean the areas with:

Solvent General

Purpose

11-026 As required

(2) Subtask 574089-010-002-001 - Remove the Fastener on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 2

Subtask elapsed time 0.50

Skills AIRFRAME

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

Fig. A-FCAAA

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Depending on fasteners installed, remove :

Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02

1 screw Item (7) Discard

or

1 screw Item (10) Discard

1 nut Item (9) Discard

and if installed

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1 washer Item (8) Discard

(b) Remove the sealant and clean the areas with:

Solvent General

Purpose

11-026 As required

(3) Subtask 574089-832-007-001 - Do a special detailed inspection of the hole at FR40,

on the LH Side

Work Zones and Access Panels

Zone Access/Work location

141 Access Panel 147AZ

Work location Frame 40

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) 51-10-01 Part 6

Service Bulletin (SB) A340-57-4098

Fig. A-FBAAA

Area to Inspect

Sheet 01

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

(a) For the inspection area, refer to Fig. A-FBAAA Sheet 01.

At the threshold given in the Planning Information Paragraph E.(2).

(b) Do a special detailed inspection of the hole at FR40, refer to Fig. A-FFAAA Sheet

01, Fig. A-FFAAA Sheet 02.

Do a rotating probe inspection, refer to NTM 51-10-01 Part 6.

1 If no crack is found:

- Accomplish Service Bulletin No.A340-57-4098 at the thresholds given in

Planning Information Paragraph E.(2).

or

- Refer to SUBTASK 574089-410-001 001 Install the Fastener on the LH

Side .

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2 If a crack is found:

- Contact Airbus before next flight.

(c) For the inspection report, refer to Appendix 01 - Inspection Report .

(4) Subtask 574089-832-008-001 - Do a special detailed inspection of the hole at FR40,

on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

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) 51-10-01 Part 6

Service Bulletin (SB) A340-57-4098

Fig. A-FBAAA

Area to Inspect

Sheet 01

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

(a) For the inspection area, refer to Fig. A-FBAAA Sheet 01.

At the threshold given in the Planning Information Paragraph E.(2).

(b) Do a special detailed inspection of the hole at FR40, refer to Fig. A-FFAAA Sheet

01, Fig. A-FFAAA Sheet 02.

Do a rotating probe inspection, refer to NTM 51-10-01 Part 6.

1 If no crack is found:

- Accomplish Service Bulletin No.A340-57-4098 at the thresholds given in

Planning Information Paragraph E.(2).

or

- Refer to SUBTASK 574089-410-002 001 Install the Fastener on the RH

Side .

2 If a crack is found:

- Contact Airbus before next flight.

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(c) For the inspection report, refer to Appendix 01 - Inspection Report .

(5) Subtask 574089-410-001-001 - Install the Fastener on the LH Side

Work Zones and Access Panels

Zone Access/Work location

141 Access Panel 147AZ

Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 2

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Kit 574089A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

7 NSA5359-5-18 1 Screw

8 NSA5368PD516B 1 Washer

9 NAS1726-5E 1 Nut

10 NSA5357-5-18 1 Screw

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-06 Part 6

Structural Repair Manual (SRM) 51-24-00

51-44-11

51-76-12

Fig. A-FCAAA

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Clean the hole with:

Solvent General

Purpose

11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 45

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@A340

SERVICE BULLETIN

(b) Do a check of the diameter of the hole, refer to the table 9 of the SRM 51-44-11.

1 If the diameter do not respect the tolerance of the table 9:

a Ream hole to second oversize, refer to the table 10 of the SRM

51-44-11.

b Install:

Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02

1 screw NSA5359-5-18 Item 7

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

2 If the diameter respect the tolerance of the table 9:

a Install:

Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02

1 nut NAS1726-5E Item 9

1 screw NSA5357-5-18 Item 10

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

(c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12:

Corrosion Inhibiting

fillet Consistency

09-016 As required

(d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2),

refer to NTM 51-10-06 Part 6.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 46

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(6) Subtask 574089-410-002-001 - Install the Fastener on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 2

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Kit 574089A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

7 NSA5359-5-18 1 Screw

8 NSA5368PD516B 1 Washer

9 NAS1726-5E 1 Nut

10 NSA5357-5-18 1 Screw

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-06 Part 6

Structural Repair Manual (SRM) 51-24-00

51-44-11

51-76-12

Fig. A-FCAAA

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Clean the hole with:

Solvent General

Purpose

11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 47

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@A340

SERVICE BULLETIN

(b) Do a check of the diameter of the hole, refer to the table 9 of the SRM 51-44-11.

1 If the diameter do not respect the tolerance of the table 9:

a Ream hole to second oversize, refer to the table 10 of the SRM

51-44-11.

b Install:

Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02

1 screw NSA5359-5-18 Item 7

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

2 If the diameter respect the tolerance of the table 9:

a Install:

Refer to Fig. A-FCAAA Sheet 01, Fig. A-FCAAA Sheet 02

1 nut NAS1726-5E Item 9

1 screw NSA5357-5-18 Item 10

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

(c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12:

Corrosion Inhibiting

fillet Consistency

09-016 As required

(d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2),

refer to NTM 51-10-06 Part 6.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 48

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@A340

SERVICE BULLETIN

**CONF 002

(1) Subtask 574089-010-001-002 - Remove the Fastener on the LH Side

Work Zones and Access Panels

Zone Access/Work location

141 Access Panel 147AZ

Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 2

Subtask elapsed time 0.50

Skills AIRFRAME

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

Fig. A-FCAAB

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Depending on fasteners installed, remove :

Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02

1 screw Item (7) Discard

or

1 screw Item (10) Discard

or

1 screw Item (11) Discard

1 nut Item (9) Discard

and if installed

1 washer Item (8) Discard

(b) Remove the sealant and clean the areas with:

Solvent General

Purpose

11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 49

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@A340

SERVICE BULLETIN

(2) Subtask 574089-010-002-002 - Remove the Fastener on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 2

Subtask elapsed time 0.50

Skills AIRFRAME

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

Fig. A-FCAAB

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Depending on fasteners installed, remove :

Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02

1 screw Item (7) Discard

or

1 screw Item (10) Discard

or

1 screw Item (11) Discard

1 nut Item (9) Discard

and if installed

1 washer Item (8) Discard

(b) Remove the sealant and clean the areas with:

Solvent General

Purpose

11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 50

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(3) Subtask 574089-832-007-002 - Do a special detailed inspection of the hole at FR40,

on the LH Side

Work Zones and Access Panels

Zone Access/Work location

141 Access Panel 147AZ

Work location Frame 40

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) 51-10-01 Part 6

Service Bulletin (SB) A340-57-4106

Fig. A-FBAAB

Area to Inspect

Sheet 01

Fig. A-FFAAB

Flow Chart

Sheet 01

Sheet 02

Sheet 03

(a) For the inspection area, refer to Fig. A-FBAAB Sheet 01.

At the threshold given in the Planning Information Paragraph E.(2).

(b) Do a special detailed inspection of the hole at FR40, refer to Fig. A-FFAAB Sheet

01, Fig. A-FFAAB Sheet 02, Fig. A-FFAAB Sheet 03.

Do a rotating probe inspection, refer to NTM 51-10-01 Part 6.

1 If no crack is found:

- Accomplish Service Bulletin No. A340-57-4106 at the thresholds given in

Planning Information Paragraph E.(2).

or

- Refer to SUBTASK 574089-410-001 002 Install the Fastener on the LH

Side .

2 If a crack is found:

- Contact Airbus before next flight.

(c) For the inspection report, refer to Appendix 01 - Inspection Report .

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 51

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(4) Subtask 574089-832-008-002 - Do a special detailed inspection of the hole at FR40,

on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

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) 51-10-01 Part 6

Service Bulletin (SB) A340-57-4106

Fig. A-FBAAB

Area to Inspect

Sheet 01

Fig. A-FFAAB

Flow Chart

Sheet 01

Sheet 02

Sheet 03

(a) For the inspection area, refer to Fig. A-FBAAB Sheet 01.

At the threshold given in the Planning Information Paragraph E.(2).

(b) Do a special detailed inspection of the hole at FR40, refer to Fig. A-FFAAB Sheet

01, Fig. A-FFAAB Sheet 02, Fig. A-FFAAB Sheet 03.

Do a rotating probe inspection, refer to NTM 51-10-01 Part 6.

1 If no crack is found:

- Accomplish Service Bulletin No.A340-57-4106 at the thresholds given in

Planning Information Paragraph E.(2).

or

- Refer to SUBTASK 574089-410-002 002 Install the Fastener on the RH

Side .

2 If a crack is found:

- Contact Airbus before next flight.

(c) For the inspection report, refer to Appendix 01 - Inspection Report .

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 52

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

(5) Subtask 574089-410-001-002 - Install the Fastener on the LH Side

Work Zones and Access Panels

Zone Access/Work location

141 Access Panel 147AZ

Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 2

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Kit 574089A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

7 NSA5359-5-18 1 Screw

8 NSA5368PD516B 1 Washer

9 NAS1726-5E 1 Nut

10 NSA5357-5-18 1 Screw

11 EN6115V5-18 1 Screw

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-06 Part 6

Structural Repair Manual (SRM) 51-24-00

51-44-11

51-76-12

Fig. A-FCAAB

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Clean the hole with:

Solvent General

Purpose

11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 53

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@A340

SERVICE BULLETIN

(b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11.

1 If the diameter do not respect the tolerance of the table 8:

a Do a check of the diameter of the hole, refer to the table 9 and 10 of the

SRM 51-44-11.

<1> If the diameter do not respect the tolerance of the table 9:

- The diameter is included between the First oversize and the

Second oversize:

. Ream the Hole to Second oversize, refer to table 10 of the

SRM 51-44-11 and install:

Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02

1 screw NSA5359-5-18 Item 7

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

- The diameter is included between the Nominal diameter and the

First oversize:

. Ream the Hole to First oversize, refer to table 9 of the

SRM 51-44-11 and install:

Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02

1 screw NSA5357-5-18 Item 10

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

<2> If the diameter respect the tolerance of the table 9:

- Install:

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 54

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02

1 screw NSA5357-5-18 Item 10

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

2 If the diameter respect the tolerance of the table 8:

a Install:

Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02

1 screw EN6115V5-18 Item 11

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

(c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12:

Corrosion Inhibiting

fillet Consistency

09-016 As required

(d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2),

refer to NTM 51-10-06 Part 6.

(6) Subtask 574089-410-002-002 - Install the Fastener on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 55

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Manhours 1.00

Minimum number of person 2

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Kit 574089A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

7 NSA5359-5-18 1 Screw

8 NSA5368PD516B 1 Washer

9 NAS1726-5E 1 Nut

10 NSA5357-5-18 1 Screw

11 EN6115V5-18 1 Screw

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-06 Part 6

Structural Repair Manual (SRM) 51-24-00

51-44-11

51-76-12

Fig. A-FCAAB

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Clean the hole with:

Solvent General

Purpose

11-026 As required

(b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11.

1 If the diameter do not respect the tolerance of the table 8:

a Do a check of the diameter of the hole, refer to the table 9 and 10 of the

SRM 51-44-11.

<1> If the diameter do not respect the tolerance of the table 9:

- The diameter is included between the First oversize and the

Second oversize:

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 56

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@A340

SERVICE BULLETIN

. Ream the Hole to Second oversize, refer to table 10 of the

SRM 51-44-11 and install:

Refer toFig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02

1 screw NSA5359-5-18 Item 7

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

- The diameter is included between the Nominal diameter and the

First oversize:

. Ream the Hole to First oversize, refer to table 9 of the

SRM 51-44-11 and install:

Refer toFig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02

1 screw NSA5357-5-18 Item 10

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

<2> If the diameter respect the tolerance of the table 9:

- Install:

Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02

1 screw NSA5357-5-18 Item 10

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 57

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@A340

SERVICE BULLETIN

Fuel Tank Sealant

Polysulfide

09-001 As required

2 If the diameter respect the tolerance of the table 8:

a Install:

Refer to Fig. A-FCAAB Sheet 01, Fig. A-FCAAB Sheet 02

1 screw EN6115V5-18 Item 11

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

(c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12:

Corrosion Inhibiting

fillet Consistency

09-016 As required

(d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2),

refer to NTM 51-10-06 Part 6.

**CONF 003

(1) Subtask 574089-010-001-004 - Remove the Fasteners on the LH Side

Work Zones and Access Panels

Zone Access/Work location

141 Access Panel 147AZ

Work location Frame 40

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

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 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 58

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

References

Fig. A-FCAAD

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Depending on fasteners installed, remove from the hole A :

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw Item (15) Discard

1 nut Item (9) Discard

or

1 screw Item (13) Discard

1 nut Item (9) Discard

and if installed

1 washer Item (8) Discard

(b) Depending on fasteners installed, remove from the hole B :

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw Item (16) Discard

1 nut Item (9) Discard

or

1 screw Item (14) Discard

1 nut Item (9) Discard

and if installed

1 washer Item (8) Discard

(c) Remove the sealant and clean the areas with:

Solvent General

Purpose

11-026 As required

(2) Subtask 574089-010-002-004 - Remove the Fasteners on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 59

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

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

Fig. A-FCAAD

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Depending on fasteners installed, remove from the hole A :

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw Item (15) Discard

1 nut Item (9) Discard

or

1 screw Item (13) Discard

1 nut Item (9) Discard

and if installed

1 washer Item (8) Discard

(b) Depending on fasteners installed, remove from the hole B :

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw Item (16) Discard

1 nut Item (9) Discard

or

1 screw Item (14) Discard

1 nut Item (9) Discard

and if installed

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 60

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@A340

SERVICE BULLETIN

1 washer Item (8) Discard

(c) Remove the sealant and clean the areas with:

Solvent General

Purpose

11-026 As required

(3) Subtask 574089-832-007-004 - Do a special detailed inspection of the holes at

FR40, on the LH Side

Work Zones and Access Panels

Zone Access/Work location

141 Access Panel 147AZ

Work location Frame 40

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6

Service Bulletin (SB) A340-57-4106

Fig. A-FBAAD

Area to Inspect

Sheet 01

Fig. A-FFAAD

Flow Chart

Sheet 01

Sheet 02

Sheet 03

(a) For the inspection area, refer to Fig. A-FBAAD Sheet 01.

At the threshold given in the Planning Information Paragraph E.(2).

(b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAD Sheet

01, Fig. A-FFAAD Sheet 02, Fig. A-FFAAD Sheet 03.

Do a rotating probe inspection, refer to NTM 51-10-01 Part 6.

1 If no crack is found:

- Accomplish Service Bulletin No.A340-57-4106 at the thresholds given in

Planning Information Paragraph E.(2).

or

- Refer to SUBTASK 574089-410-001 004 Install the Fasteners on the LH

Side .

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 61

5

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@A340

SERVICE BULLETIN

2 If a crack is found:

- Contact Airbus before next flight.

(c) For the inspection report, refer to Appendix 01 - Inspection Report .

(4) Subtask 574089-832-008-004 - Do a special detailed inspection of the holes at

FR40, on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6

Service Bulletin (SB) A340-57-4106

Fig. A-FBAAD

Area to Inspect

Sheet 01

Fig. A-FFAAD

Flow Chart

Sheet 01

Sheet 02

Sheet 03

(a) For the inspection area, refer to Fig. A-FBAAD Sheet 01.

At the threshold given in the Planning Information Paragraph E.(2).

(b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAD Sheet

01, Fig. A-FFAAD Sheet 02, Fig. A-FFAAD Sheet 03.

Do a rotating probe inspection, refer to NTM 51-10-01 Part 6.

1 If no crack is found:

- Accomplish Service Bulletin No.A340-57-4106 at the thresholds given in

Planning Information Paragraph E.(2).

or

- Refer to SUBTASK 574089-410-002 004 Install the Fasteners on the RH

Side .

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 62

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@A340

SERVICE BULLETIN

2 If a crack is found:

- Contact Airbus before next flight.

(c) For the inspection report, refer to Appendix 01 - Inspection Report .

(5) Subtask 574089-410-001-004 - Install the Fasteners on the LH Side

Work Zones and Access Panels

Zone Access/Work location

141 Access Panel 147AZ

Work location Frame 40

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 574089A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 NSA5368PD516B 2 Washer

9 NAS1726-5E 2 Nut

13 EN6115V5-14 1 Screw

14 EN6115V5-9 1 Screw

15 NSA5357-5-14 1 Screw

16 NSA5357-5-9 1 Screw

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-06 Part 6

Structural Repair Manual (SRM) 51-24-00

51-44-11

51-76-12

Fig. A-FCAAD

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 63

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@A340

SERVICE BULLETIN

(a) Clean the hole with:

Solvent General

Purpose

11-026 As required

(b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11.

1 If the diameter do not respect the tolerance of the table 8:

a Ream holes to first oversize, refer to the table 9 of the SRM 51-44-11.

b Install for the hole A:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw NSA5357-5-14 Item 15

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

c Install for the hole B:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw NSA5357-5-9 Item 16

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

2 If the diameter respect the tolerance of the table 8:

a Install for the hole A:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw EN6115V5-14 Item 13

1 nut NAS1726-5E Item 9

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 64

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@A340

SERVICE BULLETIN

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

b Install for the hole B:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw EN6115V5-9 Item 14

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

(c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12:

Corrosion Inhibiting

fillet Consistency

09-016 As required

(d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2),

refer to NTM 51-10-06 Part 6.

(6) Subtask 574089-410-002-004 - Install the Fasteners on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 65

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@A340

SERVICE BULLETIN

Material necessary to do the job

Kit 574089A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 NSA5368PD516B 2 Washer

9 NAS1726-5E 2 Nut

13 EN6115V5-14 1 Screw

14 EN6115V5-9 1 Screw

15 NSA5357-5-14 1 Screw

16 NSA5357-5-9 1 Screw

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-06 Part 6

Structural Repair Manual (SRM) 51-24-00

51-44-11

51-76-12

Fig. A-FCAAD

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Clean the hole with:

Solvent General

Purpose

11-026 As required

(b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11.

1 If the diameter do not respect the tolerance of the table 8:

a Ream holes to first oversize, refer to the table 9 of the SRM 51-44-11.

b Install for the hole A:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw NSA5357-5-14 Item 15

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 66

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@A340

SERVICE BULLETIN

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

c Install for the hole B:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw NSA5357-5-9 Item 16

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

2 If the diameter respect the tolerance of the table 8:

a Install for the hole A:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw EN6115V5-14 Item 13

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

b Install for the hole B:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw EN6115V5-9 Item 14

or

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 67

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@A340

SERVICE BULLETIN

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

(c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12:

Corrosion Inhibiting

fillet Consistency

09-016 As required

(d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2),

refer to NTM 51-10-06 Part 6.

**CONF 005

(1) Subtask 574089-010-002-003 - Remove the Fastener on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 2

Subtask elapsed time 0.50

Skills AIRFRAME

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

Fig. A-FCAAC

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Depending on fasteners installed, remove :

Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02

1 screw Item (7) Discard

or

1 screw Item (10) Discard

1 nut Item (9) Discard

and if installed

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 68

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@A340

SERVICE BULLETIN

1 washer Item (8) Discard

(b) Remove the sealant and clean the areas with:

Solvent General

Purpose

11-026 As required

(2) Subtask 574089-832-008-003 - Do a special detailed inspection of the hole at FR40,

on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

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) 51-10-01 Part 6

Service Bulletin (SB) A340-57-4098

Fig. A-FBAAC

Area to Inspect

Sheet 01

Fig. A-FFAAC

Flow Chart

Sheet 01

Sheet 02

(a) For the inspection area, refer to Fig. A-FBAAC Sheet 01.

At the threshold given in the Planning Information Paragraph E.(2).

(b) Do a special detailed inspection of the hole at FR40, refer to Fig. A-FFAAC Sheet

01, Fig. A-FFAAC Sheet 02.

Do a rotating probe inspection, refer to NTM 51-10-01 Part 6.

1 If no crack is found:

- Accomplish Service Bulletin No.A340-57-4098 at the thresholds given in

Planning Information Paragraph E.(2).

or

- Refer to SUBTASK 574089-410-002 003 Install the Fastener on the RH

Side .

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 69

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@A340

SERVICE BULLETIN

2 If a crack is found:

- Contact Airbus before next flight.

(c) For the inspection report, refer to Appendix 01 - Inspection Report .

(3) Subtask 574089-410-002-003 - Install the Fastener on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 2

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Kit 574089A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

7 NSA5359-5-18 1 Screw

8 NSA5368PD516B 1 Washer

9 NAS1726-5E 1 Nut

10 NSA5357-5-18 1 Screw

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-06 Part 6

Structural Repair Manual (SRM) 51-24-00

51-44-11

51-76-12

Fig. A-FCAAC

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Clean the hole with:

Solvent General

Purpose

11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 70

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@A340

SERVICE BULLETIN

(b) Do a check of the diameter of the hole, refer to the table 9 of the SRM 51-44-11.

1 If the diameter do not respect the tolerance of the table 9:

a Ream hole to second oversize, refer to the table 10 of the SRM

51-44-11.

b Install:

Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02

1 screw NSA5359-5-18 Item 7

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

2 If the diameter respect the tolerance of the table 9:

a Install:

Refer to Fig. A-FCAAC Sheet 01, Fig. A-FCAAC Sheet 02

1 screw NSA5357-5-18 Item 10

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

(c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12:

Corrosion Inhibiting

fillet Consistency

09-016 As required

(d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2),

refer to NTM 51-10-06 Part 6.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 71

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@A340

SERVICE BULLETIN

**CONF 007

(1) Subtask 574089-010-001-004 - Remove the Fasteners on the LH Side

Work Zones and Access Panels

Zone Access/Work location

141 Access Panel 147AZ

Work location Frame 40

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

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

Fig. A-FCAAD

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Depending on fasteners installed, remove from the hole A :

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw Item (15) Discard

1 nut Item (9) Discard

or

1 screw Item (13) Discard

1 nut Item (9) Discard

and if installed

1 washer Item (8) Discard

(b) Depending on fasteners installed, remove from the hole B :

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw Item (16) Discard

1 nut Item (9) Discard

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 72

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@A340

SERVICE BULLETIN

or

1 screw Item (14) Discard

1 nut Item (9) Discard

and if installed

1 washer Item (8) Discard

(c) Remove the sealant and clean the areas with:

Solvent General

Purpose

11-026 As required

(2) Subtask 574089-010-002-004 - Remove the Fasteners on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

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

Fig. A-FCAAD

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Depending on fasteners installed, remove from the hole A :

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw Item (15) Discard

1 nut Item (9) Discard

or

1 screw Item (13) Discard

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 73

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@A340

SERVICE BULLETIN

1 nut Item (9) Discard

and if installed

1 washer Item (8) Discard

(b) Depending on fasteners installed, remove from the hole B :

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw Item (16) Discard

1 nut Item (9) Discard

or

1 screw Item (14) Discard

1 nut Item (9) Discard

and if installed

1 washer Item (8) Discard

(c) Remove the sealant and clean the areas with:

Solvent General

Purpose

11-026 As required

(3) Subtask 574089-832-007-004 - Do a special detailed inspection of the holes at

FR40, on the LH Side

Work Zones and Access Panels

Zone Access/Work location

141 Access Panel 147AZ

Work location Frame 40

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6

Service Bulletin (SB) A340-57-4106

Fig. A-FBAAD

Area to Inspect

Sheet 01

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 74

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@A340

SERVICE BULLETIN

References

Fig. A-FFAAD

Flow Chart

Sheet 01

Sheet 02

Sheet 03

(a) For the inspection area, refer to Fig. A-FBAAD Sheet 01.

At the threshold given in the Planning Information Paragraph E.(2).

(b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAD Sheet

01, Fig. A-FFAAD Sheet 02, Fig. A-FFAAD Sheet 03.

Do a rotating probe inspection, refer to NTM 51-10-01 Part 6.

1 If no crack is found:

- Accomplish Service Bulletin No.A340-57-4106 at the thresholds given in

Planning Information Paragraph E.(2).

or

- Refer to SUBTASK 574089-410-001 004 Install the Fasteners on the LH

Side .

2 If a crack is found:

- Contact Airbus before next flight.

(c) For the inspection report, refer to Appendix 01 - Inspection Report .

(4) Subtask 574089-832-008-004 - Do a special detailed inspection of the holes at

FR40, on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6

Service Bulletin (SB) A340-57-4106

Fig. A-FBAAD

Area to Inspect

Sheet 01

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 75

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@A340

SERVICE BULLETIN

References

Fig. A-FFAAD

Flow Chart

Sheet 01

Sheet 02

Sheet 03

(a) For the inspection area, refer to Fig. A-FBAAD Sheet 01.

At the threshold given in the Planning Information Paragraph E.(2).

(b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAD Sheet

01, Fig. A-FFAAD Sheet 02, Fig. A-FFAAD Sheet 03.

Do a rotating probe inspection, refer to NTM 51-10-01 Part 6.

1 If no crack is found:

- Accomplish Service Bulletin No.A340-57-4106 at the thresholds given in

Planning Information Paragraph E.(2).

or

- Refer to SUBTASK 574089-410-002 004 Install the Fasteners on the RH

Side .

2 If a crack is found:

- Contact Airbus before next flight.

(c) For the inspection report, refer to Appendix 01 - Inspection Report .

(5) Subtask 574089-410-001-004 - Install the Fasteners on the LH Side

Work Zones and Access Panels

Zone Access/Work location

141 Access Panel 147AZ

Work location Frame 40

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 574089A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 NSA5368PD516B 2 Washer

9 NAS1726-5E 2 Nut

13 EN6115V5-14 1 Screw

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 76

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@A340

SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

14 EN6115V5-9 1 Screw

15 NSA5357-5-14 1 Screw

16 NSA5357-5-9 1 Screw

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-06 Part 6

Structural Repair Manual (SRM) 51-24-00

51-44-11

51-76-12

Fig. A-FCAAD

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Clean the hole with:

Solvent General

Purpose

11-026 As required

(b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11.

1 If the diameter do not respect the tolerance of the table 8:

a Ream holes to first oversize, refer to the table 9 of the SRM 51-44-11.

b Install for the hole A:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw NSA5357-5-14 Item 15

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 77

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@A340

SERVICE BULLETIN

c Install for the hole B:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw NSA5357-5-9 Item 16

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

2 If the diameter respect the tolerance of the table 8:

a Install for the hole A:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw EN6115V5-14 Item 13

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

b Install for the hole B:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw EN6115V5-9 Item 14

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 78

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@A340

SERVICE BULLETIN

(c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12:

Corrosion Inhibiting

fillet Consistency

09-016 As required

(d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2),

refer to NTM 51-10-06 Part 6.

(6) Subtask 574089-410-002-004 - Install the Fasteners on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 574089A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 NSA5368PD516B 2 Washer

9 NAS1726-5E 2 Nut

13 EN6115V5-14 1 Screw

14 EN6115V5-9 1 Screw

15 NSA5357-5-14 1 Screw

16 NSA5357-5-9 1 Screw

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-06 Part 6

Structural Repair Manual (SRM) 51-24-00

51-44-11

51-76-12

Fig. A-FCAAD

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 79

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@A340

SERVICE BULLETIN

(a) Clean the hole with:

Solvent General

Purpose

11-026 As required

(b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11.

1 If the diameter do not respect the tolerance of the table 8:

a Ream holes to first oversize, refer to the table 9 of the SRM 51-44-11.

b Install for the hole A:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw NSA5357-5-14 Item 15

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

c Install for the hole B:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw NSA5357-5-9 Item 16

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

2 If the diameter respect the tolerance of the table 8:

a Install for the hole A:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw EN6115V5-14 Item 13

1 nut NAS1726-5E Item 9

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 80

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@A340

SERVICE BULLETIN

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

b Install for the hole B:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw EN6115V5-9 Item 14

or

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

(c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12:

Corrosion Inhibiting

fillet Consistency

09-016 As required

(d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2),

refer to NTM 51-10-06 Part 6.

**CONF 008

(1) Subtask 574089-010-001-004 - Remove the Fasteners on the LH Side

Work Zones and Access Panels

Zone Access/Work location

141 Access Panel 147AZ

Work location Frame 40

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 81

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SERVICE BULLETIN

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Fig. A-FCAAD

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Depending on fasteners installed, remove from the hole A :

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw Item (15) Discard

1 nut Item (9) Discard

or

1 screw Item (13) Discard

1 nut Item (9) Discard

and if installed

1 washer Item (8) Discard

(b) Depending on fasteners installed, remove from the hole B :

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw Item (16) Discard

1 nut Item (9) Discard

or

1 screw Item (14) Discard

1 nut Item (9) Discard

and if installed

1 washer Item (8) Discard

(c) Remove the sealant and clean the areas with:

Solvent General

Purpose

11-026 As required

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 82

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SERVICE BULLETIN

(2) Subtask 574089-010-002-004 - Remove the Fasteners on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

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

Fig. A-FCAAD

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Depending on fasteners installed, remove from the hole A :

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw Item (15) Discard

1 nut Item (9) Discard

or

1 screw Item (13) Discard

1 nut Item (9) Discard

and if installed

1 washer Item (8) Discard

(b) Depending on fasteners installed, remove from the hole B :

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw Item (16) Discard

1 nut Item (9) Discard

or

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 83

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SERVICE BULLETIN

1 screw Item (14) Discard

1 nut Item (9) Discard

and if installed

1 washer Item (8) Discard

(c) Remove the sealant and clean the areas with:

Solvent General

Purpose

11-026 As required

(3) Subtask 574089-832-007-004 - Do a special detailed inspection of the holes at

FR40, on the LH Side

Work Zones and Access Panels

Zone Access/Work location

141 Access Panel 147AZ

Work location Frame 40

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6

Service Bulletin (SB) A340-57-4106

Fig. A-FBAAD

Area to Inspect

Sheet 01

Fig. A-FFAAD

Flow Chart

Sheet 01

Sheet 02

Sheet 03

(a) For the inspection area, refer to Fig. A-FBAAD Sheet 01.

At the threshold given in the Planning Information Paragraph E.(2).

(b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAD Sheet

01, Fig. A-FFAAD Sheet 02, Fig. A-FFAAD Sheet 03.

Do a rotating probe inspection, refer to NTM 51-10-01 Part 6.

1 If no crack is found:

- Accomplish Service Bulletin No.A340-57-4106 at the thresholds given in

Planning Information Paragraph E.(2).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

or

- Refer to SUBTASK 574089-410-001 004 Install the Fasteners on the LH

Side .

2 If a crack is found:

- Contact Airbus before next flight.

(c) For the inspection report, refer to Appendix 01 - Inspection Report .

(4) Subtask 574089-832-008-004 - Do a special detailed inspection of the holes at

FR40, on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

Manpower Resources

Manhours 3.00

Minimum number of person 1

Subtask elapsed time 3.00

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-10-01 Part 6

Service Bulletin (SB) A340-57-4106

Fig. A-FBAAD

Area to Inspect

Sheet 01

Fig. A-FFAAD

Flow Chart

Sheet 01

Sheet 02

Sheet 03

(a) For the inspection area, refer to Fig. A-FBAAD Sheet 01.

At the threshold given in the Planning Information Paragraph E.(2).

(b) Do a special detailed inspection of the holes at FR40, refer to Fig. A-FFAAD Sheet

01, Fig. A-FFAAD Sheet 02, Fig. A-FFAAD Sheet 03.

Do a rotating probe inspection, refer to NTM 51-10-01 Part 6.

1 If no crack is found:

- Accomplish Service Bulletin No.A340-57-4106 at the thresholds given in

Planning Information Paragraph E.(2).

or

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 85

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SERVICE BULLETIN

- Refer to SUBTASK 574089-410-002 004 Install the Fasteners on the RH

Side .

2 If a crack is found:

- Contact Airbus before next flight.

(c) For the inspection report, refer to Appendix 01 - Inspection Report .

(5) Subtask 574089-410-001-004 - Install the Fasteners on the LH Side

Work Zones and Access Panels

Zone Access/Work location

141 Access Panel 147AZ

Work location Frame 40

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 574089A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 NSA5368PD516B 2 Washer

9 NAS1726-5E 2 Nut

13 EN6115V5-14 1 Screw

14 EN6115V5-9 1 Screw

15 NSA5357-5-14 1 Screw

16 NSA5357-5-9 1 Screw

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-06 Part 6

Structural Repair Manual (SRM) 51-24-00

51-44-11

51-76-12

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 86

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SERVICE BULLETIN

References

Fig. A-FCAAD

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Clean the hole with:

Solvent General

Purpose

11-026 As required

(b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11.

1 If the diameter do not respect the tolerance of the table 8:

a Ream holes to first oversize, refer to the table 9 of the SRM 51-44-11.

b Install for the hole A:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw NSA5357-5-14 Item 15

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

c Install for the hole B:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw NSA5357-5-9 Item 16

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

2 If the diameter respect the tolerance of the table 8:

a Install for the hole A:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 87

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SERVICE BULLETIN

1 screw EN6115V5-14 Item 13

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

b Install for the hole B:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw EN6115V5-9 Item 14

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

(c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12:

Corrosion Inhibiting

fillet Consistency

09-016 As required

(d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2),

refer to NTM 51-10-06 Part 6.

(6) Subtask 574089-410-002-004 - Install the Fasteners on the RH Side

Work Zones and Access Panels

Zone Access/Work location

142 Access Panel 148AZ

Work location Frame 40

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 88

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SERVICE BULLETIN

Material necessary to do the job

Kit 574089A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 NSA5368PD516B 2 Washer

9 NAS1726-5E 2 Nut

13 EN6115V5-14 1 Screw

14 EN6115V5-9 1 Screw

15 NSA5357-5-14 1 Screw

16 NSA5357-5-9 1 Screw

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-001 As required

Corrosion Inhibiting fillet

Consistency

09-016 As required

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-06 Part 6

Structural Repair Manual (SRM) 51-24-00

51-44-11

51-76-12

Fig. A-FCAAD

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Clean the hole with:

Solvent General

Purpose

11-026 As required

(b) Do a check of the diameter of the hole, refer to the table 8 of the SRM 51-44-11.

1 If the diameter do not respect the tolerance of the table 8:

a Ream holes to first oversize, refer to the table 9 of the SRM 51-44-11.

b Install for the hole A:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw NSA5357-5-14 Item 15

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 89

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SERVICE BULLETIN

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

c Install for the hole B:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw NSA5357-5-9 Item 16

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

2 If the diameter respect the tolerance of the table 8:

a Install for the hole A:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw EN6115V5-14 Item 13

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

b Install for the hole B:

Refer to Fig. A-FCAAD Sheet 01, Fig. A-FCAAD Sheet 02

1 screw EN6115V5-9 Item 14

or

1 nut NAS1726-5E Item 9

and if necessary, use

1 washer NSA5368PD516B Item 8

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 90

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SERVICE BULLETIN

And install with:

Fuel Tank Sealant

Polysulfide

09-001 As required

(c) Apply the sealant over the nut as per SRM 51-24-00 and SRM 51-76-12:

Corrosion Inhibiting

fillet Consistency

09-016 As required

(d) Do a repetitive inspection at interval given in Planning Information Paragrah E.(2),

refer to NTM 51-10-06 Part 6.

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 574089-710-001-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501

28-25-00, Page Block 301

57-17-11, Page Block 401

(a) Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block

401).

(b) Refuel the center tank (Refer to AMM 28-25-00 Page Block 301).

(c) Do a leak test of the center tank (Refer to AMM 28-11-00 Page Block 501).

(d) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11

Page Block 401).

**CONF 002

(1) Subtask 574089-710-001-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501

28-25-00, Page Block 301

57-17-11, Page Block 401

(a) Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block

401).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

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SERVICE BULLETIN

(b) Refuel the center tank (Refer to AMM 28-25-00 Page Block 301).

(c) Do a leak test of the center tank (Refer to AMM 28-11-00 Page Block 501).

(d) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11

Page Block 401).

**CONF 003

(1) Subtask 574089-710-001-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501

28-25-00, Page Block 301

57-17-11, Page Block 401

(a) Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block

401).

(b) Refuel the center tank (Refer to AMM 28-25-00 Page Block 301).

(c) Do a leak test of the center tank (Refer to AMM 28-11-00 Page Block 501).

(d) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11

Page Block 401).

**CONF 005

(1) Subtask 574089-710-001-002 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501

28-25-00, Page Block 301

57-17-11, Page Block 401

(a) Install the access cover 148AZ (Refer to AMM 57-17-11 Page Block 401).

(b) Refuel the center tank (Refer to AMM 28-25-00 Page Block 301).

(c) Do a leak test of the center tank (Refer to AMM 28-11-00 Page Block 501).

(d) Do the test after removal/installation of the access cover (Refer to AMM 57-17-11

Page Block 401).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 92

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SERVICE BULLETIN

**CONF 007

(1) Subtask 574089-710-001-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501

28-25-00, Page Block 301

57-17-11, Page Block 401

(a) Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block

401).

(b) Refuel the center tank (Refer to AMM 28-25-00 Page Block 301).

(c) Do a leak test of the center tank (Refer to AMM 28-11-00 Page Block 501).

(d) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11

Page Block 401).

**CONF 008

(1) Subtask 574089-710-001-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 501

28-25-00, Page Block 301

57-17-11, Page Block 401

(a) Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11 Page Block

401).

(b) Refuel the center tank (Refer to AMM 28-25-00 Page Block 301).

(c) Do a leak test of the center tank (Refer to AMM 28-11-00 Page Block 501).

(d) Do the test after removal/installation of the access covers (Refer to AMM 57-17-11

Page Block 401).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 93

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SERVICE BULLETIN

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 574089-832-034-001

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201

53-35-13, Page Block 401

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH

side (Refer to AMM 53-35-13 Page Block 401).

(c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201).

(d) Restore the systems and the aircraft to normal operating condition.

(e) Remove the access platform(s).

**CONF 002

(1) Subtask 574089-832-034-001

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201

53-35-13, Page Block 401

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH

side (Refer to AMM 53-35-13 Page Block 401).

(c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201).

(d) Restore the systems and the aircraft to normal operating condition.

(e) Remove the access platform(s).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 94

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SERVICE BULLETIN

**CONF 003

(1) Subtask 574089-832-034-001

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201

53-35-13, Page Block 401

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH

side (Refer to AMM 53-35-13 Page Block 401).

(c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201).

(d) Restore the systems and the aircraft to normal operating condition.

(e) Remove the access platform(s).

**CONF 005

(1) Subtask 574089-832-034-002 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201

53-35-13, Page Block 401

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the access panels 192GB and 192JB (Refer to AMM 53-35-13 Page Block

401).

(c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201).

(d) Restore the systems and the aircraft to normal operating condition.

(e) Remove the access platform(s).

**CONF 007

(1) Subtask 574089-832-034-001

Manpower Resources

Skills NON SPECIFIC

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 95

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201

53-35-13, Page Block 401

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH

side (Refer to AMM 53-35-13 Page Block 401).

(c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201).

(d) Restore the systems and the aircraft to normal operating condition.

(e) Remove the access platform(s).

**CONF 008

(1) Subtask 574089-832-034-001

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 32-12-00, Page Block 201

53-35-13, Page Block 401

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the access panels 191FB for the LH side and 192GB and 192JB for the RH

side (Refer to AMM 53-35-13 Page Block 401).

(c) Close the MLG doors (Refer to AMM 32-12-00 Page Block 201).

(d) Restore the systems and the aircraft to normal operating condition.

(e) Remove the access platform(s).

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 96

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SERVICE BULLETIN

**CONF 001

AREA TO INSPECT

LH SIDE SHOWN

RH SIDE SYMMETRICAL

Y1959

STGR1

FR40DATUM

FR40

FR47

A Z141 Z142 − 

B

B

A

B

VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40

F_SB_574089_5_BAAA_01_02

Figure A-FBAAA - Sheet 01

Area to Inspect

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 97

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SERVICE BULLETIN

**CONF 002

AREA TO INSPECT

LH SIDE SHOWN

RH SIDE SYMMETRICAL

Y1959

STGR1

FR40DATUM

FR40

FR47

B

B

A

B

VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40

A Z141 Z142 − 

F_SB_574089_5_BAAB_01_01

Figure A-FBAAB - Sheet 01

Area to Inspect

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 98

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SERVICE BULLETIN

**CONF 005

RH SIDE SHOWN

FR40

FR47

A Z141 Z142 − 

B

A

AREA TO INSPECT

Y1959

STGR1

FR40 DATUM

B

VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40 F_SB_574089_5_BAAC_01_01

Figure A-FBAAC - Sheet 01

Area to Inspect

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 99

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SERVICE BULLETIN

**CONF 003, 007 thru 008

FR40

FR47

B

B

A

A Z141 Z142 − 

LH SIDE SHOWN

RH SIDE SYMMETRICAL

DATUM

Y2390 Y1959

AREA TO INSPECT

STGR1

FR40

F

W

D

VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40

LH SIDE SHOWN

RH SIDE SYMMETRICAL

Y1959

FR40DATUM

B

STGR1

C

C

F_SB_574089_5_BAAD_01_01

Figure A-FBAAD - Sheet 01

Area to Inspect

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 100

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SERVICE BULLETIN

**CONF 001

CRACK

REMOVE THE FASTENERS ON THE LH SIDE

DO A SPECIAL DETAILED INSPECTION OF THE

HOLE ON KEEL BEAM AT FRAME 40.

REFER TO FIGURE A−FBAAA.

FOR THE THRESHOLD, REFER TO PLANNING

INFORMATION PARAGRAPH E.(2).

DO A ROTATING PROBE INSPECTION.

NO

QUESTION

ACTION

FINDING

YES

REFER TO

FIGURE A−FFAAA SHEET 2 CONTACT AIRBUS

CORRECTIVE ACTION FURTHER

AIRBUS ADVISE

REFER TO SUBTASK 574089−010−001−001

AND ON THE RH SIDE

REFER TO SUBTASK 574089−010−002−001

DO A SPECIAL DETAILED INSPECTION OF

REFER TO SUBTASK 574089−832−008−001

REFER TO SUBTASK 574089−832−007−001

THE HOLE AT FR40 ON THE LH SIDE AND

DO A SPECIAL DETAILED INSPECTION OF

THE HOLE AT FR40 ON THE RH SIDE

F_SB_574089_5_FAAA_01_01

Figure A-FFAAA - Sheet 01

Flow Chart

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 101

5

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@A340

SERVICE BULLETIN

**CONF 001

OR

DO A CHECK OF THE DIAMETER

OF THE HOLE

DIAMETER

IN TOLERANCE OF

TRANSITION FIT FASTENER WITH

THE TABLE 9 OF THE

SRM 51−44−11.

FROM FIGURE A−FFAAA SHEET 1

CLEAN THE HOLE

NO YES

INSTALL NEW SAME

DIAMETER FASTENER :

NSA5357−5−18 AND

NAS1726−5E.

REFER TO THE TABLE 9

OF THE SRM 51−44−11.

REAM HOLE TO

SECOND OVERSIZE.

REFER TO THE TABLE 10

OF THE SRM 51−44−11.

INSTALL SECOND

OVERSIZE FASTENER :

NSA5359−5−18,

NSA5368PD516B AND

DO A SEALING OF THE FASTENERS.

REFER TO SRM 51−76−12.

DO A REPETITIVE INSPECTION

AT INTERVAL GIVEN IN PLANNING

INFORMATION PARAGRAPH E.(2).

REFER TO NTM 51−10−01 PART 6.

IT IS RECOMMENDED NOT TO

APPLY MOD SERVICE BULLETIN

No. A340−57−4098

BEFORE THE THRESHOLDS

APPLY MOD SERVICE BULLETIN

No. A340−57−4098

NAS1726−5E.

QUESTION

ACTION

FINDING

DESCRIBED IN PLANNING

INFORMATION PARAGRAPH

TABLE 2

F_SB_574089_5_FAAA_02_01

Figure A-FFAAA - Sheet 02

Flow Chart

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 102

5

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@A340

SERVICE BULLETIN

**CONF 002

CRACK

REMOVE THE FASTENERS ON THE LH SIDE

DO A SPECIAL DETAILED INSPECTION OF THE

HOLE ON KEEL BEAM AT FRAME 40.

REFER TO FIGURE A−FBAAB.

FOR THE THRESHOLD, REFER TO PLANNING

INFORMATION PARAGRAPH E.(2).

DO A ROTATING PROBE INSPECTION.

NO

QUESTION

ACTION

FINDING

YES

REFER TO

FIGURE A−FFAAB SHEET 2 CONTACT AIRBUS

CORRECTIVE ACTION FURTHER

AIRBUS ADVISE

REFER TO SUBTASK 574089−010−001−002

AND ON THE RH SIDE

REFER TO SUBTASK 574089−010−002−002

DO A SPECIAL DETAILED INSPECTION OF

REFER TO SUBTASK 574089−832−008−002

REFER TO SUBTASK 574089−832−007−002

THE HOLE AT FR40 ON THE LH SIDE AND

DO A SPECIAL DETAILED INSPECTION OF

THE HOLE AT FR40 ON THE RH SIDE

F_SB_574089_5_FAAB_01_01

Figure A-FFAAB - Sheet 01

Flow Chart

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 103

5

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@A340

SERVICE BULLETIN

**CONF 002

OR

DO A CHECK OF THE DIAMETER

OF THE HOLE

DIAMETER

IN TOLERANCE OF

TRANSITION FIT FASTENER WITH

THE TABLE 8 OF THE

SRM 51−44−11.

FROM FIGURE A−FFAAB SHEET 1

CLEAN THE HOLE

NO YES

APPLY MOD SERVICE BULLETIN

No. A340−57−4106

QUESTION

ACTION

FINDING

REFER TO

FIGURE A−FFAAB SHEET 3

INSTALL NEW SAME DIAMETER FASTENER :

EN6115V5−18 AND NAS1726−5E.

REFER TO THE TABLE 8

OF THE SRM 51−44−11.

DO A SEALING OF THE FASTENERS.

REFER TO SRM 51−76−12.

DO REPETITIVE INSPECTION 

AT INTERVAL GIVEN IN PLANNING

INFORMATION PARAGRAPH E.(2).

REFER TO NTM 51−10−01 PART 6.

IT IS RECOMMENDED NOT TO

APPLY MOD SERVICE BULLETIN

No. A340−57−4106

BEFORE THE THRESHOLDS

DESCRIBED IN PLANNING

INFORMATION PARAGRAPH

TABLE 2

F_SB_574089_5_FAAB_02_01

Figure A-FFAAB - Sheet 02

Flow Chart

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 104

5

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@A340

SERVICE BULLETIN

**CONF 002

DIAMETER

IN TOLERANCE OF

TRANSITION FIT FASTENER WITH

THE TABLE 9 AND 10 OF THE

SRM 51−44−11.

FROM FIGURE A−FFAAB SHEET 2

NO YES

INSTALL NEW SAME

DIAMETER FASTENER :

NSA5357−5−18 AND

NAS1726−5E.

REFER TO THE TABLE 9

OF THE SRM 51−44−11.

REAM HOLE TO

SECOND OVERSIZE.

REFER TO THE TABLE 10

OF THE SRM 51−44−11.

INSTALL SECOND

OVERSIZE FASTENER :

NSA5359−5−18,

NSA5368PD516B AND

DO A SEALING OF THE FASTENERS.

REFER TO SRM 51−76−12.

DO REPETITIVE INSPECTION 

AT INTERVAL GIVEN IN PLANNING

INFORMATION PARAGRAPH E.(2).

REFER TO NTM 51−10−01 PART 6.

NAS1726−5E.

QUESTION

ACTION

FINDING

OR

FIRST OVERSIZE DIAMETER

REAM HOLE TO

FIRST OVERSIZE.

REFER TO THE TABLE 9

OF THE SRM 51−44−11.

INSTALL FIRST

OVERSIZE FASTENER :

NSA5357−5−18

AND

NAS1726−5E.

DIAMETER

NOMINAL DIAMETER

FIRST OVERSIZE SECOND OVERSIZE

F_SB_574089_5_FAAB_03_01

Figure A-FFAAB - Sheet 03

Flow Chart

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 105

5

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@A340

SERVICE BULLETIN

**CONF 005

CRACK

REMOVE THE FASTENER ON THE RH SIDE

DO A SPECIAL DETAILED INSPECTION OF THE

HOLE ON KEEL BEAM AT FRAME 40.

REFER TO FIGURE A−FBAAC.

FOR THE THRESHOLD, REFER TO PLANNING

INFORMATION PARAGRAPH E.(2).

DO A ROTATING PROBE INSPECTION.

NO

QUESTION

ACTION

FINDING

YES

REFER TO

FIGURE A−FFAAC SHEET 2 CONTACT AIRBUS

CORRECTIVE ACTION FURTHER

AIRBUS ADVISE

REFER TO SUBTASK 574089−010−002−003

DO A SPECIAL DETAILED INSPECTION OF

REFER TO SUBTASK 574089−832−008−003

THE HOLE AT FR40, ON THE RH SIDE

F_SB_574089_5_FAAC_01_01

Figure A-FFAAC - Sheet 01

Flow Chart

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 106

5

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@A340

SERVICE BULLETIN

**CONF 005

OR

DO A CHECK OF THE DIAMETER

OF THE HOLE

DIAMETER

IN TOLERANCE OF

TRANSITION FIT FASTENER WITH

THE TABLE 9 OF THE

SRM 51−44−11.

FROM FIGURE A−FFAAC SHEET 1

CLEAN THE HOLE

NO YES

INSTALL NEW SAME

DIAMETER FASTENER :

NSA5357−5−18 AND

NAS1726−5E.

REFER TO THE TABLE 9

OF THE SRM 51−44−11.

REAM HOLE TO

SECOND OVERSIZE.

REFER TO THE TABLE 10

OF THE SRM 51−44−11.

INSTALL SECOND

OVERSIZE FASTENER :

NSA5359−5−18,

NSA5368PD516B AND

DO A SEALING OF THE FASTENERS.

REFER TO SRM 51−76−12.

DO A REPETITIVE INSPECTION

AT INTERVAL GIVEN IN PLANNING

INFORMATION PARAGRAPH E.(2).

REFER TO NTM 51−10−01 PART 6.

NAS1726−5E.

QUESTION

ACTION

FINDING

IT IS RECOMMENDED NOT TO

APPLY MOD SERVICE BULLETIN

No. A340−57−4098

BEFORE THE THRESHOLDS

APPLY MOD SERVICE BULLETIN

No. A340−57−4098

DESCRIBED IN PLANNING

INFORMATION PARAGRAPH

TABLE 2

F_SB_574089_5_FAAC_02_01

Figure A-FFAAC - Sheet 02

Flow Chart

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 107

5

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@A340

SERVICE BULLETIN

**CONF 003, 007 thru 008

CRACK

REMOVE THE FASTENERS ON THE LH SIDE

DO A SPECIAL DETAILED INSPECTION OF THE

HOLES A AND B ON KEEL BEAM AT FRAME 40.

REFER TO FIGURE A−FBAAD.

FOR THE THRESHOLD, REFER TO PLANNING

INFORMATION PARAGRAPH E.(2).

DO A ROTATING PROBE INSPECTION.

NO

QUESTION

ACTION

FINDING

YES

REFER TO

FIGURE A−FFAAD SHEET 2 CONTACT AIRBUS

CORRECTIVE ACTION FURTHER

AIRBUS ADVISE

REFER TO SUBTASK 574089−010−001−004

AND ON THE RH SIDE

REFER TO SUBTASK 574089−010−002−004

DO A SPECIAL DETAILED INSPECTION OF

REFER TO SUBTASK 574089−832−008−004

REFER TO SUBTASK 574089−832−007−004

THE HOLE AT FR40 ON THE LH SIDE AND

DO A SPECIAL DETAILED INSPECTION OF

THE HOLE AT FR40 ON THE RH SIDE

F_SB_574089_5_FAAD_01_02

Figure A-FFAAD - Sheet 01

Flow Chart

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 108

5

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@A340

SERVICE BULLETIN

**CONF 003, 007 thru 008

OR

DO A CHECK OF THE DIAMETER

OF THE HOLES

DIAMETER

IN TOLERANCE OF

TRANSITION FIT FASTENER WITH

THE TABLE 8 OF THE

SRM 51−44−11.

FROM FIGURE A−FFAAD SHEET 1

CLEAN THE HOLES

NO YES

REFER TO

FIGURE A−FFAAD SHEET 3

REFER TO

FIGURE A−FFAAD SHEET 3

QUESTION

ACTION

FINDING

APPLY MOD SERVICE BULLETIN

No. A340−57−4106

IT IS RECOMMENDED NOT TO

APPLY MOD SERVICE BULLETIN

No. A340−57−4106

BEFORE THE THRESHOLDS

DESCRIBED IN PLANNING

INFORMATION PARAGRAPH

TABLE 2

F_SB_574089_5_FAAD_02_04

Figure A-FFAAD - Sheet 02

Flow Chart

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 109

5

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@A340

SERVICE BULLETIN

**CONF 003, 007 thru 008

FROM FIGURE A−FFAAD SHEET 2

INSTALL NEW SAME DIAMETER FASTENERS :

EN6115V5−14 AND NAS1726−5E

FOR HOLE A.

REAM HOLES TO

FIRST OVERSIZE.

REFER TO THE TABLE 9

OF THE SRM 51−44−11.

INSTALL FIRST OVERSIZE FASTENERS :

NSA5357−5−14 AND NAS1726−5E

FOR HOLE A.

DO A SEALING OF THE FASTENERS.

REFER TO SRM 51−76−12.

DO A REPETITIVE INSPECTION

AT INTERVAL GIVEN IN PLANNING

INFORMATION PARAGRAPH E.(2).

REFER TO NTM 51−10−01 PART 6.

INSTALL NSA5357−5−9 AND

QUESTION

ACTION

FINDING

NAS1726−5E FOR HOLE B.

INSTALL EN6115V5−9 OR EN6115V5−10

AND NAS1726−5E FOR HOLE B.

REFER TO THE TABLE 8

OF THE SRM 51−44−11.

FROM FIGURE A−FFAAD SHEET 2

F_SB_574089_5_FAAD_03_02

Figure A-FFAAD - Sheet 03

Flow Chart

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 110

5

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@A340

SERVICE BULLETIN

**CONF 001

LH SIDE SHOWN

RH SIDE SYMMETRICAL

Y1959

STGR1

FR40DATUM

FR40

FR47

B

B

A

B

VIEW FROM INSIDE CENTER TANK AT FR40

C

A Z141 Z142 − 

F_SB_574089_5_CAAA_01_01

Figure A-FCAAA - Sheet 01

Removal/Installation of the Fasteners

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 111

5

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@A340

SERVICE BULLETIN

**CONF 001

Y1959

DATUM

HEAD ON HIDDEN SIDE

FASTENERS NOT AFFECTED

OR

DEPENDS ON AIRCRAFT

CONFIGURATION

F

APPLY MAT No. 09−001

F

VIEW INSIDE CENTER TANK AT FR40

ITEM AND ONLY IF NECESSARY

FR40

NOTE:

01

(7)

(8)

(9)

7

8

9

(10)

(8)

(9)

10

8

9

(8) 8

01

STGR1

C

F

W

D

F_SB_574089_5_CAAA_02_01

Figure A-FCAAA - Sheet 02

Removal/Installation of the Fasteners

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 112

5

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@A340

SERVICE BULLETIN

**CONF 002

LH SIDE SHOWN

RH SIDE SYMMETRICAL

Y1959

STGR1

FR40DATUM

FR40

FR47

B

B

A

B

VIEW FROM INSIDE CENTER TANK AT FR40

C

A Z141 Z142 − 

F_SB_574089_5_CAAB_01_01

Figure A-FCAAB - Sheet 01

Removal/Installation of the Fasteners

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 113

5

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@A340

SERVICE BULLETIN

**CONF 002

HEAD ON HIDDEN SIDE

FASTENERS NOT AFFECTED

APPLY MAT No. 09−001

F

VIEW INSIDE CENTER TANK AT FR40

ITEM AND ONLY IF NECESSARY

NOTE:

01

(8) 8

C

OR

DEPENDS ON AIRCRAFT

CONFIGURATION

(7)

(8)

(9)

7

8

9

(10)

(8)

(9)

10

8

9

01

STGR1

OR

(11)

(8)

(9)

11

8

9

Y1959

DATUM

F

FR40

F

W

D

F_SB_574089_5_CAAB_02_01

Figure A-FCAAB - Sheet 02

Removal/Installation of the Fasteners

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 114

5

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@A340

SERVICE BULLETIN

**CONF 005

RH SIDE SHOWN

FR40

FR47

B

A

VIEW FROM INSIDE CENTER TANK AT FR40

A Z141 Z142 − 

Y1959

STGR1

FR40 DATUM

C

B

F_SB_574089_5_CAAC_01_01

Figure A-FCAAC - Sheet 01

Removal/Installation of the Fasteners

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 115

5

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@A340

SERVICE BULLETIN

**CONF 005

HEAD ON HIDDEN SIDE

FASTENERS NOT AFFECTED

OR

DEPENDS ON AIRCRAFT

CONFIGURATION

APPLY MAT No. 09−001

F

VIEW INSIDE CENTER TANK AT FR40

ITEM AND ONLY IF NECESSARY

NOTE:

01

(7)

(8)

(9)

7

8

9

(10)

(8)

(9)

10

8

9

(8) 8

01

C

Y1959

FR40 DATUM

STGR1

F

F

W

D

F_SB_574089_5_CAAC_02_01

Figure A-FCAAC - Sheet 02

Removal/Installation of the Fasteners

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 116

5

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@A340

SERVICE BULLETIN

**CONF 003, 007 thru 008

FR40

FR47

B

B

A

A Z141 Z142 − 

LH SIDE SHOWN

RH SIDE SYMMETRICAL

DATUM

Y2390 Y1959

STGR1

FR40

F

W

D

VIEW FROM INSIDE CENTER TANK ON AFT SIDE OF FR40

LH SIDE SHOWN

RH SIDE SYMMETRICAL

Y1959

FR40DATUM

B

STGR1

C

C

D

F_SB_574089_5_CAAD_01_01

Figure A-FCAAD - Sheet 01

Removal/Installation of the Fasteners

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 117

5

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@A340

SERVICE BULLETIN

**CONF 003, 007 thru 008

F

F

HOLE B

HOLE A

VIEW INSIDE CENTER TANK AT FR40

HEAD ON HIDDEN SIDE

FASTENERS NOT AFFECTED

APPLY MAT No. 09−001

F

NOTE:

01

01

OR

DEPENDS ON AIRCRAFT

CONFIGURATION

(9)

(16)

9

16

(9)

(14)

9

14

OR

DEPENDS ON AIRCRAFT

CONFIGURATION

(9)

(15)

9

15

(9)

(13)

9

13

F

W

D

(8) 8 (8) 8

(8) 8 (8) 8

D

ITEM AND ONLY IF NECESSARY (8) 8

F_SB_574089_5_CAAD_02_03

Figure A-FCAAD - Sheet 02

Removal/Installation of the Fasteners

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 118

5

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@A340

SERVICE BULLETIN

Appendix 01 - Inspection Report

**CONF ALL

(1) The results of the inspection, including no findings, replacement or action to be done, must be

forwarded to Airbus department SEES1, on the attached inspection report sheet.

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 1

5

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@A340

SERVICE BULLETIN

Appendix 01 - Inspection Report

**CONF 001 thru 002

SIDE

LH

RH

NO CRACK CRACK DIAMETER

LH

RH

LH

RH

HOLE REAMED TO NEXT OVERSIZE

NOMINAL DIAMETER FIRST OVERSIZE SECOND OVERSIZE

INSTALLATION OF THE FASTENER AT:

PLEASE PRECISE OTHER FINDINGS :

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A340−57−4089

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE −

INSPECTION METHOD : SPECIAL DETAILED

INSPECTION

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

SIDE

SIDE

F_SB_574089_5_RAAA_01_00

Figure A-FRAAA - Sheet 01

Inspection Report

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 2

5

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@A340

SERVICE BULLETIN

Appendix 01 - Inspection Report

**CONF 005

SIDE

RH

NO CRACK CRACK DIAMETER

RH

RH

HOLE REAMED TO NEXT OVERSIZE

NOMINAL DIAMETER FIRST OVERSIZE SECOND OVERSIZE

INSTALLATION OF THE FASTENER AT:

PLEASE PRECISE OTHER FINDINGS :

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A340−57−4089

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE −

INSPECTION METHOD : SPECIAL DETAILED

INSPECTION

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

SIDE

SIDE

F_SB_574089_5_RAAB_01_00

Figure A-FRAAB - Sheet 01

Inspection Report

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 3

5

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@A340

SERVICE BULLETIN

Appendix 01 - Inspection Report

**CONF 003, 007 thru 008

SIDE NO CRACK CRACK DIAMETER

LH

RH

LH

RH

HOLE REAMED TO NEXT OVERSIZE

NOMINAL DIAMETER FIRST OVERSIZE

INSTALLATION OF THE FASTENER AT:

HOLE A

HOLE A RH

RH

LH

LH

HOLE B

HOLE B

HOLE A HOLE B

HOLE A HOLE A HOLE B HOLE B

PLEASE PRECISE OTHER FINDINGS :

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A340−57−4089

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE −

INSPECTION METHOD : SPECIAL DETAILED

INSPECTION

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

F_SB_574089_5_RAAC_01_00

Figure A-FRAAC - Sheet 01

Inspection Report

DATE: Oct 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 4

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@A340

SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM

FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT).

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 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 1

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

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 30/03 SERVICE BULLETIN No.: A340-57-4089

REVISION No.: 05 - Nov 13/12 Page: 1

5

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