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 MANDATORY

ATA SYSTEM : 28

TITLE : FUEL - GENERAL - REVISE THE ELECTRICAL BONDING OF THE EQUIPMENT IN THE

FUEL TANKS

MODIFICATION No. : 49135H14088, 50104S16539, 51825S16856

This page transmits Revision No. 05 of Service Bulletin No. A340-28-4097

ADDITIONAL WORK

Configuration 01, 05 and 06: No additional work is required by this revision for aircraft modified by any

previous issue and on which Config. 01, 05 or 06 was previously valid.

Configuration 02 and 03: For operators who have already embodied the Revision 03 or any previous

revision of this Service Bulletin on aircraft which were previously in Config. 02 or 03: It will be necessary

to check their embodiment history records and report to Airbus if the Electrical Bonding of the Water

Drain System (Trim Tank) and the Electrical Bonding of the Ventilation Intake System were completed

as it is shown in Figure 46 and Figure 48.

- If operator records confirm that the Electrical Bonding of the Water Drain System (Trim Tank) and

the Electrical Bonding of the Ventilation Intake System were completed - NO ADDITIONAL WORK

IS REQUIRED BY THIS REVISION

- If operator records confirm that the Electrical Bonding of the Water Drain System (Trim Tank) and

the Electrical Bonding of the Ventilation Intake System were not completed - ADDITIONAL WORK

IS REQUIRED BY THIS REVISION

Config. 07: ADDITIONAL WORK is required by this revision for aircraft modified by Revision 00, 01, 02,

03 or 04 and on which Config. 04 was previously valid.

REASON

This Revision is issued to :

- change the Mat. No. 09-530 to Mat. No. 09-001

- add ADDITIONAL WORK for aircraft modified by Revision 00, 01, 02, 03 or 04 (For Config. 07,

installation of the bonding point in the center tank added).

- introduce minor changes.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 1 of 7

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A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

CHANGES

SUMMARY :

- EFFECTIVITY

. Effectivity has been updated.

- MANPOWER

. The text introduced at revision 03 has been added to the additional work title. Config. 07 and

Config. 02, 03 and 07 ADDITIONAL WORK have been added. Note has been added.

- MATERIAL INFORMATION

. Kit A01 has been raised in issue. Kit B04 has been added to Config. 01 and Config. 02. The

text introduced at revision 03 has been added to the additional work title. Config. 07 has been

added. Additional Work for Config. 07 has been added. Supplementary kit has been added

to Config. 02, 03 and 07.

PLANNING INFORMATION :

- EFFECTIVITY

. 1.A. Effectivity has been updated. The text introduced at revision 03 has been added to the

additional work title. Kit by Config, Configs. 01, 02 and 04 have been updated. Config. 07 have

been added. Kit No. 284097A01 has been raised in issue. Kits A03 have been added.

- DESCRIPTION

. 1.D.(7) Config. 07 has been added.

. 1.D.(8) The text introduced at revision 03 has been added to the additional work title

. 1.D.(9) The text introduced at revision 03 has been added to the additional work title

. 1.D.(10) Config. 07 additional work has been added.

. 1.D.(11) Additional Work has been added for Config. 02 and 03.

- MANPOWER

. 1.G. Kit A01 has been raised in issue. Config. 04 test manhours have increased to 2. The text

introduced at revision 03 has been added to the additional work title. Config. 07 and Config. 02,

03 and 07 additional work have been added.

- WEIGHT AND BALANCE

. 1.H. Kit A01 has been raised in issue.

MATERIAL INFORMATION :

- MATERIAL - PRICE AND AVAILABILITY

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 2

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A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- Material

. 2.A.(1) AIRBUS address has been amended.

- Price and Availability

. 2.A.(2) Kit A01 has been raised in issue. Kits C02S01, A03 and A04 have been added. Kit

prices and calandar days have been amended.

- LIST OF COMPONENTS

. 2.C. Kit A01 has been raised in issue.

. 2.C. Kit A03 has been added.

. 2.C. Kit A04 has been added.

. 2.C. Kit 284097C01 raised to Rev 04. Items 10 and 11 deleted. Qty of Item 6 and Item 8 raised to 5.

. 2.C. Kit 284097C02 raised to Rev 04. Item 10 and 11 deleted. Qty of Item 6 and Item 8 raised to 8.

. 2.C. Kit C02S01 added.

- LIST OF MATERIALS - OPERATOR SUPPLIED

- Consumable Materials

-

. 2.D.(1) Sealant 09-530 changed to 09-001B

ACCOMPLISHMENT INSTRUCTIONS :

- Preparation

. 3.A.(1)(a)4 Workstep has been added.

. 3.A.(1)(b)4 Workstep has been added.

. 3.A.(1)(b)5 Workstep has been added.

. 3.A.(1)(b)6 Workstep has been added.

. 3.A.(1)(b)7 Workstep has been added.

. 3.A.(1)(b)12 Workstep has been added.

. 3.A.(1)(c) The text introduced at revision 03 has been added to the additional work title

. 3.A.(1)(d) The text introduced at revision 03 has been added to the additional work title

. 3.A.(1)(e) Config. 07 has been added.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 3

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A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- MODIFICATION

. 3.B.(3)(a) Note has been amended.

. 3.B.(4)(a) Note has been amended.

. 3.B.(4)(a)3 Workstep has been added.

. 3.B.(5) Kit A01 has been raised in issue.

. 3.B.(6) Config. 07 has been added.

. 3.B.(7)(b)5 CML reference 09-530 has been amended to 09-001B.

. 3.B.(7)(c)3 CML reference 09-530 has been amended to 09-001B.

. 3.B.(7)(d)5 CML reference 09-530 has been amended to 09-001B.

. 3.B.(8)(b)5 CML reference 09-530 has been amended to 09-001B.

. 3.B.(8)(c)3 CML reference 09-530 has been changed to 09-001B.

. 3.B.(8)(d)5 CML reference 09-530 has been amended to 09-001B.

. 3.B.(9) The text introduced at revision 03 has been added to the additional work title

. 3.B.(10) The text introduced at revision 03 has been added to the additional work title

. 3.B.(11) Config. 07 has been added.

. 3.B.(12) Additional work has been added.

- TESTS

. 3.C.(1)(a)2 Workstep has been updated.

. 3.C.(2)(a)1 Workstep has been updated.

. 3.C.(2)(a)2 Workstep has been updated.

. 3.C.(2)(a)3 Workstep has been added.

. 3.C.(2)(a)4 Workstep has been added.

. 3.C.(2)(a)5 Workstep has been added.

. 3.C.(2)(a)6 Workstep has been added.

. 3.C.(2)(a)7 Workstep has been added.

. 3.C.(2)(b)1b Workstep has been added.

. 3.C.(2)(b)1d Workstep has been amended.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 4

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A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

. 3.C.(2)(b)1e Workstep has been added.

. 3.C.(3) Config. 07 has been added.

. 3.C.(4) The text introduced at revision 03 has been added to the additional work title

. 3.C.(5) The text introduced at revision 03 has been added to the additional work title

. 3.D.(3) Config. 07 has been added.

. 3.D.(4) The text introduced at revision 03 has been added to the additional work title

. 3.D.(5) Config. 07 ADDITIONAL WORK has been added.

- Figure 3

. Figure 3, Sheet 1: mhm becomes milliohms.

- Figure 4

. Figure 4 : Detail D updated.

- Figure 5

. Figure 5, Sheet 3 : updated.

- Figure 6

. Figure 6, Sheet 1 : mhm becomes milliohms.

- Figure 7

. Sheet 1 has been updated

- Figure 8

. Figure 8, Sheet 1 : mhm becomes milliohms.

- Figure 9

. Sheets 1, 4 and 8 have been updated. Sheet 9 added.

- Figure 10

. Figure 10 : Items 124 thru 127 deleted.

- Figure 11

. Figure 11, Sheet 1 updated.

- Figure 12

. Figure 12, Sheets 1 thru 3 : mhm becomes milliohms.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 5

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A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- Figure 14

. Figure 14, Sheets 1 thru 2 : mhm becomes milliohms.

- Figure 16

. Figure 16, Sheet 1 : mhm becomes milliohms.

- Figure 17

. Sheet 5 has been updated.

- Figure 18

. Figure 18, Sheet 1 : mhm becomes milliohms.

- Figure 20

. Figure 20, Sheet 1 : mhm becomes milliohms.

- Figure 22

. Sheet 1 has been updated.

- Figure 28

. New Figures 28 thru Figure 38 inserted and subsequent figures renumbered.

APPENDIX 1 :

- Figure

- 1. Config. 03 and Figure 2 added, Figure 1 updated.

FILING 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 of this Service Bulletin was revised to incorporate the comments from the validation

on MSN 0075.

Revision No. 02 was issued to change the compliance from recommended to mandatory. The

opportunity was taken to update the effectivity, to correct Figure references in Table 1 and to include

configurations throughout. The Kit applicability is also amended and the Manhours revised. The

concurrent requirement of SB A340-28-4118 is also added.

Revision No. 03 was issued to include the instructions for electrical bonding of:

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 6

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A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- the fuel pump canisters for Config 01 and 02 aircraft (previously included only for Config 03 aircraft)

- the water drain valve between rib 1 and rib 2 that was omitted from previous revisions.

Because of these anomalies, Config. 05 (Kit 284097B08R00) and Config. 06 (Kit 284097B09R00) were

added to address the additional work necessary.

Changes were also included following a validation of the Service Bulletin on MSN 0091.

Revision 04 was issued to clarify the applicability of the Kits 284097B02, 284097B03, 284097C01 and

284097C02 to the configurations 01, 02 and 03.

Washers, Item 10 and 11 have been deleted from Kits 284097C01R04 and 284097C02R04 and have

been superseded by washers, Items 8 and 6.

The opportunity has been taken to update the effectivity and make minor text corrections.

REVISION SEQUENCE

ORIGINAL : Jun 14/04

REVISION No. : 01 - Mar 03/05

REVISION No. : 02 - Aug 16/06

REVISION No. : 03 - Jul 03/07

REVISION No. : 04 - Sep 15/08

REVISION No. : 05 - Jun 03/10

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 7

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A340

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 8

Printed in France © AIRBUS 2008 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 MANDATORY

ATA SYSTEM : 28

TITLE : FUEL - GENERAL - REVISE THE ELECTRICAL BONDING OF THE EQUIPMENT IN THE

FUEL TANKS

MODIFICATION No. : 49135H14088, 50104S16539, 51825S16856

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

As part of the Fuel System Safety Program, AIRBUS has carried out an investigation of the electrical bonding

in the aircraft fuel tanks.

The result of these investigations is the issue of this Service Bulletin, which introduces additional bonding

leads and electrical bonding points.

The accomplishment of this Service Bulletin provides improved electrical bonding to make sure that

continuous electrical bonding protection of all the equipment in the wing fuel tanks for the design life goal

of the aircraft. In addition, this Service Bulletin is required to comply with FAA Special Federal Aviation

Regulation (SFAR) 88 and EASA/JAA Interim Policy 25/12 requirements.

A booklet including photographs taken during the validation of this Service Bulletin is available on AIRBUS

World, Maintenance and Engineering, Service Bulletin Information.

This Service Bulletin has been validated on A340 aircraft MSN 0075 and MSN 0091.

EVALUATION TABLE

COMPLIANCE Mandatory CANCELS INSPECTION SB No

POTENTIAL AD Yes A/C OPERATION AFFECTED No

RELIABILITY AFFECTED No PAX COMFORT AFFECTED No

COST SAVING No ETOPS AFFECTED No

STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED No

DEFUEL/VENTILATION Yes

KIT PRICE (USD) See SB

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 1 of 5

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A340

SERVICE BULLETIN

SUMMARY

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 49135H14088, 50104S16539, 51825S16856

As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural

strength, reliability, operational characteristics, affecting the airworthiness of the product. All other changes

are major changes.

EFFECTIVITY

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

13W AAW ACA AFR ALK ARG B3R CAL CCA CES CPA DGA DLH ETD FIN GFA IBE KAC LAN M3R MAU

MPD MSR NMB OAL PAL QAF R3L RJA S3R SAA SAS SWR TAP THT THY UAE VCV VIR XAX

CONCURRENT REQUIREMENTS

Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the following

Service Bulletin or the equivalent production modification:

Service Bulletin No. A340-28-4118 Mod. No. 55118H15875

REFERENCES/REPERCUSSIONS

TFU : None

OEB : None

AOT : None

SIL : None

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

OTHERS : None

NATURE OF THE WORK

AIRCRAFT : Yes

EQUIPMENT : No

HARD : No

SOFT : No

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 2

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A340

SERVICE BULLETIN

SUMMARY

OBRM : No

MANPOWER

Config. 01

TOTAL MANHOURS 451.0

ELAPSED TIME (HOURS) 260.35

Config. 02

TOTAL MANHOURS 453.0

ELAPSED TIME (HOURS) 260.35

Config. 03

TOTAL MANHOURS 453.0

ELAPSED TIME (HOURS) 260.35

Config. 04

TOTAL MANHOURS 58.50

ELAPSED TIME (HOURS) 58.50

Config. 07

TOTAL MANHOURS 130.0

ELAPSED TIME (HOURS) 65.0

Config. 02. ADDITIONAL WORK

TOTAL MANHOURS 42.0

ELAPSED TIME (HOURS) 26.00

Config. 03. ADDITIONAL WORK

TOTAL MANHOURS 42.0

ELAPSED TIME (HOURS) 26.00

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 3

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A340

SERVICE BULLETIN

SUMMARY

Config. 05 ADDITIONAL WORK (Introduced at revision 03)

TOTAL MANHOURS 29.0

ELAPSED TIME (HOURS) 8.0

Config. 06 ADDITIONAL WORK (Introduced at revision 03)

TOTAL MANHOURS 11.5

ELAPSED TIME (HOURS) 6.0

Config. 07 ADDITIONAL WORK

TOTAL MANHOURS 176.50

ELAPSED TIME (HOURS) 88.0

MATERIAL INFORMATION

AIRCRAFT DATA

Config. 01 :

The modification of one aircraft requires Kit 284097A01R06 Kit 284097A02R00 Kit 284097B01R01 Kit

284097B02R02 Kit 284097B04R01 Kit 284097B05R03 Kit 284097B06R03 Kit 284097B07R03 and Kit

284097C01R04 consisting of bonding leads, clamps, bolts, washers and nuts.

Config. 02 :

The modification of one aircraft requires Kit 284097A01R06 Kit 284097A02R00 Kit 284097B01R01

Kit 284097B02R02 Kit 284097B04R01 Kit 284097B05R03 Kit 284097B06R03 Kit 284097B07R03 Kit

284097C02R04 and Kit 284097C02S01 consisting of bonding leads, clamps, bolts, washers and nuts.

Config. 03 :

The modification of one aircraft requires Kit 284097A01R06 Kit 284097A02R00 Kit 284097B01R01

Kit 284097B03R02 Kit 284097B04R01 Kit 284097B05R03 Kit 284097B06R03 Kit 284097B07R03 Kit

284097C02R04 and Kit 284097C02S01 consisting of bonding leads, clamps, bolts, washers and nuts.

Config. 04 :

There are no materials necessary for the check of the bonding points on this configuration.

Config. 05 ADDITIONAL WORK (Introduced at revision 03):

The modification of one aircraft requires Kit 284097B08R00 consisting of bonding leads, clamps,

bolts, washers and nuts.

Config. 06 ADDITIONAL WORK (Introduced at revision 03):

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 4

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A340

SERVICE BULLETIN

SUMMARY

The modification of one aircraft requires Kit 284097B09R00 consisting of bonding leads, clamps,

bolts, washers and nuts.

Config. 07 (Introduced by this revision) The modification of one aircraft requires Kit 284097A03R00

consisting of bonding leads, clamps, bolts, washers and nuts.

NOTE : Config. 07 is valid for aircraft MSNs 0474 and 0483. These aircraft are post MOD 4160 and

49135 therefore no need to perform this modification in the trim tank.

Config. 07 ADDITIONAL WORK (Introduced by this revision) The modification of one aircraft requires

Kit 284097A04R00 consisting of bonding leads, clamps, bolts, washers and nuts.

APPENDICES

Refer to APPENDIX 01 Configurations of related points to be checked.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 5

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SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 6

Printed in France © AIRBUS 2008 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 MANDATORY

ATA SYSTEM : 28

TITLE : FUEL - GENERAL - REVISE THE ELECTRICAL BONDING OF THE EQUIPMENT IN THE

FUEL TANKS

MODIFICATION No. : 49135H14088, 50104S16539, 51825S16856

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 part to third parties and shall not be duplicated in any manner

(except for the purpose 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

A. EFFECTIVITY

(1) Models

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

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft MSN :

0002-0009 0011 0013-0015 0018-0029 0031-0035 0038-0041 0043 0044

0046-0049 0051-0053 0056-0058 0061 0063 0074-0076 0078-0081 0084 0085

0088-0091 0093 0094 0097 0101 0103 0104 0114 0115 0117 0123 0125 0126 0128

0129 0131 0133-0137 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

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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SERVICE BULLETIN

0429 0430 0433-0435 0438 0442 0446 0447 0450 0459 0467 0470 0474 0483

0528 0538 0541 0545 0546

(b) 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

13W 0009

AAW 0151

ACA 0278

AFR 0029 0049 0078 0084 0168 0174 0186 0207 0210 0237 0245 0246

0260 0307 0310 0319 0373 0377 0399

ALK 0032 0033 0034 0367 0374

ARG 0048 0063 0074 0080 0085 0093

B3R 0046

CAL 0402 0406 0411 0415 0433 0541

CCA 0192 0199 0201 0242 0243 0264

CES 0129 0131 0141 0161 0182

CPA 0123 0126 0128 0136 0137 0142 0147 0157 0160 0208 0218

0220 0227 0228 0381

DGA 0075 0081

DLH 0020 0024 0027 0028 0035 0052 0053 0056 0135 0158 0213 0233

0252 0274 0297 0304 0321 0325 0327 0335 0347 0352 0354

0355 0379 0390 0434 0447

ETD 0117

FIN 0058

GFA 0039 0040 0097 0103 0133 0212 0215 0282

IBE 0005 0088 0125 0134 0145 0146 0170 0193 0197 0217 0221 0302

0318 0329 0332 0378 0387 0414 0459 0474 0483

KAC 0089 0090 0101 0104

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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A340

SERVICE BULLETIN

OPERATOR MSN

LAN 0167 0359 0363 0429 0442

M3R 0061

MAU 0076 0094 0152 0194 0268

MPD 0007 0013 0015

MSR 0156 0159 0178

NMB 0047 0051

OAL 0235 0239 0280 0292

PAL 0173 0176 0187 0196

QAF 0026 0528

R3L 0004

RJA 0014 0022 0038 0043

S3R 0204

SAA 0006 0008 0011 0018 0019 0021

SAS 0413 0424 0430 0435 0450 0467 0470

SWR 0150 0154 0169 0175 0179 0263 0538 0545 0546

TAP 0041 0044 0079 0091

THT 0385 0395 0438 0446

THY 0023 0025 0057 0115 0180 0216 0257 0270 0331

UAE 0139 0149 0163 0166 0185 0190 0202 0236

VCV 0031

VIR 0002 0003 0114 0164 0214 0225

XAX 0273

(c) Effectivity by MSN and Kit/Configuration

The Kits and configurations applicable to these MSNs are given at the end of this list

0002-0009 0011 0013-0015 0018-0029 0031-0035 0038-0041 0043-0044

0046-0049 0051-0053 0056-0058 0061 0063

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 3

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A340

SERVICE BULLETIN

KIT No. QTY PER A/C CONFIGURATION

284097A01R06 1 01

284097A02R00 1 01

284097B01R01 1 01

284097B02R02 1 01

284097B04R01 1 01

284097B05R03 1 01

284097B06R03 1 01

284097B07R03 1 01

284097C01R04 1 01

284097B08R00 1 05

NOTE(01) Config. 01 is applicable to aircraft that are before Mod. Nos.

41600H12719, 41300H12600 and 49630S16377.

NOTE(02) Config. 05 is applicable to aircraft where Kit B08R00 is necessary for

additional work (Introduced at revision 03). This is only applicable

to operators with aircraft listed under Configs. 01 and 02 who have

accomplished this Service Bulletin before Revision No. 03.

NOTE(03) The Kit 284097A02R00 is a complement of Kit 284197A01R02 or Kit

284097A01R03.

The aircraft which have ordered Kit 284097A01R02 or Kit

284097A01R03 must also order Kit 284097A02R00 before application

of Service Bulletin on aircraft.

The Kits and configurations applicable to these MSNs are given at the end of this list

0074-0076 0078-0081 0084-0085 0088-0091 0093-0094 0097 0101 0103-0104

0114-0115 0125 0133-0134 0145-0146 0151 0156 0159 0178

KIT No. QTY PER A/C CONFIGURATION

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 4

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A340

SERVICE BULLETIN

284097A01R06 1 02

284097A02R00 1 02

284097B01R01 1 02

284097B02R02 1 02

284097B04R01 1 02

284097B05R03 1 02

284097B06R03 1 02

284097B07R03 1 02

284097C02R04 1 02

284097B08R00 1 05

NOTE(01) Config. 02 is applicable to aircraft that are after Mod. No. 41600H12719

and before Mod. Nos. 41300H12600 and 49630S16377.

Mod. No. 41600H12719 installs a forward transfer pump in the trim

horizontal stabilizer.

NOTE(02) Config. 05 is applicable to aircraft where Kit B08R00 is necessary for

additional work (Introduced at revision 03). This is only applicable

to operators with aircraft listed under Configs. 01 and 02 who have

accomplished this Service Bulletin before Revision No. 03.

NOTE(03) The Kit 284097A02R00 is a complement of Kit 284197A01R02 or Kit

284097A01R03.

The aircraft which have ordered Kit 284097A01R02 or Kit

284097A01R03 must also order Kit 284097A02R00 before application

of Service Bulletin on aircraft.

NOTE(04) To accomplish the ADDITIONAL WORK it is necessary the Kit

284097C02S01.

All parts of the Kit 284097C02S01 are included in the original Kit

284097C02R03 or Kit 284097C02R04 that you ordered for the

accomplishment of the Revision 03 or any previous Revision of this

Service Bulletin. Therefore, please, check if you have all these parts in

your stock before ordering the Kit 284097C02S01.

The Kits and configurations applicable to these MSNs are given at the end of this list

0117 0123 0126 0128-0129 0131 0135-0137 0139 0141-0142 0147 0149-0150

0152 0154 0157-0158 0160-0161 0163-0164 0166-0170 0173-0176 0179-0180

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

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 5

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A340

SERVICE BULLETIN

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

KIT No. QTY PER A/C CONFIGURATION

284097A01R06 1 03

284097A02R00 1 03

284097B01R01 1 03

284097B03R02 1 03

284097B04R01 1 03

284097B05R03 1 03

284097B06R03 1 03

284097B07R03 1 03

284097C02R04 1 03

284097B09R00 1 06

NOTE(01) Config. 03 is applicable to aircraft that are after Mod. Nos.

41600H12719 and 41300H12600 and before Mod. No. 49630S16377.

Mod. No. 41300H12600 defines the A340 growth version.

NOTE(02) Config. 06 is applicable to aircraft where Kit B09R00 is necessary for

additional work (Introduced at revision 03). This is only applicable to

operators with aircraft listed under Config. 03 who have accomplished

this Service Bulletin before Revision No. 03.

NOTE(03) The Kit 284097A02R00 is a complement of Kit 284197A01R02 or Kit

284097A01R03.

The aircraft which have ordered Kit 284097A01R02 or Kit

284097A01R03 must also order Kit 284097A02R00 before application

of Service Bulletin on aircraft.

NOTE(04) The Kit/Modification applicability is as follows :

- Kit 284097A01R06 is applicable to aircraft before Mod. No. 49630S16377

(FUEL - REVISE ELECTRICAL BONDING OF EQUIPMENT IN FUEL TANKS)

- Kit 284097B01R01 is applicable to aircraft before Mod. No. 49135H14088

- Kit 284097B02R02 is applicable to aircraft before Mod. No. 41300H12600

(WINGS - GENERAL - DEFINE A340 GROWTH VERSION) and before

Mod. No. 49135H14088

- Kit 284097B03R02 is applicable to aircraft after Mod. No. 41300H12600

and before Mod. No. 49135H14088

- Kits 284097B04R01 thru 284097B07R03 are applicable to aircraft before

Mod. No. 49135H14088

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 6

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A340

SERVICE BULLETIN

- Kit 284097C01R04 is applicable to aircraft before Mod. No. 41600H12719

(FUEL - TRIM TRANSFER SYSTEM - FIT FORWARD TRANSFER PUMP IN

THE TRIM HORIZONTAL STABILIZER) and before Mod. No. 49135H14088

- Kit 284097C02R04 is applicable to aircraft after Mod. No. 41600H12719

(FUEL - TRIM TRANSFER SYSTEM - FIT FORWARD TRANSFER PUMP IN

THE TRIM HORIZONTAL STABILIZER) and before Mod. No. 49135H14088.

NOTE(05) To accomplish the ADDITIONAL WORK it is necessary the Kit

284097C02S01.

All parts of the Kit 284097C02S01 are included in the original Kit

284097C02R03 or Kit 284097C02R04 that you ordered for the

accomplishment of the Revision 03 or any previous Revision of this

Service Bulletin. Therefore, please, check if you have all these parts in

your stock before ordering the Kit 284097C02S01.

The Kits and configurations applicable to these MSNs are given at the end of this list

0528 0538 0541 0545-0546

KIT No. QTY PER A/C CONFIGURATION

None 04

NOTE(01) Config. 04 is applicable to aircraft that are after Mod. Nos.

41300H12600, 41600H12719, 49135H14088 and 49630S16377.

Mod. No. 49630S16377 revises the electrical bonding of equipment

in fuel tanks.

The Kits and configurations applicable to these MSNs are given at the end of this list

0474 0483

KIT No. QTY PER A/C CONFIGURATION

284097A03R00 1 07

284097A04R00 1 07

NOTE(01) Config. 07 is valid for aircraft on which Mod. No. 49630S16377 (FUEL -

GENERAL - REVISE ELECTRICAL BONDING OF EQUIPMENT IN

FUEL TANKS) is not embodied and on which Mod. No. 49135H14088

(FUEL - GENERAL - REVISE ELECTRICAL BONDING OF

EQUIPMENT IN FUEL TANKS) is embodied.

NOTE(02) Kit 284097A04R00 concerns ADDITIONAL WORK is required by this

revision for aircraft modified by Revision 00 thru 04.

(3) Spares

None

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 7

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A340

SERVICE BULLETIN

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

As part of the Fuel System Safety Program, AIRBUS has carried out an investigation of the

electrical bonding in the aircraft fuel tanks.

This Service Bulletin has been validated on A340 aircraft MSNs 0075 and 0091.

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

available on AIRBUS World, Maintenance and Engineering, Service Bulletin Information.

(2) Objective/Action

The result of these investigations is the issue of this Service Bulletin, which introduces

additional bonding leads and electrical bonding points.

(3) Advantages

The accomplishment of this Service Bulletin provides improved electrical bonding to make

sure that continuous electrical bonding protection of all the equipment in the wing fuel

tanks for the design life goal of the aircraft. In addition, this Service Bulletin is required to

comply with FAA Special Federal Aviation Regulation (SFAR) 88 and EASA/JAA Intrim

Policy 25/12 requirements.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to:

(1) Config. 01 thru Config. 04

(a) Make the work area safe.

(b) Defuel and vent the fuel tanks.

(c) Put platforms in position.

(d) Remove the access panels.

(e) Get access to the applicable fuel-tanks.

(2) Config. 01 thru Config. 03

(a) In the wing tank electrically bond:

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 8

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A340

SERVICE BULLETIN

1 The wing skin panels

2 The equipment in the wing inner fuel tanks

3 The wing water drains system

4 The wing fuel diffusers

5 The wing fuel pumps

6 The wing fuel pipes

(3) Config. 01 thru Config. 03

(a) In the center tank electrically bond :

1 Check the bonding points in the center tank.

2 Modify or install the bonding points.

(4) Config. 04

(a) In the center tank electrically bond :

1 Check the applicable bonding points in the center tank.

(5) Config. 01 thru Config. 03

(a) In the trim tank electrically bond:

1 The THS Trim Tank - Water Drain System

2 The THS Trim Tank - Drainage Line

3 The Ventilation Intake System

(6) Config. 01 thru Config. 04

(a) Close-up the access.

(b) Do a fuel leak check.

(c) Remove the access platforms.

(d) Complete the documentation.

(7) Config. 07

(a) Check the bonding points in the center tank.

(b) Modify or install the bonding points.

(8) Config. 05 ADDITIONAL WORK (Introduced at revision 03)

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REVISION No. : 05 - Jun 03/10 Page : 9

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A340

SERVICE BULLETIN

NOTE : Only applicable on Config. 01 and Config. 02 aircraft where this Service

Bulletin has been accomplished previously before Revision No. 03.

(a) Make the work area safe.

(b) Defuel and vent the wing fuel tanks.

(c) Put platforms in position.

(d) Remove the access panels.

(e) Get access to the wing fuel-tanks.

(f) In the wing tanks electrically bond:

1 The wing fuel pumps.

2 The wing water drain between Rib 1 and Rib 2.

(g) Close-up the access.

(h) Do a fuel leak check.

(i) Remove the access platforms.

(j) Complete the documentation.

(9) Config. 06 ADDITIONAL WORK (Introduced at revision 03)

NOTE : Only applicable on Config. 03 aircraft where this Service Bulletin has been

accomplished previously before Revision No. 03.

(a) Make the work area safe.

(b) Defuel and vent the wing fuel tanks.

(c) Put platforms in position.

(d) Remove the access panels.

(e) Get access to the wing fuel-tanks.

(f) In the wing tanks electrically bond:

1 The wing water drain between Rib 1 and Rib 2.

(g) Close-up the access.

(h) Do a fuel leak check.

(i) Remove the access platforms.

(j) Complete the documentation.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 10

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A340

SERVICE BULLETIN

(10) Config. 07 , ADDITIONAL WORK (Introduced by this revision)

(a) Preparation

(b) Modify or install the bonding points.

(c) Test

(d) Close-up

(11) Config. 02 Config. 03 , ADDITIONAL WORK (Introduced by this revision)

NOTE : This ADDITIONAL WORK is only applicable to operators who have already

embodied the Revision 03 or any previous revision of this Service Bulletin

and their operator records confirm that the electrical bonding of the Water

Drain System and electrical bonding of the Ventilation Intake System were

not completed.

(a) Do electrical bonding on Water Drain System and Ventilation Intake System.

E. COMPLIANCE

(1) Classification

Mandatory

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is expected to be rendered mandatory by the issue

of an Airworthiness Directive (AD) published by the European Aviation Safety Agency

(EASA). The accomplishment timescale, which has not yet been defined, will be given in

the AD.

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA 21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS

origin, and which affects the content of this Service Bulletin, the operator is responsible for

obtaining approval by its airworthiness authority for any adaptation necessary before incorporation

of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to do

the work.

These estimates assume that the work will be done by experienced personnel, and may need to

be revised upwards to suit operators’ 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.

Config. 01

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 11

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A340

SERVICE BULLETIN

Get access Center Fuel Tank 52.0

Check bonding points (Kit A01R06) 45.0

Modification (Kit A01R06) 70.0

Do the Test 2.0

Close up Center Fuel Tank 52.0

Get access Wing Fuel Tank 40.0

Modification (Kit B01R01) 16.0

Modification (Kit B02R02) 12.0

Modification (Kit B04R01) 10.0

Modification (Kit B05R03) 26.0

Modification (Kit B06R03) 14.0

Modification (Kit B07R03) 20.0

Do the Test 8.0

Close up Wing Fuel Tank 40.0

Get access Trim Fuel Tank 16.0

Modification (Kit C01R04) 10.0

Do the Test 2.0

Close up Trim Fuel Tank 16.0

TOTAL MANHOURS 451.0

ELAPSED TIME (HOURS) 260.35

NOTE : The check of the presence of blue coating for one bonding point takes approximately

5 minutes.

The measure of the electrical resistance of one bonding point takes approximately

15 minutes.

Config. 02

Get access Center Fuel Tank 52.0

Check the bonding points (Kit A01R06) 45.0

Modification (Kit A01R06) 70.0

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 12

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A340

SERVICE BULLETIN

Do the Test 2.0

Close up Center Fuel Tank 52.0

Get access Wing Fuel Tank 40.0

Modification (Kit B01R01) 16.0

Modification (Kit B02R02) 12.0

Modification (Kit B04R01) 10.0

Modification (Kit B05R03) 26.0

Modification (Kit B06R03) 14.0

Modification (Kit B07R03) 20.0

Do the Test 8.0

Close up Wing Fuel Tank 40.0

Get access Trim Fuel Tank 16.0

Modification (Kit C02R04) 12.0

Do the Test 2.0

Close up Trim Fuel Tank 16.0

TOTAL MANHOURS 453.0

ELAPSED TIME (HOURS) 260.35

Config. 03

Get access Center Fuel Tank 52.0

Check bonding points (Kit A01R06) 45.0

Modification (Kit A01R06) 70.0

Do the Test 2.0

Close up Center Fuel Tank 52.0

Get access Wing Fuel Tank 40.0

Modification (Kit B01R01) 16.0

Modification (Kit B03R02) 12.0

Modification (Kit B04R01) 10.0

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 13

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A340

SERVICE BULLETIN

Modification (Kit B05R03) 26.0

Modification (Kit B06R03) 14.0

Modification (Kit B07R03) 20.0

Do the Test 8.0

Close up Wing Fuel Tank 40.0

Get access Trim Fuel Tank 16.0

Modification (Kit C02R04) 12.0

Do the Test 2.0

Close up Trim Fuel Tank 16.0

TOTAL MANHOURS 453.0

ELAPSED TIME (HOURS) 260.35

Config. 04

Get access Center Fuel Tank 26.0

Check the 46 and 47 points (blue coat) 0.5

Check the 46 and 47 points (resistance) 1.0

Test 2.0

Close-up 30.0

TOTAL MANHOURS 59.5

ELAPSED TIME (HOURS) 59.5

NOTE : The check of the presence of blue coating for one bonding point takes approximately

5 minutes.

The measure of the electrical resistance of one bonding point takes approximately

15 minutes.

Config. 07

Get access 26.0

Check of the bonding points 1.5

Modification/installation bonding points 70.0

Test 2.5

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 14

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A340

SERVICE BULLETIN

Close-up 30.0

TOTAL MANHOURS 130.0

ELAPSED TIME (HOURS) 65.0

NOTE : The check of the presence of blue coating for one bonding point takes approximately

5 minutes.

The measure of the electrical resistance of one bonding point takes approximately

15 minutes.

Config. 02 thru Config. 03 ADDITIONAL WORK

Get access 16.0

Modification 8.0

Test 2.0

Close up 16.0

TOTAL MANHOURS 42.0

ELAPSED TIME (HOURS) 26.0

Config. 05 ADDITIONAL WORK (Introduced at revision 03)

Get access Wing Fuel Tank 8.0

Modification (Kit B08R00) 12.0

Do the Test 1.0

Close up Wing Fuel Tank 8.0

TOTAL MANHOURS 29.0

ELAPSED TIME (HOURS) 8.0

Config. 06 ADDITIONAL WORK (Introduced at revision 03)

Get access Wing Fuel Tank 4.0

Modification (Kit B09R00) 3.0

Do the Test 0.5

Close up Wing Fuel Tank 4.0

TOTAL MANHOURS 11.5

ELAPSED TIME (HOURS) 6.0

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 15

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A340

SERVICE BULLETIN

Config. 07 ADDITIONAL WORK

Get access 54.0

Check of the bonding points 1.5

Modification/installation bonding points 68.0

Test 2.5

Close-up 54.0

TOTAL MANHOURS 180.00

ELAPSED TIME (HOURS) 89.0

NOTE : The check of the presence of blue coating for one bonding point takes approximately

5 minutes.

The measure of the electrical resistance of one bonding point takes approximately

15 minutes.

H. WEIGHT AND BALANCE

Config. 01 thru Config. 03 , Kit 284097A01R06

For aircraft models 340-211, 340-212 and 340-213 :

Manufacturers Empty Weight : +0.20 kg (+0.44 lb)

Effect on Balance : +6.18 kgm (+44.69 lb.ft)

For aircraft models 340-311, 340-312 and 340-313 :

Manufacturers Empty Weight : +0.20 kg (+0.44 lb)

Effect on Balance : +6.60 kgm (+47.77 lb.ft)

Config. 01 thru Config. 02 , Kit 284097B01R01 thru Kit 284097B02R02

and Kit 284097B05R03 thru Kit 284097B08R00

For aircraft models 340-211, 340-212 and 340-213 :

Manufacturers Empty Weight : +2.81 kg (+6.19 lb)

Effect on Balance : +100.37 kgm (+725.97 lb.ft)

For aircraft models 340-311, 340-312 and 340-313:

Manufacturers Empty Weight : +2.81 kg (+6.19 lb)

Effect on Balance : +106.37 kgm (+769.35 lb.ft)

Config. 03 , Kit 284097B01R01 and Kit 284097B03R02 thru Kit 284097B07R03

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 16

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A340

SERVICE BULLETIN

For aircraft models 340-213 :

Manufacturers Empty Weight : +2.81 kg (+6.19 lb)

Effect on Balance : +100.37 kgm (+725.97 lb.ft)

For aircraft models 340-313 :

Manufacturers Empty Weight : +2.81 kg (+6.19 lb)

Effect on Balance : +106.37 kgm (+769.35 lb.ft)

Config. 01 thru Config. 03 , Kit 284097C01R04 and Kit 284097C02R04

Manufacturers Empty Weight : +0.10 kg (+0.22 lb)

Effect on Balance : +6.28 kgm (+45.42 lb.ft)

I. ELECTRICAL LOAD DATA

Not changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) : 06-31-53 06-41-53 12-34-24 20-21-11

20-28-00 25-21-41 25-80-00 27-40-00

28-00-00 28-10-00 28-11-00 28-12-48

28-25-00 28-27-56 28-42-44 32-12-00

53-00-00 53-35-13 55-11-14 57-17-11

57-27-11 57-56-11

Consumable Material List (CML)

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

Standards Manual (SM)

Structural Repair Manual (SRM) : 51-21-00 51-24-00 51-42-11 51-43-12

51-44-11 51-49-00 51-75-12 51-76-12

K. PUBLICATIONS AFFECTED

Aircraft Maintenance Manual (AMM) : 28-00-00 57-00-00

Illustrated Parts Catalog (IPC) : 28-11-42 28-25-03 28-26-03 28-27-07

Structural Repair Manual (SRM) : 57-00-00

L. INTERCHANGEABILITY/MIXABILITY

Not applicable

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 17

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A340

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 18

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A340

SERVICE BULLETIN

2. MATERIAL INFORMATION

A. MATERIAL - PRICE AND AVAILABILITY

(1) Material

Customers with aircraft shown in the effectivity of this Service Bulletin should send a

purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:

AIRBUS Material Logistics and Suppliers

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet: http://spares.airbus.com

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

(2) Price and Availability

Kit 284097A01R06

Cost : 568.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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 284097A02R00

Cost : 80.00 US dollars

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 284097A03R00

Cost : 440.00 US dollars

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.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 19

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A340

SERVICE BULLETIN

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

at the issue date of the Service Bulletin.

Kit 284097A04R00

Cost : 440.00 US dollars

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 284097B01R01

Cost : 148.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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 284097B02R02

Cost : 258.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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 284097B03R02

Cost : 430.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 20

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A340

SERVICE BULLETIN

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

at the issue date of the Service Bulletin.

Kit 284097B04R01

Cost : 68.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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 284097B05R03

Cost : 210.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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 284097B05S02

Cost : 42.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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 284097B06R03

Cost : 222.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 21

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A340

SERVICE BULLETIN

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

at the issue date of the Service Bulletin.

Kit 284097B06S02

Cost : 50.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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 284097B07R03

Cost : 2855.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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 284097B07S03

Cost : 1544.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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 284097C01R04

Cost : 121.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 22

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

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

at the issue date of the Service Bulletin.

Kit 284097C02S01

Cost : 60.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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 284097C02R04

Cost : 186.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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 284097B08R00

Cost : 85.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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 284097B09R00

Cost : 45.00 US dollars

Availability : 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require 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.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 23

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A340

SERVICE BULLETIN

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

at the issue date of the Service Bulletin.

This table shows the supplemental kits (S KITS) needed to update the kits already held in

your stock to the latest status:

Kit Held by Operator Supplementary Kits

Required

Latest Status of Kit INST/DISP

284097A01R03 284097A02R00* 284097A01R06

284097A01R05 NONE 284097A01R06

284097A03R00 NONE 284097A03R00

284097A04R00 NONE 284097A04R00 NONE

284097B01R01 NONE 284097B01R01

284097B02R01 NONE 284097B02R02

284097B02R02 NONE 284097B02R02

284097B03R01 NONE 284097B03R02

284097B03R02 NONE 284097B03R02

284097B04R00 NONE 284097B04R01

284097B04R01 NONE 284097B04R01

284097B05R02 284097B05S02 284097B05R03

284097B05R03 NONE 284097B05R03

284097B06R02 284097B06S02 284097B06R03

284097B06R03 NONE 284097B06R03

284097B07R02 284097B07S03 284097B07R03

284097B07R03 NONE 284097B07R03

284097B08R00 NONE 284097B08R00

284097B09R00 NONE 284097B09R00

284097C01R03 NONE 284097C01R04

284097C02R03 284097C02S01 284097C02R04

284097C02R04 NONE 284097C02R04

NOTE : *Kit 284097A02R00 is a complemental Kit.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

C. LIST OF COMPONENTS

Kit 284097A01R06

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 24

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A340

SERVICE BULLETIN

3 NSA5050-3 17 Nut

21 NSA5519-3B 2 Clamp

22 E0088-10-125 2 Lead

23 NAS6603-2 10 Bolt

26 NSA5519-2B 4 Clamp

27 E0088-10-190 2 Lead

28 E0088-10-63 4 Lead

35 ASNA2050DCJ3215 16 Rivet

36 F5791036900100 1 Support

37 NAS1096-3-8 5 Screw

38 NAS1096-3-9 1 Screw

39 NAS1149F0332P 1 Washer

40 MS35650-302 5 Nut

41 NSA5575-8A 1 Clamp

42 NSA5575-11 3 Clamp

45 E0088-10-80 3 Lead

84 A2823301800500 4 Angle

98 F5791001800200 1 Support (98) F5791001800000 03 *

99 F5791001800300 1 Support (98) F5791001800000 03 *

116 NAS1149D0316H 2 Washer

117 E0088-10-250 2 Lead

128 AN735D40 1 Clamp

NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common

Support Data Dictionary (CSDD), Chapter 2.

NOTE(*) Discard

Kit 284097A02R00

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

22 E0088-10-125 2 Lead

99 F5791001800300 1 Support (98) F5791001800000 03 *

NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common

Support Data Dictionary (CSDD), Chapter 2.

NOTE(*) Discard

NOTE : Refer to the AIRBUS Standards Manual (SM) 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. The SM will give you the correct part number

to part number relationship.

Kit 284097A03R00

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

3 NSA5050-3 11 Nut

21 NSA5519-3B 1 Clamp

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 25

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A340

SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

22 E0088-10-125 1 Lead

23 NAS6603-2 8 Bolt

26 NSA5519-2B 3 Clamp

27 E0088-10-190 1 Lead

28 E0088-10-63 4 Lead

35 ASNA2050DCJ3215 12 Rivet

36 F5791036900100 1 Support

37 NAS1096-3-8 4 Screw

38 NAS1096-3-9 1 Screw

39 NAS1149F0332P 1 Washer

40 MS35650-302 5 Nut

41 NSA5575-8A 1 Clamp

42 NSA5575-11 3 Clamp

45 E0088-10-80 2 Lead

84 A2823301800500 2 Angle

98 F5791001800200 1 Support (98) F5791001800000 03 *

99 F5791001800300 1 Support (98) F5791001800000 03 *

116 NAS1149D0316H 2 Washer

117 E0088-10-250 2 Lead

NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common

Support Data Dictionary (CSDD), Chapter 2.

NOTE(*) Discard

NOTE : Refer to the AIRBUS Standards Manual (SM) 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. The SM will give you the correct part number

to part number relationship.

Kit 284097A04R00

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

3 NSA5050-3 11 Nut

21 NSA5519-3B 1 Clamp

22 E0088-10-125 1 Lead

23 NAS6603-2 8 Bolt

26 NSA5519-2B 3 Clamp

27 E0088-10-190 1 Lead

28 E0088-10-63 4 Lead

35 ASNA2050DCJ3215 12 Rivet

36 F5791036900100 1 Support

37 NAS1096-3-8 4 Screw

38 NAS1096-3-9 1 Screw

39 NAS1149F0332P 1 Washer

40 MS35650-302 5 Nut

41 NSA5575-8A 1 Clamp

42 NSA5575-11 3 Clamp

45 E0088-10-80 2 Lead

84 A2823301800500 2 Angle

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 26

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A340

SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

98 F5791001800200 1 Support (98) F5791001800000 03 *

99 F5791001800300 1 Support (98) F5791001800000 03 *

116 NAS1149D0316H 2 Washer

117 E0088-10-250 2 Lead

NOTE : For definitions of interchangeability codes in column INT. refer to ATA Common

Support Data Dictionary (CSDD), Chapter 2.

NOTE(*) Discard

NOTE : Refer to the AIRBUS Standards Manual (SM) 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. The SM will give you the correct part number

to part number relationship.

Kit 284097B01R01

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

1 ASNA2027VBV3-3 14 Bolt

2 AN960-10L 28 Washer

3 NSA5474-3K7 14 Nut

Kit 284097B02R02

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

3 NSA5474-3K7 10 Nut

4 NAS1790-4R20 4 Bolt

5 NSA5474-4K7 10 Nut

7 NAS6603-2 10 Bolt

8 AN742D6 10 Clamp

9 NAS1790-4R16 4 Bolt

10 E0088-41-100 10 Lead

11 NAS1790-4R10 2 Bolt

Kit 284097B03R02

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

3 NSA5474-3K7 10 Nut

4 NAS1790-4R20 6 Bolt

5 NSA5474-4K7 10 Nut

6 E0088-41-125 8 Lead

7 NAS6603-2 10 Bolt

8 AN742D6 10 Clamp

9 NAS1790-4R16 2 Bolt

10 E0088-41-100 2 Lead

11 NAS1790-4R10 2 Bolt

Kit 284097B04R01

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 27

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A340

SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

3 NSA5474-3K7 8 Nut

5 NSA5474-4K7 8 Nut

6 E0088-41-125 8 Lead

7 NAS6603-2 8 Bolt

15 NAS6604-7 4 Bolt

16 NAS6604-8 4 Bolt

17 NAS1149F0432P 8 Washer

29 AN742D4 8 Clamp

Kit 284097B05R03

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

2 AN960-10L 16 Washer

3 NSA5474-3K7 50 Nut

7 NAS6603-2 40 Bolt

12 E0088-10-100 8 Lead

13 E0088-10-160 12 Lead

14 NAS6603-6 2 Bolt

18 E0088-10-250 4 Lead

19 NAS6603-7 4 Bolt

21 NAS6603-10 2 Bolt

24 E0088-10-570 4 Lead

26 E0088-10-125 8 Lead

27 NAS6603-14 8 Bolt

29 AN742D4 40 Clamp

Kit 284097B05S02

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

12 E0088-10-100 8 Lead

29 AN742D4 40 Clamp

Kit 284097B06R03

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

7 NAS6603-2 10 Bolt

8 AN742D6 4 Clamp

19 NAS6603-1 2 Bolt

26 E0088-10-125 2 Lead

27 E0088-16-160 2 Lead

28 NSA5050-4 4 Nut

29 AN742D4 6 Clamp

30 NSA5050-3 10 Nut

32 NAS1790-4R14 4 Bolt

33 E0088-41-160 4 Lead

34 E0088-51-125 2 Lead

35 MS21042-06 2 Nut

36 NAS1096-1-6 2 Screw

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 28

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A340

SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

38 NAS6605-10 2 Bolt

39 NSA5474-5K7 2 Nut

Kit 284097B06S02

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

7 NAS6603-2 2 Bolt

8 AN742D6 2 Clamp

26 E0088-10-125 2 Lead

28 NSA5050-4 2 Nut

30 NSA5050-3 2 Nut

32 NAS1790-4R14 2 Bolt

33 E0088-41-160 2 Lead

Kit 284097B07R03

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

40 NSA5477VHK5-10 6 Bolt

41 NSA5477VHK5-11 2 Bolt

42 NSA5477VHK5-13 2 Bolt

43 NSA5477VHK5-15 2 Bolt

44 NSA5477VHK5-20 2 Bolt

45 NSA5477VHK6-15 4 Bolt

46 NSA5477VHK6-16 2 Bolt

47 NSA5472-5K7 12 Nut

48 NSA5472-6K7 2 Nut

49 NSA5477VHK5-9 4 Bolt

50 NSA5477VHK5-12 2 Bolt

51 NSA5477VHK5-14 2 Bolt

52 NSA5477VHK5-19 2 Bolt

53 NSA5477VHK6-14 2 Bolt

Kit 284097B07S03

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

40 NSA5477VHK5-10 2 Bolt

49 NSA5477VHK5-9 4 Bolt

50 NSA5477VHK5-12 2 Bolt

51 NSA5477VHK5-14 2 Bolt

52 NSA5477VHK5-19 2 Bolt

53 NSA5477VHK6-14 2 Bolt

45 NSA5477VHK6-15 2 Bolt

Kit 284097B08R00

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 29

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A340

SERVICE BULLETIN

3 NSA5474-3K7 8 Nut

5 NSA5474-4K7 8 Nut

6 E0088-41-125 8 Lead

7 NAS6603-2 10 Bolt

8 AN742D6 2 Clamp

15 NAS6604-7 4 Bolt

16 NAS6604-8 4 Bolt

17 NAS1149F0432P 8 Washer

28 NSA5050-4 2 Nut

29 AN742D4 8 Clamp

30 NSA5050-3 2 Nut

32 NAS1790-4R14 2 Bolt

33 E0088-41-160 2 Lead

Kit 284097B09R00

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

7 NAS6603-2 2 Bolt

8 AN742D6 2 Clamp

28 NSA5050-4 2 Nut

30 NSA5050-3 2 Nut

32 NAS1790-4R14 2 Bolt

33 E0088-41-160 2 Lead

Kit 284097C01R04

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

3 MS20470AD5-10A 4 Rivet

4 F2818007601200 2 Lead

5 NAS1096-1-7 5 Screw

6 NAS1149DN632K 5 Washer

7 NSA5519-4B 5 Clamp

8 NAS1149DN616H 5 Washer

9 MS21042-06 5 Nut

12 F2828007500400 2 Lead

Kit 284097C02R04

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

3 MS20470AD5-10A 4 Rivet

4 F2818007601200 2 Lead

5 NAS1096-1-7 8 Screw

6 NAS1149DN632K 8 Washer

7 NSA5519-4B 7 Clamp

8 NAS1149DN616H 8 Washer

9 MS21042-06 8 Nut

12 F2828007500400 4 Lead

13 F2828007400600 1 Lead

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 30

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A340

SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

14 NSA5519-2B 1 Clamp

NOTE : Refer to the AIRBUS Standards Manual (SM) 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. The SM will give you the correct part number

to part number relationship.

Kit 284097C02S01

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

3 MS20470AD5-10A 4 rivet

4 F2818007601200 2 b.lead

5 NAS1096-1-7 2 screw

6 NAS1149DN632K 2 washer

7 NSA5519-4B 2 clamp

8 NAS1149DN616H 2 washer

9 MS21042-06 2 nut

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP

MAT No.

Lubricant Mat. No. 06-004 As required

Varnish Mat. No. 07-001D As required

Sealant Mat. No. 09-001B As required

Sealant Mat. No. 09-002 As required

Sealant Mat. No. 09-002D As required

Sealant Mat. No. 09-013B As required

Sealant Mat. No. 09-016B As required

Sealant Mat. No. 09-025 As required

Cleaning Agent Mat. No. 11-026 As required

Alodine Mat. No. 13-002 As required

Primer Mat. No. 16-001C As required

Wash Primer Mat. No. 16-020 As required

Emery (320) None As required

Lockwire MS20995C32 None As required

(2) Components

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

NSA5479BV6-17X 4 Bolt

NSA5479BV6-18X 4 Bolt

ASNA2327-3-10 2 Bracket

ASNA2528-3 2 Nut

ASNA2531-4 4 Nut

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 31

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A340

SERVICE BULLETIN

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

ASNA2531-7 8 Nut

MS21061-3 4 Nut

MS21069-3 6 Nut

NSA5050-3 11 Nut

NSA5050-4 8 Nut

NSA5050-6 4 Nut

MS21075L3 4 Nut

ASNA2050DCJ3215 218 Rivet

ASNA2050DCJ3620 32 Rivet

ASNA2050DXJ4020 25 Rivet

ASNA2051DCJ2412 22 Rivet

ASNA2055-03 4 Washer

313 A/R Marker

317 A/R Marker

358 A/R Marker

NSA8203-025 2 O-ring

AN742D6 20 Clamp *

NOTE(*) This item replaces Clamp PN AN742D5 supplied in Kits 284097B02R01

and B03R01.

E. PARTS TO BE RE-IDENTIFIED BY THE OPERATOR

ITEM NEW PART No. KEYWORD ITEM OLD PART No. INT

118 A2821003820200 Plate (118) A2821003820000 03

132 A2821040500100 Sleeve (132) A2821040500000 03

29 F2821003700200 Pipe (29) F2821003700000 03

30 F2821003700300 Pipe (30) F2821003700100 03

20 F2821019400200 Rod (20) F2821019400000 03

131 F2821035800095 Pipe (131) F2821035800000 03

25 F2821070700200 Pipe (25) F2821070700000 03

NOTE : For definitions of interchangeability codes shown in column INT. refer to ATA Common

Support Data Dictionary (CSDD), Chapter 2.

F. TOOLING - PRICE AND AVAILABILITY

None

G. SPECIAL TOOLS

None

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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A340

SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL

WARNING : MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE

IN POSITION BEFORE YOU START A TASK ON OR NEAR :

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND THE RELATED DOORS

- COMPONENTS THAT MOVE

MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS.

WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY

INSTALLED ON THE LANDING GEAR.

THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR.

WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND 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 THE SAFETY AREA, DO NOT:

- SMOKE - MAKE SPARKS OR FIRE - USE ANY EQUIPMENT THAT IS NOT

APPROVED FOR REFUEL/DEFUEL PROCEDURES.

CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY

SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR

MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND

THE WORK AREA AS CLEAN AS POSSIBLE, TO DO THIS :

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER

CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

(1) Preparation

(a) Config. 01 thru Config. 03

1 Put the warning notices in position before you work on the aircraft.

2 Make sure that the aircraft is electrically grounded (Refer to AMM 12-34-24,

Page block 201).

3 Defuel the wing, center tank and the THS trim fuel tanks (Refer to AMM

28-25-00, Page block 301).

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A340

SERVICE BULLETIN

4 Do the procedure as specified in the removal of the covers 147AZ and 148AZ

and open them (Refer to AMM 57-17-11, Page block 401).

5 Put the warning notices in position:

- On the HYD/FUEL control panel 245VU, to tell persons not to refuel the

aircraft.

- On the refuel/defuel control panel 990VU, to tell persons not to refuel the

aircraft.

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

block 201).

7 Make sure that the circuit breakers of the systems that you will work on are open,

safety and tagged.

8 Trim the horizontal tail plane back to the full up position (Refer to AMM 27-40-00).

9 Put access platforms in position below the LH and RH wings and zone 319

and zone 346.

10 Open the access door 312AR (Refer to AMM 55-11-04).

11 Config. 01 open the access panel 319BR and 319 BL. (Refer to AMM 55-11-14,

Page block 401).

12 Config. 02 thru Config. 03 open the access panel 319DR and 319 BL. (Refer

to AMM 55-11-14, Page block 401).

13 Remove the trim tank transfer-pump housing, if required (Refer to AMM

28-27-56, Page block 401).

14 Open the NACA vent intake panel 346AB (Refer to AMM 28-12-48, Page block

401).

15 Remove the access panels 541AB (641AB), 541AZ (641AZ), 541BZ (641BZ),

541BB (641BB), 541FB (641FB), 541SB (641SB), 542AB (642AB), 542KB

(642KB), 541CZ (641CZ) and 560CB (660CB) (Refer to AMM 57-27-11, Page

block 401).

16 Remove the access panels 191KB and 192PB (Refer to AMM 53-35-13, Page

block 401).

17 For the detail 22 (Refer to Figure 11, Sheet 5), Do the procedure as specified in

the removal of the passenger seat between FR40 and FR40.2 and remove them

(If necessary) (Refer to AMM 25-21-41, Page block 401).

18 For the detail 22 (Refer to Figure 11, Sheet 5), remove the floor panel 251WF

between FR40 and FR42 (If necessary) (Refer to AMM 53-00-00, Page block

201).

19 Disengage the insulation on the FR47 (Refer to AMM 25-80-00, Page block 001).

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20 Open the access doors 147AZ and 148AZ (Refer to AMM 57-17-11, Page

block 401).

21 Vent the fuel tanks (Refer to AMM 28-10-00, Page block 301).

22 Remove the flap track fairings 534AB (634AB) and 534CB (634CB) (Refer to

AMM 57-56-11, Page block 401 for access to the wing skin bolt (P1)).

(b) Config. 04

1 Make sure that the aircraft is grounded (Refer to AMM 12-34-24, Page block 201).

2 Put the access platforms in position.

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

block 201).

4 Do the procedure as specified in the removal of the under wing tank access

panels 541AB, 641AB and remove them (Refer to AMM 57-27-11, Page block

401).

5 Remove the access panels 541AZ, 541BZ, 641AZ and 641BZ (Refer to AMM

57-27-11, Page block 401).

6 Do the procedure as specified in the removal of the belly fairing access panels

191KB and 192PB and remove them (Refer to AMM 53-35-13, Page block 401).

7 For the detail 22 (Refer to Figure 11, Sheet 5), Do the procedure as specified in

the removal of the passenger seat between FR40 and FR40.2 and remove them

(If necessary) (Refer to AMM 25-21-41, Page block 401).

8 For the detail 22 (Refer to Figure 11, Sheet 5), remove the floor panel 251WF

between FR40 and FR42 (If necessary) (Refer to AMM 53-00-00, Page block

201).

9 Disengage the insulation on the FR47 (Refer to AMM 25-80-00, Page block 001).

10 If installed, do the procedure as specified in the removal of the center tank

harnesses 91QT and 92QT (Refer to AMM 28-42-44, Page block 401).

11 Defuel the center fuel tank (Refer to AMM 28-25-00, Page block 301).

12 Do the procedure as specified in the removal of the covers 147AZ and 148AZ

and open them (Refer to AMM 57-17-11, Page block 401).

13 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).

(c) Config. 05 ADDITIONAL WORK (Introduced at revision 03)

1 Put the warning notices in position before you work on the aircraft.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 35

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

2 Make sure that the aircraft is electrically grounded (Refer to AMM 12-34-24,

Page block 201).

3 Defuel the wing fuel tanks (Refer to AMM 28-25-00, Page block 301).

4 Put the warning notices in position:

- On the HYD/FUEL control panel 245VU, to tell persons not to refuel the

aircraft.

- On the refuel/defuel control panel 990VU, to tell persons not to refuel the

aircraft.

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

block 201).

6 Make sure that the circuit breakers of the systems that you will work on are open,

safety and tagged.

7 Put access platforms in position below the LH and RH wings between ribs 1 to 5.

8 Remove the access panels 541AB (641AB), 541BB (641BB), 541AZ (641AZ)

and 541CZ (641CZ) (Refer to AMM 57-27-11, Page block 401).

9 Vent the inner fuel tanks (Refer to AMM 28-10-00, Page block 301).

(d) Config. 06 ADDITIONAL WORK (Introduced at revision 03)

1 Put the warning notices in position before you work on the aircraft.

2 Make sure that the aircraft is electrically grounded (Refer to AMM 12-34-24,

Page block 201).

3 Defuel the wing fuel tanks (Refer to AMM 28-25-00, Page block 301).

4 Put the warning notices in position:

- On the HYD/FUEL control panel 245VU, to tell persons not to refuel the

aircraft.

- On the refuel/defuel control panel 990VU, to tell persons not to refuel the

aircraft.

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

block 201).

6 Make sure that the circuit breakers of the systems that you will work on are open,

safety and tagged.

7 Put access platforms in position below the LH and RH wings at ribs 1 to 3.

8 Remove the access panels 541AB (641AB) and 541AZ (641AZ) (Refer to AMM

57-27-11, Page block 401).

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 36

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

9 Vent the inner fuel tanks (Refer to AMM 28-10-00, Page block 301).

(e) Config. 07

1 Make sure that the aircraft is grounded (Refer to AMM 12-34-24, Page block 201).

2 Put the access platforms in position.

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

block 201).

4 Defuel the center fuel tank (Refer to AMM 28-25-00, Page block 301).

5 Do the procedure as specified in the removal of the covers 147AZ and 148AZ

and open them (Refer to AMM 57-17-11, Page block 401).

6 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).

(2) Standard Practices

(a) For the electrical bonding procedure (Refer to AMM 20-28-00, Page block 001).

(b) For the Station/Frame (STA/FR) identification (Refer to AMM 06-31-53, Page

block 001).

(c) For the material specification (Mat. No.) in this Service Bulletin (Refer to

Consumable Materials List (CML)).

(d) Clean the surfaces with Cleaning Agent (Mat. No. 11-026).

(e) Use a non-metallic spatula to remove the sealant and clean the areas with Cleaning

Agent (Mat. No. 11-026).

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

(g) Removal and installation of fasteners (Refer to SRM 51-42-11, Page block 001).

(h) Cut the rivets to the necessary length.

(i) For standard torque values (Refer to SRM 51-49-00).

(j) For information on tightening torques for standard threaded fasteners (Refer to AMM

20-21-11, Page block 201).

(k) For fastener, hole and drill data (Refer to SRM 51-44-11).

(l) For the application of sealant (Refer to SRM 51-24-00).

(m) For the repair of protective treatments (Refer to SRM 51-21-00).

(n) Apply the Fuel Tank Sealant Polysulfide (Mat. No. 09-001B).

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 37

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A340

SERVICE BULLETIN

(o) Apply the Chemical Conversion Coating Yellow Aluminum (Mat. No. 13-002).

(p) Apply the Polyurethane Primer (Mat. No. 16-001C).

(q) Apply the Corrosion Inhibiting fillet Consistency (Mat. No. 09-016B) to the interfaces

of the structure and all the parts.

(r) Apply the Fuel Tank Sealant Polysulfide (Mat. No. 09-002) to the interfaces of

the structure and all the parts.

(s) Apply the Low Density Fuel Tank Sealant (Mat. No. 09-002D).

(t) Apply the Corrosion Inhibiting sealant Sprayable (Mat. No. 09-025).

(u) Apply the Corrosion Inhibiting Brush Consistency (Mat. No. 09-013B) on the

fasteners.

(v) For the repair of the paint coatings (Refer to SRM 51-75-12).

(w) For fuel tank sealing (Refer to SRM 51-76-12).

(x) For alternative and substitute fasteners (Refer to SRM 51-43-12).

(y) For the re-identification of the parts, use the indelible markers, staedtler 313 or

staedtler 317 or staedtler 358.

B. MODIFICATION

(1) Wing Tank Bonding, Config. 01 thru Config. 02

NOTE : The procedures that follow are applicable for the LH and RH wings.

(a) Do the electrical bonding of the structure and the equipment as listed in Table 1.

Table 1

AREA EQUIPMENT &

SYSTEM

ELECTRICAL

BONDING METHOD

REF. FIGURE KIT No.

Rib Bay 1-2, 3-4,

4-5, 11-12, 23-24

Fuel Diffuser to

Mounting Bracket

Bond bolt to the

structure.

Fig.43 B01R01

Rib Bay 2-5,

22-23, 32-33

Water Drain Install the bonding

lead. Bond the pipe

clamp to the pipe

and the bolt to the

structure.

Fig.41 B02R02

Rib Bay 2-3, 3-4 Pump Canister to

Pipe

Install the bonding

lead. Bond the

pipe clamp to the

pipe. Bond the

pump canister to the

attachment fitting.

Fig.44 B04R01

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 38

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

AREA EQUIPMENT &

SYSTEM

ELECTRICAL

BONDING METHOD

REF. FIGURE KIT No.

Rib Bay 2-3 Fuel Pipe lug Reinstall the bonding

lead to the lug.

Fig.44 B04R01

Rib Bay 2-3, 3-4 Pressure Switch

Pipes

Install the bonding

lead. Bond the pipe

clamp to the pipe.

Bond the bolt to the

structure.

Fig.40 B05R03

Rib Bay 1-2 Fuel Pipe Tie Rod to

Rib 1 Structure

Install the bonding

lead. Bond the tie

rod clamp to the tie

rod. Bond the bolt to

the structure.

Fig.45 B06R03

Rib Bay 1-2 Water Drain Install the bonding

leads. Bond the pipe

clamps to the pipes.

Bond the bolts to the

structure.

Fig.45 B06R03

Lower Skin Rib

1-2

Stringer 14 (Q) Bond the bolt thru

the skin and the

structure.

Fig.39 Sheet 5 B07R03

Lower Skin Rib

1-2

Stringer 19 (P) Bond the bolt thru

the skin and the

structure.

Fig.39 Sheet 5 B07R03

Lower Skin Rib

3-4

Stringer 14 (N) Bond the bolt thru

the skin and the

structure.

Fig.39 Sheet 4 B07R03

Lower Skin Rib

4-5

Stringer 19 (M) Bond the bolt thru

the skin and the

structure.

Fig.39 Sheet 3 B07R03

Lower Skin Rib

11-12

Stringer 20 (L) Bond the bolt thru

the skin and the

structure.

Fig.39 Sheet 2 B07R03

Lower Skin Rib

23-24

Stringer 20 (K) Bond the bolt thru

the skin and the

structure.

Fig.39 Sheet 2 B07R03

Lower Skin Rib

23-24

Rear Spar (J) Bond the bolt thru

the skin and the

structure.

Fig.39 Sheet 2 B07R03

(b) Kit 284097B01R01

Modify the Electrical Bonding of the Fuel Diffuser to the Mounting Bracket between

Rib Bays 1-2, 3-4, 4-5, 11-12 and 23-24.

Refer to Figure 43 Sheet 1.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 39

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A340

SERVICE BULLETIN

1 Remove the diffusers between ribs 1-2, 3-4, 4-5, 11-12 and 23-24 (Refer to AMM

28-25-42, Page block 401).

NOTE : To do the electrical bonding of the wing skins it is necessary

to remove the diffusers. It is recommended to use the Kit

284097B01R01 to do the electrical bonding of the diffusers and to

use the Kit 284097B07R03 to do the wing skin at the same time.

2 Remove:

14 Nut Item (3) Discard

28 Washer Item (2) Discard

14 Bolt Item (1) Discard

3 Prepare for electrical bonding (Refer to AMM 20-28-00, Page block 201).

4 Install the diffusers between ribs 1-2, 3-4, 4-5, 11-12 and 23-24 (Refer to AMM

28-25-42, Page block 401).

5 Install:

14 Bolt ASNA2027VBV3-3 Item 1

28 Washer AN960-10L Item 2

14 Nut NSA5474-3K7 Item 3

6 Do the Electrical Bonding Test (Refer to AMM 20-28-00, Page block 501).

7 Apply sealant to the fasteners and bare metal areas (Refer to AMM 20-28-00,

Page block 201).

(c) Kit 284097B07R03

Modify the Electrical Bonding of the Lower Wing Skin between the Rib Bays 1-2, 3-4,

4-5, 11-12 and 23-24.

Refer to Figure 39 Sheet 1 thru Sheet 6

NOTE : To do the electrical bonding of the wing skins it is necessary to remove

the diffusers. It is recommended to use the Kit 284097B01R01 to do the

electrical bonding of the diffusers and to use the Kit 284097B07R03 to

do the wing skin at the same time.

1 Remove the bellmouth assy. PN F2825015800051 (LH) and F2825015800151

(RH) to get access to wing skin bolt (position Q) between ribs 1 and 2, at

stringer 14.

2 Remove:

4 Bolt Item (40) Discard

2 Bolt Item (41) Discard

2 Bolt Item (42) Discard

2 Bolt Item (43) Discard

2 Bolt Item (44) Discard

2 Pin Item (45) Discard

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 40

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

or

2 Pin Item (46) Discard

12 Nut Item (47) Discard

2 Nut Item (48) Discard

NOTE : When you remove the fasteners, Items (40) thru (46), measure their

grip lengths so that you can select the correct oversize replacement

fasteners.

3 Ream the holes for 1st oversize fasteners (Refer to SRM 51-44-11).

4 Prepare for electrical bonding (Refer to AMM 20-28-00, Page block 201).

5 Use the correct grip length fastener and install:

4 Bolt-Hi Lok NSA5477VHK5-10 Item 40

or

4 Bolt-Hi Lok NSA5477VHK5-9 Item 49

2 Bolt-Hi Lok NSA5477VHK5-11 Item 41

or

2 Bolt-Hi Lok NSA5477VHK5-10 Item 40

2 Bolt-Hi Lok NSA5477VHK5-13 Item 42

or

2 Bolt-Hi Lok NSA5477VHK5-12 Item 50

2 Bolt-Hi Lok NSA5477VHK5-15 Item 43

or

2 Bolt-Hi Lok NSA5477VHK5-14 Item 51

2 Bolt-Hi Lok NSA5477VHK5-20 Item 44

or

2 Bolt-Hi Lok NSA5477VHK5-19 Item 52

or

2 Bolt-Hi Lok NSA5477VHK6-14 Item 53

2 Bolt-Hi Lok NSA5477VHK6-16 Item 46

or

2 Bolt-Hi Lok NSA5477VHK6-15 Item 45

12 Nut NSA5472-5K7 Item 47

2 Nut NSA5472-6K7 Item 48

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 41

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

6 Do the Electrical Bonding Test (Refer to AMM 20-28-00, Page block 501).

7 Apply sealant to the fasteners and bare metal areas (Refer to AMM 20-28-00,

Page block 201).

8 Install the bellmouth assy. p/n F2825015800051 (LH) and F2825015800151

(RH) that was removed to get access to wing skin bolt (position Q) between

ribs 1 and 2, at stringer 14.

(d) Kit 284097B02R02

Modify the Electrical Bonding to the Water Drains between Rib Bays 2-5, 22-23

and 32-33.

Refer to Figure 41, Sheet 1 thru Sheet 5.

1 Remove:

4 Bolt Item (4) Discard

10 Nut Item (5) Discard

4 Bolt Item (9) Discard

2 Bolt Item (11) Discard

2 Prepare for electrical bonding (Refer to AMM 20-28-00, Page block 201).

3 Install:

10 Nut NSA5474-3K7 Item 3

4 Bolt NAS1790-4R20 Item 4

10 Nut NSA5474-4K7 Item 5

10 Bolt NAS6603-2 Item 7

4 Bolt NAS1790-4R16 Item 9

10 Lead-Bonding E0088-41-100 Item 10

2 Bolt NAS1790-4R10 Item 11

10 Clamp AN742D6 Item 8

4 Do the Electrical Bonding Test (Refer to AMM 20-28-00, Page block 501).

5 Apply sealant to the fasteners and bare metal areas (Refer to AMM 20-28-00,

Page block 201).

(e) Kit 284097B04R01

Modify the Electrical Bonding of the Pump Canisters to the Pipe between Rib

Bay 2-3 and 3-4.

Refer to Figure 44, Sheet 1.

1 Remove:

8 Nut Item (5) Discard

4 Bolt Item (15) Discard

4 Bolt Item (16) Discard

8 Washer Item (17) Discard

2 Prepare for electrical bonding, (Refer to AMM 20-28-00, Page block 201).

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 42

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

3 Install:

8 Nut NSA5474-3K7 Item 3

8 Nut NSA5474-4K7 Item 5

8 Lead-Bonding E0088-41-125 Item 6

8 Bolt NAS6603-2 Item 7

8 Clamp AN742D4 Item 29

4 Bolt NAS6604-7 Item 15

4 Bolt NAS6604-8 Item 16

8 Washer-Flat NAS1149F0432P Item 17

4 Do the Electrical Bonding Test (Refer to AMM 20-28-00, Page block 501).

5 Apply sealant to the fasteners and bare metal areas (Refer to AMM 20-28-00,

Page block 201).

(f) Kit 284097B05R03

Modify the Electrical Bonding of the Pressure Switch Pipes between Rib Bays

2-3 and 3-4.

Refer to Figure 40, Sheet 1 thru Sheet 6.

1 Remove:

16 Washer Item (2) Discard

10 Nut Item (3) Discard

2 Bolt Item (14) Discard

4 Bolt Item (19) Discard

2 Bolt Item (21) Discard

8 Bolt Item (27) Discard

2 Prepare for electrical bonding (Refer to AMM 20-28-00, Page block 201).

3 Install:

16 Washer AN960-10L Item 2

50 Nut NSA5474-3K7 Item 3

40 Bolt NAS6603-2 Item 7

8 Lead-Bonding E0088-10-100 Item 12

12 Lead-Bonding E0088-10-160 Item 13

2 Bolt NAS6603-6 Item 14

4 Lead-Bonding E0088-10-250 Item 18

4 Bolt NAS6603-7 Item 19

2 Bolt NAS6603-10 Item 21

4 Lead-Bonding E0088-10-570 Item 24

8 Lead-Bonding E0088-10-125 Item 26

8 Bolt NAS6603-14 Item 27

40 Clamp AN742D4 Item 29

4 Do the Electrical Bonding Test (Refer to AMM 20-28-00, Page block 501).

5 Apply sealant to the fasteners and bare metal areas (Refer to AMM 20-28-00,

Page block 201).

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 43

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A340

SERVICE BULLETIN

(g) Kit 284097B06R03

Modify the Electrical Bonding of the Fuel Pipe Tie Rod to the Rib 1 Structure and the

Water Drains between Rib Bay 1-2.

Refer to Figure 45, Sheet 1 thru Sheet 3.

1 Remove:

2 Nut Item (28) Discard

4 Bolt Item (32) Discard

2 Nut Item (35) Discard

2 Screw Item (36) Discard

2 Bolt Item (38) Discard

2 Nut Item (39) Discard

2 Prepare for electrical bonding (Refer to AMM 20-28-00, Page block 201).

3 Install:

10 Bolt NAS6603-2 Item 7

4 Clamp AN742D6 Item 8

2 Bolt NAS6603-1 Item 19

2 Lead-Bonding E0088-10-125 Item 26

2 Lead-Bonding E0088-16-160 Item 27

4 Nut NSA5050-4 Item 28

6 Clamp AN742D4 Item 29

10 Nut NSA5050-3 Item 30

4 Bolt NAS1790-4R14 Item 32

4 Lead-Bonding E0088-41-160 Item 33

2 Lead-Bonding E0088-51-125 Item 34

2 Nut MS21042-06 Item 35

2 Screw NAS1096-1-6 Item 36

2 Bolt NAS6605-10 Item 38

2 Nut NSA5474-5K7 Item 39

4 Do the Electrical Bonding Test (Refer to AMM 20-28-00, Page block 501).

5 Apply sealant to the fasteners and bare metal areas (Refer to AMM 20-28-00,

Page block 201).

(2) Wing Tank Bonding, Config. 03

NOTE : The procedures that follow are applicable to the LH and RH wings.

(a) Do the electrical bonding of the structure and the equipment as listed in Table 2.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 44

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Table 2

AREA EQUIPMENT &

SYSTEM

ELECTRICAL

BONDING METHOD

REF. FIGURE KIT No.

Rib Bay 1-2, 3-4,

4-5, 11-12, 23-24

Fuel Diffuser to

Mounting Bracket

Bond bolt to the

structure.

Fig.43 B01R01

Rib Bay 2-5,

22-23, 32-33

Water Drain Install the bonding

lead. Bond the pipe

clamp to the pipe

and the bolt to the

structure.

Fig.42 B03R02

Rib Bay 2-3, 3-4 Pump Canister to

Pipe

Install the bonding

lead. Bond the

pipe clamp to the

pipe. Bond the

pump canister to the

attachment fitting.

Fig.44 B04R01

Rib Bay 2-3 Fuel Pipe lug Reinstall the bonding

lead to the lug.

Fig.44 B04R01

Rib Bay 2-3, 3-4 Pressure Switch

Pipes

Install the bonding

lead. Bond the pipe

clamp to the pipe.

Bond the bolt to the

structure.

Fig.40 B05R03

Rib Bay 1-2 Fuel Pipe Tie Rod to

Rib 1 Structure

Install the bonding

lead. Bond the tie

rod clamp to the tie

rod. Bond the bolt to

the structure.

Fig.45 B06R03

Rib Bay 1-2 Water Drain Install the bonding

leads. Bond the pipe

clamps to the pipes.

Bond the bolts to the

structure.

Fig.45 B06R03

Lower Skin Rib

1-2

Stringer 14 (Q) Bond the bolt thru

the skin and the

structure.

Fig.39 Sheet 5 B07R03

Lower Skin Rib

1-2

Stringer 19 (P) Bond the bolt thru

the skin and the

structure.

Fig.39 Sheet 5 B07R03

Lower Skin Rib

3-4

Stringer 14 (N) Bond the bolt thru

the skin and the

structure.

Fig.39 Sheet 4 B07R03

Lower Skin Rib

4-5

Stringer 19 (M) Bond the bolt thru

the skin and the

structure.

Fig.39 Sheet 3 B07R03

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 45

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

AREA EQUIPMENT &

SYSTEM

ELECTRICAL

BONDING METHOD

REF. FIGURE KIT No.

Lower Skin Rib

11-12

Stringer 20 (L) Bond the bolt thru

the skin and the

structure.

Fig.39 Sheet 2 B07R03

Lower Skin Rib

23-24

Stringer 20 (K) Bond the bolt thru

the skin and the

structure.

Fig.39 Sheet 2 B07R03

Lower Skin Rib

23-24

Rear Spar (J) Bond the bolt thru

the skin and the

structure.

Fig.39 Sheet 2 B07R03

(b) Kit 284097B01R01

Modify the Electrical Bonding of the Fuel Diffuser to the Mounting Bracket between

Rib Bays 1-2, 3-4, 4-5, 11-12 and 23-24.

Refer to Figure 43, Sheet 1.

1 Remove the diffusers between ribs 1-2, 3-4, 4-5, 11-12 and 23-24 (Refer to AMM

28-25-42, Page block 401).

NOTE : To do the electrical bonding of the wing skins it is necessary

to remove the diffusers. It is recommended to use the Kit

284097B01R01 to do the electrical bonding of the diffusers and to

use the Kit 284097B07R03 to do the wing skin at the same time.

2 Remove:

14 Nut Item (3) Discard

28 Washer Item (2) Discard

14 Bolt Item (1) Discard

3 Prepare for electrical bonding (Refer to AMM 20-28-00, Page block 201).

4 Install the diffusers between ribs 1-2, 3-4, 4-5, 11-12 and 23-24 (Refer to AMM

28-25-42, Page block 401).

5 Install:

14 Bolt ASNA2027VBV3-3 Item 1

28 Washer AN960-10L Item 2

14 Nut NSA5474-3K7 Item 3

6 Do the Electrical Bonding Test (Refer to AMM 20-28-00, Page block 501).

7 Apply sealant to the fasteners and bare metal areas (Refer to AMM 20-28-00,

Page block 201).

(c) Kit 284097B07R03

Modify the Electrical Bonding of the Lower Wing Skin between the Rib Bays 1-2, 3-4,

4-5, 11-12 and 23-24.

Refer to Figure 39, Sheet 1 thru Sheet 6

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 46

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

NOTE : To do the electrical bonding of the wing skins it is necessary to remove

the diffusers. It is recommended to use the Kit 284097B01R01 to do the

electrical bonding of the diffusers and to use the Kit 284097B07R03 to

do the wing skin at the same time.

1 Remove the bellmouth assy. PN F2825015800051 (LH) and F2825015800151

(RH) to get access to wing skin bolt (position Q) between ribs 1 and 2, at

stringer 14.

2 Remove:

4 Bolt Item (40) Discard

2 Bolt Item (41) Discard

2 Bolt Item (42) Discard

2 Bolt Item (43) Discard

2 Bolt Item (44) Discard

2 Pin Item (45) Discard

or

2 Pin Item (46) Discard

12 Nut Item (47) Discard

2 Nut Item (48) Discard

NOTE : When you remove the fasteners, Items (40) thru (46), measure their

grip lengths so that you can select the correct oversize replacement

fasteners.

3 Ream the holes for 1st oversize fasteners (Refer to SRM 51-44-11).

4 Prepare for electrical bonding (Refer to AMM 20-28-00, Page block 201).

5 Use the correct grip length fastener and install:

4 Bolt-Hi Lok NSA5477VHK5-10 Item 40

or

4 Bolt-Hi Lok NSA5477VHK5-9 Item 49

2 Bolt-Hi Lok NSA5477VHK5-11 Item 41

or

2 Bolt-Hi Lok NSA5477VHK5-10 Item 40

2 Bolt-Hi Lok NSA5477VHK5-13 Item 42

or

2 Bolt-Hi Lok NSA5477VHK5-12 Item 50

2 Bolt-Hi Lok NSA5477VHK5-15 Item 43

or

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 47

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

2 Bolt-Hi Lok NSA5477VHK5-14 Item 51

2 Bolt-Hi Lok NSA5477VHK5-20 Item 44

or

2 Bolt-Hi Lok NSA5477VHK5-19 Item 52

2 Bolt-Hi Lok NSA5477VHK6-15 Item 45

or

2 Bolt-Hi Lok NSA5477VHK6-14 Item 53

or

2 Bolt-Hi Lok NSA5477VHK6-15 Item 45

12 Nut NSA5472-5K7 Item 47

2 Nut NSA5472-6K7 Item 48

6 Do the Electrical Bonding Test (Refer to AMM 20-28-00, Page block 501).

7 Apply sealant to the fasteners and bare metal areas (Refer to AMM 20-28-00,

Page block 201).

8 Install the bellmouth assy. p/n F2825015800051 (LH) and F2825015800151

(RH) that was removed to get access to wing skin bolt (position Q) between

ribs 1 and 2, at stringer 14.

(d) Kit 284097B03R02

Modify the Electrical Bonding to the Water Drains between Rib Bays 2-5, 22-23

and 32-33.

Refer to Figure 42, Sheet 1 thru Sheet 3.

1 Remove:

6 Bolt Item (4) Discard

10 Nut Item (5) Discard

2 Bolt Item (9) Discard

2 Bolt Item (11) Discard

2 Prepare for electrical bonding (Refer to AMM 20-28-00, Page block 201).

3 Install:

10 Nut NSA5474-3K7 Item 3

6 Bolt NAS1790-4R20 Item 4

10 Nut NSA5474-4K7 Item 5

8 Lead-Bonding E0088-41-125 Item 6

10 Bolt NAS6603-2 Item 7

2 Bolt NAS1790-4R16 Item 9

2 Lead-Bonding E0088-41-100 Item 10

2 Bolt NAS1790-4R10 Item 11

10 Clamp AN742D6 Item 8

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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SERVICE BULLETIN

4 Do the Electrical Bonding Test (Refer to AMM 20-28-00, Page block 501).

5 Apply sealant to the fasteners and bare metal areas (Refer to AMM 20-28-00,

Page block 201).

(e) Kit 284097B04R01

Modify the Electrical Bonding of the Pump Canisters to the Pipe between Rib

Bay 2-3 and 3-4.

Refer to Figure 44, Sheet 1.

1 Remove:

8 Nut Item (5) Discard

4 Bolt Item (15) Discard

4 Bolt Item (16) Discard

8 Washer Item (17) Discard

2 Prepare for electrical bonding (Refer to AMM 20-28-00, Page block 201).

3 Install:

8 Nut NSA5474-3K7 Item 3

8 Nut NSA5474-4K7 Item 5

8 Lead-Bonding E0088-41-125 Item 6

8 Bolt NAS6603-2 Item 7

8 Clamp AN742D4 Item 29

4 Bolt NAS6604-7 Item 15

4 Bolt NAS6604-8 Item 16

8 Washer-Flat NAS1149F0432P Item 17

4 Do the Electrical Bonding Test (Refer to AMM 20-28-00, Page block 501).

5 Apply sealant to the fasteners and bare metal areas (Refer to AMM 20-28-00,

Page block 201).

(f) Kit 284097B05R03

Modify the Electrical Bonding of the Pressure Switch Pipes between Rib Bays

2-3 and 3-4.

Refer to Figure 40, Sheet 1 thru Sheet 6.

1 Remove:

16 Washer Item (2) Discard

10 Nut Item (3) Discard

2 Bolt Item (14) Discard

4 Bolt Item (19) Discard

2 Bolt Item (21) Discard

8 Bolt Item (27) Discard

2 Prepare for electrical bonding (Refer to AMM 20-28-00, Page block 201).

3 Install:

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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A340

SERVICE BULLETIN

16 Washer AN960-10L Item 2

50 Nut NSA5474-3K7 Item 3

40 Bolt NAS6603-2 Item 7

8 Lead-Bonding E0088-10-100 Item 12

12 Lead-Bonding E0088-10-160 Item 13

2 Bolt NAS6603-6 Item 14

4 Lead-Bonding E0088-10-250 Item 18

4 Bolt NAS6603-7 Item 19

2 Bolt NAS6603-10 Item 21

4 Lead-Bonding E0088-10-570 Item 24

8 Lead-Bonding E0088-10-125 Item 26

8 Bolt NAS6603-14 Item 27

40 Clamp AN742D4 Item 29

4 Do the Electrical Bonding Test (Refer to AMM 20-28-00, Page block 501).

5 Apply sealant to the fasteners and bare metal areas (Refer to AMM 20-28-00,

Page block 201).

(g) Kit 284097B06R03

Modify the Electrical Bonding of the Fuel Pipe Tie Rod to the Rib 1 Structure and the

Water Drains between Rib Bay 1-2.

Refer to Figure 45, Sheet 1 thru Sheet 3.

1 Remove:

2 Nut Item (28) Discard

4 Bolt Item (32) Discard

2 Nut Item (35) Discard

2 Screw Item (36) Discard

2 Bolt Item (38) Discard

2 Nut Item (39) Discard

2 Prepare for electrical bonding (Refer to AMM 20-28-00, Page block 201).

3 Install:

10 Bolt NAS6603-2 Item 7

4 Clamp AN742D6 Item 8

2 Bolt NAS6603-1 Item 19

2 Lead-Bonding E0088-10-125 Item 26

2 Lead-Bonding E0088-16-160 Item 27

4 Nut NSA5050-4 Item 28

6 Clamp AN742D4 Item 29

10 Nut NSA5050-3 Item 30

4 Bolt NAS1790-4R14 Item 32

4 Lead-Bonding E0088-41-160 Item 33

2 Lead-Bonding E0088-51-125 Item 34

2 Nut MS21042-06 Item 35

2 Screw NAS1096-1-6 Item 36

2 Bolt NAS6605-10 Item 38

2 Nut NSA5474-5K7 Item 39

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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A340

SERVICE BULLETIN

4 Do the Electrical Bonding Test (Refer to AMM 20-28-00, Page block 501).

5 Apply sealant to the fasteners and bare metal areas (Refer to AMM 20-28-00,

Page block 201).

(3) Config. 04 only

(a) Check the bonding points in the center tank.

Refer to Figure 1

Refer to Figure 2

Refer to Figure 3

NOTE : In Fuel Center Tank, the modification consists in :

- Checking the bonding points identified as potentially non conform, refer to

Figure 1, Sheet 1.

For each point identified check the presence of blue coat :

- If blue coat present, no further action.

- If no blue coat then :

Measure the electrical resistance between part and the structure, (Refer

to AMM 20-28-00, Page block 501).

- If the ohmic resistance is less than 10 milliohms, apply the blue coat.

- If the ohmic resistance is more than 10 milliohms, do the bonding,

(Refer to AMM 20-28-00, Page block 201).

1 Check the bonding points Items 46 and 47 at FR42.

Refer to Figure 1, Sheet 1, (General location)

Refer to Figure 2, Sheets 1 and 2, (Detailed location)

Refer to Figure 3, Sheet 1, (Result table)

(4) Config. 01 thru Config. 03

(a) Check the bonding points in the center tank.

Refer to Figure 4

Refer to Figure 5

Refer to Figure 6

Refer to Figure 7

Refer to Figure 8

Refer to Figure 9

Refer to Figure 10

Refer to Figure 11

Refer to Figure 12

Refer to Figure 13

Refer to Figure 14

Refer to Figure 15

Refer to Figure 16

Refer to Figure 17

Refer to Figure 18

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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A340

SERVICE BULLETIN

Refer to Figure 19

Refer to Figure 20

NOTE : In Fuel Center Tank, the modification consists in :

- Checking the bonding points identified as potentially non conform, refer to

Figure 4, Sheet 1.

For each point identified check the presence of blue coat :

- If blue coat present, no further action.

- If no blue coat then :

Measure the electrical resistance between part and the structure, (Refer

to AMM 20-28-00, Page block 501).

- If the ohmic resistance is less than 10 milliohms, apply the blue coat.

- If the ohmic resistance is more than 10 milliohms, do the bonding,

(Refer to AMM 20-28-00, Page block 201).

1 Check the bonding points Items 1 thru 9 and 65 on the outer side of the rib 1

(RH side).

Refer to Figure 4, Sheet 1, (General location)

Refer to Figure 5, Sheets 1 thru 5, (Detailed location)

Refer to Figure 6, Sheet 1, (Result table)

2 Check the bonding points Items 10 thru 14 and 66 thru 67 on the inner side of

the rib 1 (RH side).

Refer to Figure 4, Sheet 1, (General location)

Refer to Figure 7, Sheets 1 thru 4, (Detailed location)

Refer to Figure 8, Sheet 1, (Result table)

3 Check the bonding points Items 15 thru 19, 68 thru 71, 118 thru 123, 145

and 146 on the lower panel.

Refer to Figure 4, Sheet 1, (General location)

Refer to Figure 9, Sheets 1 thru 9, (Detailed location)

Refer to Figure 10, Sheet 1, (Result table)

4 Check the bonding points Items 20 thru 22, 72 thru 114 and 128 thru 134

on the upper panel.

Refer to Figure 4, Sheet 1, (General location)

Refer to Figure 11, Sheets 1 thru 7, (Detailed location)

Refer to Figure 12, Sheets 1 thru 3, (Result table)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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5 Check the bonding points Items 23 thru 45 and 135 thru 136 at FR47 on the

outer side.

Refer to Figure 4, Sheet 1, (General location)

Refer to Figure 13, Sheets 1 thru 13, (Detailed location)

Refer to Figure 14, Sheet 1 thru 2, (Result table)

6 Check the bonding points Items 48 thru 55 and 137 thru 144 at FR47 on the

inner side.

Refer to Figure 4, Sheet 1, (General location)

Refer to Figure 15, Sheets 1 thru 7, (Detailed location)

Refer to Figure 16, Sheet 1, (Result table)

7 Check the bonding points Items 56 thru 64 and 115 thru 117 on the outer

side of the rib 1 (LH side).

Refer to Figure 4, Sheet 1, (General location)

Refer to Figure 17, Sheets 1 thru 6, (Detailed location)

Refer to Figure 18, Sheet 1, (Result table)

8 Check the bonding points Items 46 and 47 at FR42.

Refer to Figure 4, Sheet 1, (General location)

Refer to Figure 19, Sheets 1 and 2, (Detailed location)

Refer to Figure 20, Sheet 1, (Result table)

(5) Config. 01 thru Config. 03

(a) Modify or install the bonding points.

Refer to Figure 21

Refer to Figure 22

Refer to Figure 23

Refer to Figure 24

Refer to Figure 25

Refer to Figure 26

Refer to Figure 27

Refer to Kit 284097A01R06

Refer to Kit 284097A02R00

1 Do the electrical bonding of the structure and the equipments as listed in Table 1.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 53

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SERVICE BULLETIN

Table 1

AREA EQUIPMENT AND

SYSTEM

ELECTRICAL

BONDING

METHOD

REF. FIGURE KIT No.

Between FR46 and

FR47 in the center

tank.

Fuel pipe. Install the bonding

lead. Bond the pipe

clamp to the pipe.

Fig. 21 A01R06

Between FR46 and

FR47 in the center

tank.

Restrictor valve

(5506QA).

Install the bonding

lead. Bond the pipe

clamp to the pipe.

Bond the screw to

the structure.

Fig. 22 A01R06

Between FR45 and

FR46 in the center

tank.

Pump canister. Install the bonding

lead. Bond the pipe

clamp to the pipe.

Bond the pump

canister to the

attachment fitting.

Fig. 23 A01R06

Between FR42 and

FR47 in the center

tank.

Hydraulic pipe

routing.

Bond the screw

to the structure.

Install the bonding

lead. Bond the pipe

clamp to the pipe.

Fig. 24 A01R06

On FR47 ACT plumbing fuel. Install the bonding

lead. Bond the pipe

clamp to the pipe.

Fig. 25 A01R06

Between FR46 and

FR47 in the center

tank.

Plumbing refuel. Install the bonding

lead. Bond the pipe

clamp to the pipe.

Fig. 26 A01R06

Rib 1 RH side and

Rib 1 LH side.

Angles to the

structure.

Install the angles. Fig. 27 A01R06

2 Modify the pipe from the filling fuel between FR46 and FR47.

Refer to Figure 21

a Remove :

Refer to Figure 21, Sheet 1

1 screw Item (23) Retain

1 nut Item (3) Discard

- Disengage the bonding leads Item (19).

b On the rod Item (20), do a stripping to the dimensions given in the Figure 21,

Sheet 2

c On the rod Item (20), install :

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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SERVICE BULLETIN

Refer to Figure 21, Sheets 1 and 2

1 Clamp NSA5519-3B Item 21

1 Lead-Bonding E0088-10-125 Item 22

1 Bolt NAS6603-2 Item 23

1 Nut NSA5050-3 Item 3

d Re-identify the rod :

Refer to Figure 21, Sheet 1

1 Rod F2821019400000 Item (20)

becomes

1 Rod F2821019400200 Item 20

e On the pipe Item (137), do a stripping to a diameter of 14 mm (0.551 in.)

and on the opposite side, do a stripping to a diameter of 14 mm (0.551

in.) (Refer to Figure 21, Sheet 3).

f Install :

- Put in position the bonding leads Item (19) and Item 22 on the pipe Item

(137) (Refer to Figure 21, Sheet 1).

. Install the screw and the nut.

1 Screw Item (23)

1 Nut NSA5050-3 Item 3

NOTE(01) Item (23) was retained at removal.

NOTE(02) Apply the Chemical Conversion Coating Yellow Aluminum

(Mat. No. 13-002) and Polyurethane Primer (Mat. No.

16-001C) on the rod Item 20 (Refer to Figure 21, Sheets 1

and 2).

3 Modify the feed pipe between the restrictor valve FIN 5506QA and the pressure

switch FIN 53QU.

Refer to Figure 22

a Remove :

Refer to Figure 22, Sheet 2

1 Screw Item (1) Retain

1 Nut Item (3) Discard

- Disengage the bonding leads Item (19).

b On the pipe Item (25), do a stripping to the dimensions given in the Figure

22, Sheet 2.

c On the pipe Item (25) install :

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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1 Bolt NAS6603-2 Item 23

1 Nut NSA5050-3 Item 3

1 Clamp NSA5519-2B Item 26

1 Bonding-Lead E0088-10-190 Item 27

d Re-identify the pipe :

1 Pipe F2821070700000 Item (25)

becomes

1 Pipe F2821070700200 Item 25

e Install :

- Put in position the bonding leads items (19) and 27 on the restrictor

valve FIN 5506QA.

- Install the screw and the nut.

1 Screw Item (1)

1 Nut NSA5050-3 Item 3

NOTE(01) Item (1) was retained at removal.

NOTE(02) Apply the Chemical Conversion Coating Yellow Aluminum

(Mat. No. 13-002) and Polyurethane Primer (Mat. No.

16-001C) on the pipe Item 25 (Refer to Figure 22, Sheet 2).

4 Modify the feed pipes of the fuel canisters FIN 5600QA1 and FIN 5600QA2.

Refer to Figure 23

a Remove :

2 Screw Item (1) Retain

2 Washer Item (12) Retain

b On the blanking plates Item (118), do a stripping to a diameter of 14 mm

(0.551 in.) (Refer to Figure 23, Sheets 1 thru 4).

c Re-identify the blanking plates.

1 Plate A2821003820000 Item (118)

becomes

2 Plate A2821003820200 Item 118

d Install :

2 Screw Item (1)

2 Washer Item (12)

2 Bonding-Lead E0088-10-250 Item 117

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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SERVICE BULLETIN

2 plate A2821003820200 Item 118

NOTE : Items (1) and (12) were retained at removal.

e Install the clamp with the bonding lead on the pipes Item (29) and Item (30).

Refer to Figure 23, Sheets 1 and 2

- Do a stripping on the pipes Item (29) and Item (30) to the dimensions

given in the Figure 23, Sheet 2.

- Install :

Refer to Figure 23, Sheets 1 and 2

2 Bolt NAS6603-2 Item 23

2 Nut NSA5050-3 Item 3

2 Clamp NSA5519-2B Item 26

2 Bonding-Lead E0088-10-63 Item 28

- Re-identify the pipe :

1 Pipe F2821003700000 Item (29)

becomes

1 Pipe F2821003700200 Item 29

1 Pipe F2821003700100 Item (30)

becomes

1 Pipe F2821003700300 Item 30

NOTE : Apply the Chemical Conversion Coating Yellow Aluminum

(Mat. No. 13-002) and Polyurethane Primer (Mat. No.

16-001C) on the pipes Item 29 and Item 30 (Refer to Figure

23, Sheet 2).

f Replace the supports Item (98).

Refer to Figure 23, Sheet 5

- Remove :

4 Rivet Item (35) Discard

2 Support F5791001800000 Item (98) Discard

- On the existing holes of the structure, do a stripping to a diameter of 10

mm (0.393 in.) (Refer to Figure 23, Sheet 5).

- Install :

1 Support F5791001800200 Item 98

1 Support F5791001800300 Item 99

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SERVICE BULLETIN

with

4 Rivet ASNA2050DCJ3215 Item 35

. Put in position the bonding lead Item 28 on the support Items 98

and 99 and install :

2 Bolt NAS6603-2 Item 23

g Install the angles Item 84 on the structure between stiffener 27 and stiffener

28.

Refer to Figure 23, Sheets 1 thru 4

- Temporarily put in position the angles Item 84 on the structure at the

dimensions given on Figure 23, Sheets 2 and 3.

2 angle A2823301800500 Item 84

- Drill the structure to match the holes of the angle Item 84 to a diameter

between 3.25 mm (0.127 in.) min. and 3.35 mm (0.131 in.) max. dia.

(Refer to Figure 23, Sheet 3).

- Remove the angles.

- On the angles, do a stripping to a diameter of 10 mm (0.393 in.) (Refer

to Figure 23, Sheet 3).

- Deburr and clean the drilled area.

- On the opposite side of the structure, do a stripping to a diameter of 10

mm (0.393 in.) (Refer to Figure 23, Sheet 4).

- Install the angles :

2 Angle A2823301800500 Item 84

with

4 Rivet ASNA2050DCJ3215 Item 35

NOTE : Before installation of the angles, clean the surfaces with

Solvent (Mat. No. 11-026) and apply the Fuel Tank Sealant

Polysulfide (Mat. No. 09-002) between the structure and the

angles (Refer to Figure 23, Sheet 3).

- Put in position the bonding lead Item 117 on the angles Item 84 (Refer

to Figure 23, Sheet 2).

- Install the screw and the washer :

2 Bolt NAS6603-2 Item 23

2 Washer NAS1149D0316H Item 116

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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A340

SERVICE BULLETIN

5 Modify the routing of the hydraulic pipe between FR42 and FR47.

Refer to Figure 24

a Remove :

2 Screw Item (33) Retain

2 Block clamp Item (34) Retain

4 Rivet Item (35) Discard

1 Support Item (36) Discard

1 Screw Item (37) Retain

1 Screw Item (38) Retain

1 Washer Item (39) Retain

1 Nut Item (3) Discard

1 Bonding-Lead Item (43) Retain

1 Nut Item (40) Discard

1 Clamp Item (44) Retain

b On the new support Item 36, do a stripping to a diameter of 12 mm (0.472

in.) and on the opposite side of the structure, do a stripping to a diameter of

12 mm (0.472 in.) (Refer to Figure 24, Sheet 2).

c Install :

2 Screw Item (33)

2 Block clamp Item (34)

1 Screw Item (37)

1 Screw Item (38)

1 Washer Item (39)

1 Bonding-Lead Item (43)

1 Clamp Item (44)

4 Rivet ASNA2050DCJ3215 Item 35

1 Support F5791036900100 Item 36

4 Screw NAS1096-3-8 Item 37

1 Screw NAS1096-3-9 Item 38

1 Washer NAS1149F0332P Item 39

5 Nut MS35650-302 Item 40

5 Nut NSA5050-3 Item 3

1 Clamp NSA5575-8A Item 41

3 Clamp NSA5575-11 Item 42

2 Bonding-Lead E0088-10-63 Item 28

2 Bonding-Lead E0088-10-80 Item 45

NOTE : Items (33), (34), (37), (38), (39), (43) and (44) were retained

at removal.

6 Modify the pipe of the ACT plumbing fuel system.

Refer to Figure 25, Sheets 1 and 2

a Remove :

2 Screw Item (23) Retain

2 Nut Item (3) Discard

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- Disengage the bonding leads Item (117), Item (129) and Item (130).

b On the pipe Item (131) and on the sleeve Item (132), do a stripping to the

dimension given in the Figure 25, Sheet 2

c On the pipe Item (131) and on the sleeve Item (132), install :

1 Bolt NAS6603-2 Item 23

1 Screw NAS1096-3-8 Item 37

2 Nut NSA5050-3 Item 3

1 Clamp NSA5519-2B Item 26

1 Clamp AN735D40 Item 128

1 Bonding-Lead E0088-10-190 Item 27

1 Bonding-Lead E0088-10-80 Item 45

d Re-identify the pipe and the sleeve :

Refer to Figure 25, Sheets 1 and 2

1 Pipe F2821035800000 Item (131)

becomes

1 Pipe F2821035800095 Item 131

1 Sleeve A2821040500000 Item (132)

becomes

1 Sleeve A2821040500100 Item 132

e Install :

- Put in position the bonding leads Item 27, Item (117) and Item (129) on

the valve ACT (5806QA) and put in position the bonding leads Item 45,

Item (117) and Item (130) on the fuel crossfeed valve (5801QA).

- Install the screw and the nut :

2 Screw Item (23)

2 Nut NSA5050-3 Item 3

NOTE(01) Item (23) was retained at removal.

NOTE(02) Apply the Chemical Conversion Coating Yellow Aluminum

(Mat. No. 13-002) and Polyurethane Primer (Mat. No.

16-001C) on the pipe Item 131 and on the sleeve Item 132

(Refer to Figure 25, Sheets 1 and 2).

7 Modify the pipe of the plumbing refuel system between FR46 and FR47.

Refer to Figure 26 Sheets 1 thru 3

a Remove :

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A340

SERVICE BULLETIN

Refer to Figure 26, Sheet 1

1 Screw Item (23) Retain

1 Nut Item (3) Discard

- Disengage the bonding lead Item (19).

b On the rod Item (20), do a stripping to the dimensions given in the Figure

26, Sheet 2.

c On the rod Item (20), install :

Refer to Figure 26, Sheets 1 and 2

1 Clamp NSA5519-3B Item 21

1 Lead-Bonding E0088-10-125 Item 22

1 Bolt NAS6603-2 Item 23

1 Nut NSA5050-3 Item 3

d Re-identify the rod :

Refer to Figure 26, Sheet 1

1 Rod F2821019400000 Item (20)

becomes

1 Rod F2821019400200 Item 20

e On the pipe Item (138), do a stripping to a diameter of 14 mm (0.551 in.)

and on the opposite side, do a stripping to a diameter of 14 mm (0.551 in.)

(Refer to Figure 26, Sheets 1 and 3).

f Install :

- Put in position the bonding leads Item (19) and Item 22 on the pipe

Item (138).

- Install the screw and the nut.

1 Screw Item (23)

1 Nut NSA5050-3 Item 3

NOTE(01) Item (23) was retained at removal.

NOTE(02) Apply the Chemical Conversion Coating Yellow Aluminum

(Mat. No. 13-002) and Polyurethane Primer (Mat. No.

16-001C) on the rod Item 20 (Refer to Figure 26, Sheets

1 and 2).

8 Install the angles on the rib 1, LH and RH side, between FR40 and FR47, only

if points 9 and 61 are not installed.

Refer to Figure 27

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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SERVICE BULLETIN

a Drill the structure to match the holes of the angle Item 84 to a diameter

between 3.25 mm (0.127 in.) min. and 3.35 mm (0.131 in.) max. diameter.

b Remove the angles.

c Deburr and clean the drilled area.

d On the opposite side of the structure, do a stripping to a diameter of 10

mm (0.393 in.).

e Install :

2 Angle A2823301800500 Item 84

attach with :

4 Rivet ASNA2050DCJ3215 Item 35

NOTE : Before installation of the angle Item 84, clean the surfaces with

Solvent (Mat. No. 11-026) and apply the Fuel Tank Sealant

Polysulfide (Mat. No. 09-002) between the structure and the

angle Item 84.

(6) Config. 07

NOTE : Config. 07 is introduced at revision 05 and is valid for aircraft not modified by

any previous revision and on which Config. 04 was previously valid.

(a) Check the bonding points in the center tank.

Refer to Figure 28

Refer to Figure 29

Refer to Figure 30

NOTE : In Fuel Center Tank, the modification consists in :

- Checking the bonding points identified as potentially non conform, refer to

Figure 28, Sheet 1.

For each point identified check the presence of blue coat :

- If blue coat present, no further action.

- If no blue coat then :

Measure the electrical resistance between part and the structure, (Refer

to AMM 20-28-00, Page block 501).

- If the ohmic resistance is less than 10 milliohms, apply the blue coat.

- If the ohmic resistance is more than 10 milliohms, do the bonding,

(Refer to AMM 20-28-00, Page block 201).

1 Check the bonding points Items 46 and 47 at FR42.

Refer to Figure 28, Sheet 1, (General location)

Refer to Figure 29, Sheets 1 and 2, (Detailed location)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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Refer to Figure 30, Sheet 1, (Result table)

(b) Modify or install the bonding points.

Refer to Figure 31

Refer to Figure 32

Refer to Figure 33

Refer to Figure 34

Refer to Kit 284097A03R00

1 Do the electrical bonding of the structure and the equipments as listed in Table 1.

Table 1

AREA EQUIPMENT AND

SYSTEM

ELECTRICAL

BONDING

METHOD

REF. FIGURE KIT No.

Between FR46 and

FR47 in the center

tank.

Fuel pipe. Install the bonding

lead. Bond the pipe

clamp to the pipe.

Fig. 31 A03R00

Between FR46 and

FR47 in the center

tank.

Restrictor valve

(5506QA).

Install the bonding

lead. Bond the pipe

clamp to the pipe.

Bond the screw to

the structure.

Fig. 32 A03R00

Between FR45 and

FR46 in the center

tank.

Pump canister. Install the bonding

lead. Bond the pipe

clamp to the pipe.

Bond the pump

canister to the

attachment fitting.

Fig. 33 A03R00

Between FR42 and

FR47 in the center

tank.

Hydraulic pipe

routing.

Bond the screw

to the structure.

Install the bonding

lead. Bond the pipe

clamp to the pipe.

Fig. 34 A03R00

2 Modify the pipe from the filling fuel between FR46 and FR47.

Refer to Figure 31

a Remove :

Refer to Figure 31, Sheet 1

1 screw Item (23) Retain

1 nut Item (3) Discard

- Disengage the bonding leads Item (19).

b On the rod Item (20), do a stripping to the dimensions given in the Figure

31, Sheet 2.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 63

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A340

SERVICE BULLETIN

c On the rod Item (20), install :

Refer to Figure 31, Sheets 1 and 2

1 Clamp NSA5519-3B Item 21

1 Lead-Bonding E0088-10-125 Item 22

1 Bolt NAS6603-2 Item 23

1 Nut NSA5050-3 Item 3

d Re-identify the rod :

Refer to Figure 31, Sheet 1

1 Rod F2821019400000 Item (20)

becomes

1 Rod F2821019400200 Item 20

e On the pipe Item (137), do a stripping to a diameter of 14 mm (0.551 in.)

and on the opposite side, do a stripping to a diameter of 14 mm (0.551

in.) (Refer to Figure 31, Sheet 3).

f Install :

- Put in position the bonding leads Item (19) and Item 22 on the pipe Item

(137) (Refer to Figure 31, Sheet 1).

. Install the screw and the nut.

1 Screw Item (23)

1 Nut NSA5050-3 Item 3

NOTE(01) Item (23) was retained at removal.

NOTE(02) Apply the Chemical Conversion Coating Yellow Aluminum

(Mat. No. 13-002) and Polyurethane Primer (Mat. No.

16-001C) on the rod Item 20 (Refer to Figure 31, Sheets 1

and 2).

3 Modify the feed pipe between the restrictor valve FIN 5506QA and the pressure

switch FIN 53QU.

Refer to Figure 32

a Remove :

Refer to Figure 32, Sheet 2

1 Screw Item (1) Retain

1 Nut Item (3) Discard

- Disengage the bonding leads Item (19).

b On the pipe Item (25), do a stripping to the dimensions given in the Figure

32, Sheet 2.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 64

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A340

SERVICE BULLETIN

c On the pipe Item (25) install :

1 Bolt NAS6603-2 Item 23

1 Nut NSA5050-3 Item 3

1 Clamp NSA5519-2B Item 26

1 Bonding-Lead E0088-10-190 Item 27

d Re-identify the pipe :

1 Pipe F2821070700000 Item (25)

becomes

1 Pipe F2821070700200 Item 25

e Install :

- Put in position the bonding leads items (19) and 27 on the restrictor

valve FIN 5506QA.

- Install the screw and the nut.

1 Screw Item (1)

1 Nut NSA5050-3 Item 3

NOTE(01) Item (1) was retained at removal.

NOTE(02) Apply the Chemical Conversion Coating Yellow Aluminum

(Mat. No. 13-002) and Polyurethane Primer (Mat. No.

16-001C) on the pipe Item 25 (Refer to Figure 32, Sheet 2).

4 Modify the feed pipes of the fuel canisters FIN 5600QA1 and FIN 5600QA2.

Refer to Figure 33

a Remove :

2 Screw Item (1) Retain

2 Washer Item (12) Retain

b On the blanking plates Item (118), do a stripping to a diameter of 14 mm

(0.551 in.) (Refer to Figure 33, Sheets 1 thru 4).

c Re-identify the blanking plates.

1 Plate A2821003820000 Item (118)

becomes

2 Plate A2821003820200 Item 118

d Install :

2 Screw Item (1)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 65

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A340

SERVICE BULLETIN

2 Washer Item (12)

2 Bonding-Lead E0088-10-250 Item 117

2 plate A2821003820200 Item 118

NOTE : Items (1) and (12) were retained at removal.

e Install the clamp with the bonding lead on the pipes Item (29) and Item (30).

Refer to Figure 33, Sheets 1 and 2

- Do a stripping on the pipes Item (29) and Item (30) to the dimensions

given in the Figure 33, Sheet 2.

- Install :

Refer to Figure 33, Sheets 1 and 2

2 Bolt NAS6603-2 Item 23

2 Nut NSA5050-3 Item 3

2 Clamp NSA5519-2B Item 26

2 Bonding-Lead E0088-10-63 Item 28

- Re-identify the pipe :

1 Pipe F2821003700000 Item (29)

becomes

1 Pipe F2821003700200 Item 29

1 Pipe F2821003700100 Item (30)

becomes

1 Pipe F2821003700300 Item 30

NOTE : Apply the Chemical Conversion Coating Yellow Aluminum

(Mat. No. 13-002) and Polyurethane Primer (Mat. No.

16-001C) on the pipes Item 29 and Item 30 (Refer to Figure

33, Sheet 2).

f Replace the supports Item (98).

Refer to Figure 33, Sheet 5

- Remove :

4 Rivet Item (35) Discard

2 Support F5791001800000 Item (98) Discard

- On the existing holes of the structure, do a stripping to a diameter of 10

mm (0.393 in.) (Refer to Figure 33, Sheet 5).

- Install :

1 Support F5791001800200 Item 98

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 66

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A340

SERVICE BULLETIN

1 Support F5791001800300 Item 99

with

4 Rivet ASNA2050DCJ3215 Item 35

. Put in position the bonding lead Item 28 on the support Items 98

and 99 and install :

2 Bolt NAS6603-2 Item 23

g Install the angles Item 84 on the structure between stiffener 27 and stiffener

28.

Refer to Figure 33, Sheets 1 thru 4

- Temporarily put in position the angles Item 84 on the structure at the

dimensions given on Figure 33, Sheets 2 and 3.

2 angle A2823301800500 Item 84

- Drill the structure to match the holes of the angle Item 84 to a diameter

between 3.25 mm (0.127 in.) min. and 3.35 mm (0.131 in.) max. dia.

(Refer to Figure 33, Sheet 3).

- Remove the angles.

- On the angles, do a stripping to a diameter of 10 mm (0.393 in.) (Refer

to Figure 33, Sheet 3).

- Deburr and clean the drilled area.

- On the opposite side of the structure, do a stripping to a diameter of 10

mm (0.393 in.) (Refer to Figure 33, Sheet 4).

- Install the angles :

2 Angle A2823301800500 Item 84

with

4 Rivet ASNA2050DCJ3215 Item 35

NOTE : Before installation of the angles, clean the surfaces with

Solvent (Mat. No. 11-026) and apply the Fuel Tank Sealant

Polysulfide (Mat. No. 09-002) between the structure and the

angles (Refer to Figure 33, Sheet 3).

- Put in position the bonding lead Item 117 on the angles Item 84 (Refer

to Figure 33, Sheet 2).

- Install the screw and the washer :

2 Bolt NAS6603-2 Item 23

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 67

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A340

SERVICE BULLETIN

2 Washer NAS1149D0316H Item 116

5 Modify the routing of the hydraulic pipe between FR42 and FR47.

Refer to Figure 34

a Remove :

2 Screw Item (33) Retain

2 Block clamp Item (34) Retain

4 Rivet Item (35) Discard

1 Support Item (36) Discard

1 Screw Item (37) Retain

1 Screw Item (38) Retain

1 Washer Item (39) Retain

1 Nut Item (3) Discard

1 Bonding-Lead Item (43) Retain

1 Nut Item (40) Discard

1 Clamp Item (44) Retain

b On the new support Item 36, do a stripping to a diameter of 12 mm (0.472

in.) and on the opposite side of the structure, do a stripping to a diameter of

12 mm (0.472 in.) (Refer to Figure 34, Sheet 2).

c Install :

2 Screw Item (33)

2 Block clamp Item (34)

1 Screw Item (37)

1 Screw Item (38)

1 Washer Item (39)

1 Bonding-Lead Item (43)

1 Clamp Item (44)

4 Rivet ASNA2050DCJ3215 Item 35

1 Support F5791036900100 Item 36

4 Screw NAS1096-3-8 Item 37

1 Screw NAS1096-3-9 Item 38

1 Washer NAS1149F0332P Item 39

5 Nut MS35650-302 Item 40

5 Nut NSA5050-3 Item 3

1 Clamp NSA5575-8A Item 41

3 Clamp NSA5575-11 Item 42

2 Bonding-Lead E0088-10-63 Item 28

2 Bonding-Lead E0088-10-80 Item 45

NOTE : Items (33), (34), (37), (38), (39), (43) and (44) were retained

at removal.

(7) Config. 01

Kit 284097C01R04

Trim Tank Bonding

(a) Do the electrical bonding of the structure and equipment as listed in Table 4.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 68

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A340

SERVICE BULLETIN

Table 4

AREA EQUIPMENT &

SYSTEM

ELECTRICAL

BONDING

METHOD

REF. FIGURE Kit No.

Rib 2-3 Water Drain Install the bonding

lead. Bond the pipe

clamp to the pipe.

Bond the bolt to the

structure.

Fig. 46, Sheet 1

and Sheet 2

C01R04

Under the Center

tank

Drainage Line Install the bonding

lead. Bond the pipe

clamp to the pipe.

Fig. 47, Sheet 1 C01R04

Rib 18-19 (RH) Ventilation Intake

System

Bond the contact

surfaces between

Elbow and Flame

arrestor. Bond two

of the unions of the

Elbow and Flame

arrestor.

Fig. 48, Sheet 1 None

(b) Do electrical bonding on Water Drain System.

Kit 284097C01R04

Refer to Figure 46.

1 Remove from its position the support showed in Figure 46 Sheet 2.

2 Screw Item (1) Retain

2 Washer Item (2) Retain

4 Rivet Item (3) Discard

2 Remove the surface protection of the water drain tube and the support in the

marked area (Refer to AMM 20-28-00).

3 Clean the holes of the support and the holes of the structure to eliminate surface

protection (Refer to AMM 20-28-00).

4 Install the support and the new bonding lead, Item 4.

4 Rivet MS20470AD5-10A Item 3

2 Bonding Lead F2818007601200 Item 4

2 Screw Item (1)

2 Washer Item (2)

2 Clamp NSA5519-4B Item 7

2 Screw NAS1096-1-7 Item 5

2 Washer NAS1149DN632K Item 6

2 Washer NAS1149DN616H Item 8

2 Nut MS21042-06 Item 9

5 Apply Fuel Tank Sealant Polysulfide (Mat. No. 09-001B) and varnish (Mat. No.

07-001D) over the electrical bonding (Refer to AMM 20-28-00).

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 69

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A340

SERVICE BULLETIN

(c) Do electrical bonding on Refuel-Defuel System (drainage line).

Kit 284097C01R04

Refer to Figure 47 , Sheet 1.

1 Remove the surface protection of the drainage line tubes in the marked area

(Refer to AMM 20-28-00).

2 Install the bonding leads, Item 12.

2 Bonding Lead F2828007500400 Item 12

3 Clamp NSA5519-4B Item 7

3 Screw NAS1096-1-7 Item 5

3 Washer NAS1149DN632K Item 6

3 Washer NAS1149DN616H Item 8

3 Nut MS21042-06 Item 9

3 Apply Fuel Tank Sealant Polysulfide (Mat. No. 09-001B) and varnish (Mat. No.

07-001D) over the electrical bonding (Refer to AMM 20-28-00).

(d) Do electrical bonding on Ventilation Intake System.

Refer to Figure 48, Sheet 1.

1 Remove the elbow from the flame arrestor.

4 Bolt Item (15) Retain

4 Washer Item (16) Retain

4 Nut Item (17) Retain

1 O-ring Item (18) Retain

2 Remove the surface protection on all the surface between the elbow and the

flame arrestor (Refer to AMM 20-28-00).

3 Remove the surface protection in the marked area of two of the four bolts,

Item 15 (Refer to AMM 20-28-00).

4 Install the elbow on the flame arrestor.

4 Bolt Item (15)

4 Washer Item (16)

4 Nut Item (17)

1 O-ring Item (18)

5 Apply Fuel Tank Sealant Polysulfide (Mat. No. 09-001B) and varnish (Mat. No.

07-001D) over the electrical bonding (Refer to AMM 20-28-00).

(8) Config. 02 thru Config. 03

Kit 284097C02R04

Trim Tank Bonding

(a) Do the electrical bonding of the structure and the equipment as listed in Table 5.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 70

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A340

SERVICE BULLETIN

Table 5

AREA EQUIPMENT &

SYSTEM

ELECTRICAL

BONDING

METHOD

REF. FIGURE Kit No.

Rib 2-3 Water Drain Install the bonding

lead. Bond the pipe

clamp to the pipe.

Bond the bolt to the

structure.

Fig. 46, Sheet 1

and Sheet 2

C02R04

Under the Center

tank

Drainage Line Install the bonding

lead. Bond the pipe

clamp to the pipe.

Fig. 47, Sheet 2 C02R04

Rib 18-19 (RH) Ventilation Intake

System

Bond the contact

surfaces between

Elbow and Flame

arrestor. Bond two

of the unions of the

Elbow and Flame

arrestor.

Fig. 48, Sheet 1 None

(b) Do electrical bonding on Water Drain System.

Kit 284097C02R04

Refer to Figure 46.

1 Remove from its position the support showed in Figure 46, Sheet 2.

2 Screw Item (1) Retain

2 Washer Item (2) Retain

4 Rivet Item (3) Discard

2 Remove the surface protection of the water drain tube and the support in the

marked area (Refer to AMM 20-28-00).

3 Clean the holes of the support and the holes of the structure to eliminate surface

protection (Refer to AMM 20-28-00).

4 Install the support and the new bonding lead, Item 4.

4 Rivet MS20470AD5-10A Item 3

2 Bonding Lead F2818007601200 Item 4

2 Screw Item (1)

2 Washer Item (2)

2 Clamp NSA5519-4B Item 7

2 Screw NAS1096-1-7 Item 5

2 Washer NAS1149DN632K Item 6

2 Washer NAS1149DN616H Item 8

2 Nut MS21042-06 Item 9

5 Apply Fuel Tank Sealant Polysulfide (Mat. No. 09-001B) and varnish (Mat. No.

07-001D) over the electrical bonding (Refer to AMM 20-28-00).

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 71

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A340

SERVICE BULLETIN

(c) Do electrical bonding on Refuel-Defuel System (drainage line).

Kit 284097C02R04

Refer to Figure 47, Sheet 2.

1 Remove the surface protection of the drainage line tubes in the marked area

(Refer to AMM 20-28-00).

2 Install the bonding leads, Items 12 and 13.

4 Bonding Lead F2828007500400 Item 12

1 Bonding Lead F2828007400600 Item 13

5 Clamp NSA5519-4B Item 7

1 Clamp NSA5519-2B Item 14

6 Screw NAS1096-1-7 Item 5

6 Washer NAS1149DN632K Item 6

6 Washer NAS1149DN616H Item 8

6 Nut MS21042-06 Item 9

3 Apply Fuel Tank Sealant Polysulfide (Mat. No. 09-001B) and varnish (Mat. No.

07-001D) over the electrical bonding (Refer to AMM 20-28-00).

(d) Do electrical bonding on Ventilation Intake System.

Refer to Figure 48, Sheet 1.

1 Remove the elbow from the flame arrestor.

4 Bolt Item (15) Retain

4 Washer Item (16) Retain

4 Nut Item (17) Retain

1 O-ring Item (18) Retain

2 Remove the surface protection on all the surface between the elbow and the

flame arrestor (Refer to AMM 20-28-00).

3 Remove the surface protection in the marked area of two of the four bolts,

Item (15) (Refer to AMM 20-28-00).

4 Install the elbow on the flame arrestor.

4 Bolt Item (15)

4 Washer Item (16)

4 Nut Item (17)

1 O-ring Item (18)

5 Apply Fuel Tank Sealant Polysulfide (Mat. No. 09-001B) and varnish (Mat. No.

07-001D) over the electrical bonding (Refer to AMM 20-28-00).

(9) Config. 05 ADDITIONAL WORK (Introduced at revision 03)

NOTE : This additional work, introduced by revision 03 and workstep (2)(a), is required

for aircraft modified by revision 03, 02, 01 or 00 on which Config. 01 or Config.

02 was valid. Workstep (2)(b) is required for aircraft modified by revision 03, 02,

01 or 00 on which Config. 01 , Config. 02 or Config. 03 was previously valid.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 72

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A340

SERVICE BULLETIN

(a) Kit 284097B08R00

Modify the Electrical Bonding of the Pump Canisters to the Pipe between Rib

Bay 2-3 and 3-4

Refer to Figure 44, Sheet 1

1 Remove:

8 Nut Item (5) Discard

4 Bolt Item (15) Discard

4 Bolt Item (16) Discard

8 Washer Item (17) Discard

2 Prepare for electrical bonding (Refer to AMM 20-28-00, Page block 201).

3 Install:

8 Nut NSA5474-3K7 Item 3

8 Nut NSA5474-4K7 Item 5

8 Lead-Bonding E0088-41-125 Item 6

8 Bolt NAS6603-2 Item 7

4 Bolt NAS6604-7 Item 15

4 Bolt NAS6604-8 Item 16

8 Washer-Flat NAS1149F0432P Item 17

8 Clamp AN742D4 Item 29

4 Do the Electrical Bonding Test (Refer to AMM 20-28-00, Page block 501).

5 Apply sealant to the fasteners and bare metal areas (Refer to AMM 20-28-00,

Page block 201).

(b) Kit 284097B08R00

Modify the Electrical Bonding to the Water Drain between Rib Bays 1-2 at Stringers

8-9 or Stringers 17-18

Refer to Figure 45, Sheet 3

NOTE : It will be necessary to do a check of the water drain valves at each

position to see which water drain valve was not modified by this Service

Bulletin at a previous issue.

1 Remove:

2 Nut Item (28) Discard

2 Bolt Item (32) Discard

2 Prepare for electrical bonding (Refer to AMM 20-28-00, Page block 201).

3 Install:

2 Bolt NAS6603-2 Item 7

2 Clamp AN742D6 Item 8

2 Nut NSA5050-4 Item 28

2 Nut NSA5050-3 Item 30

2 Bolt NAS1790-4R14 Item 32

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 73

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A340

SERVICE BULLETIN

2 Lead-Bonding E0088-41-160 Item 33

4 Do the Electrical Bonding Test (Refer to AMM 20-28-00, Page block 501).

5 Apply sealant to the fasteners and bare metal areas (Refer to AMM 20-28-00,

Page block 201).

(10) Config. 06 ADDITIONAL WORK (Introduced at revision 03)

NOTE : This additional work was introduced by revision 03 and is required for aircraft

modified by revision 03, 02, 01 or 00 on which Config. 01 , Config. 02 or

Config. 03 was previously valid.

(a) Kit 284097B09R00

Modify the Electrical Bonding to the Water Drain between Rib Bays 1-2 at Stringers

8-9 or Stringers 17-18

Refer to Figure 45, Sheet 3

NOTE : It will be necessary to do a check of the water drain valves at each

position to see which water drain valve was not modified by this Service

Bulletin at a previous issue.

1 Remove:

2 Nut Item (28) Discard

2 Bolt Item (32) Discard

2 Prepare for electrical bonding (Refer to AMM 20-28-00, Page block 201).

3 Install:

2 Bolt NAS6603-2 Item 7

2 Clamp AN742D6 Item 8

2 Nut NSA5050-4 Item 28

2 Nut NSA5050-3 Item 30

2 Bolt NAS1790-4R14 Item 32

2 Lead-Bonding E0088-41-160 Item 33

4 Do the Electrical Bonding Test (Refer to AMM 20-28-00, Page block 501).

5 Apply sealant to the fasteners and bare metal areas (Refer to AMM 20-28-00,

Page block 201).

(11) Config. 07 , ADDITIONAL WORK

NOTE : This additional work is introduced by revision 05 and is required for aircraft

modified by revision 04, 03, 02, 01 or 00 and on which Config. 04 was

previously valid.

(a) Modify or install the bonding points.

Refer to Figure 35

Refer to Figure 36

Refer to Figure 37

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 74

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A340

SERVICE BULLETIN

Refer to Figure 38

Refer to Kit 284097A04R00

1 Do the electrical bonding of the structure and the equipments as listed in Table 1.

Table 1

AREA EQUIPMENT AND

SYSTEM

ELECTRICAL

BONDING

METHOD

REF. FIGURE KIT No.

Between FR46 and

FR47 in the center

tank.

Fuel pipe. Install the bonding

lead. Bond the pipe

clamp to the pipe.

Fig. 35 A04R00

Between FR46 and

FR47 in the center

tank.

Restrictor valve

(5506QA).

Install the bonding

lead. Bond the pipe

clamp to the pipe.

Bond the screw to

the structure.

Fig. 36 A04R00

Between FR45 and

FR46 in the center

tank.

Pump canister. Install the bonding

lead. Bond the pipe

clamp to the pipe.

Bond the pump

canister to the

attachment fitting.

Fig. 37 A04R00

Between FR42 and

FR47 in the center

tank.

Hydraulic pipe

routing.

Bond the screw

to the structure.

Install the bonding

lead. Bond the pipe

clamp to the pipe.

Fig. 38 A04R00

2 Modify the pipe from the filling fuel between FR46 and FR47.

Refer to Figure 35

a Remove :

Refer to Figure 35, Sheet 1

1 screw Item (23) Retain

1 nut Item (3) Discard

- Disengage the bonding leads Item (19).

b On the rod Item (20), do a stripping to the dimensions given in the Figure 35,

Sheet 2

c On the rod Item (20), install :

Refer to Figure 35, Sheets 1 and 2

1 Clamp NSA5519-3B Item 21

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 75

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A340

SERVICE BULLETIN

1 Lead-Bonding E0088-10-125 Item 22

1 Bolt NAS6603-2 Item 23

1 Nut NSA5050-3 Item 3

d Re-identify the rod :

Refer to Figure 35, Sheet 1

1 Rod F2821019400000 Item (20)

becomes

1 Rod F2821019400200 Item 20

e On the pipe Item (137), do a stripping to a diameter of 14 mm (0.551 in.)

and on the opposite side, do a stripping to a diameter of 14 mm (0.551

in.) (Refer to Figure 35, Sheet 3).

f Install :

- Put in position the bonding leads Item (19) and Item 22 on the pipe Item

(137) (Refer to Figure 35, Sheet 1).

. Install the screw and the nut.

1 Screw Item (23)

1 Nut NSA5050-3 Item 3

NOTE(01) Item (23) was retained at removal.

NOTE(02) Apply the Chemical Conversion Coating Yellow Aluminum

(Mat. No. 13-002) and Polyurethane Primer (Mat. No.

16-001C) on the rod Item 20 (Refer to Figure 35, Sheets 1

and 2).

3 Modify the feed pipe between the restrictor valve FIN 5506QA and the pressure

switch FIN 53QU.

Refer to Figure 36

a Remove :

Refer to Figure 36, Sheet 2

1 Screw Item (1) Retain

1 Nut Item (3) Discard

- Disengage the bonding leads Item (19).

b On the pipe Item (25), do a stripping to the dimensions given in the Figure

36, Sheet 2.

c On the pipe Item (25) install :

1 Bolt NAS6603-2 Item 23

1 Nut NSA5050-3 Item 3

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 76

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A340

SERVICE BULLETIN

1 Clamp NSA5519-2B Item 26

1 Bonding-Lead E0088-10-190 Item 27

d Re-identify the pipe :

1 Pipe F2821070700000 Item (25)

becomes

1 Pipe F2821070700200 Item 25

e Install :

- Put in position the bonding leads items (19) and 27 on the restrictor

valve FIN 5506QA.

- Install the screw and the nut.

1 Screw Item (1)

1 Nut NSA5050-3 Item 3

NOTE(01) Item (1) was retained at removal.

NOTE(02) Apply the Chemical Conversion Coating Yellow Aluminum

(Mat. No. 13-002) and Polyurethane Primer (Mat. No.

16-001C) on the pipe Item 25 (Refer to Figure 36, Sheet 2).

4 Modify the feed pipes of the fuel canisters FIN 5600QA1 and FIN 5600QA2.

Refer to Figure 37

a Remove :

2 Screw Item (1) Retain

2 Washer Item (12) Retain

b On the blanking plates Item (118), do a stripping to a diameter of 14 mm

(0.551 in.) (Refer to Figure 37, Sheets 1 thru 4).

c Re-identify the blanking plates.

1 Plate A2821003820000 Item (118)

becomes

2 Plate A2821003820200 Item 118

d Install :

2 Screw Item (1)

2 Washer Item (12)

2 Bonding-Lead E0088-10-250 Item 117

2 plate A2821003820200 Item 118

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 77

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A340

SERVICE BULLETIN

NOTE : Items (1) and (12) were retained at removal.

e Install the clamp with the bonding lead on the pipes Item (29) and Item (30).

Refer to Figure 37, Sheets 1 and 2

- Do a stripping on the pipes Item (29) and Item (30) to the dimensions

given in the Figure 37, Sheet 2.

- Install :

Refer to Figure 37, Sheets 1 and 2

2 Bolt NAS6603-2 Item 23

2 Nut NSA5050-3 Item 3

2 Clamp NSA5519-2B Item 26

2 Bonding-Lead E0088-10-63 Item 28

- Re-identify the pipe :

1 Pipe F2821003700000 Item (29)

becomes

1 Pipe F2821003700200 Item 29

1 Pipe F2821003700100 Item (30)

becomes

1 Pipe F2821003700300 Item 30

NOTE : Apply the Chemical Conversion Coating Yellow Aluminum

(Mat. No. 13-002) and Polyurethane Primer (Mat. No.

16-001C) on the pipes Item 29 and Item 30 (Refer to Figure

37, Sheet 2).

f Replace the supports Item (98).

Refer to Figure 37, Sheet 5

- Remove :

4 Rivet Item (35) Discard

2 Support F5791001800000 Item (98) Discard

- On the existing holes of the structure, do a stripping to a diameter of 10

mm (0.393 in.) (Refer to Figure 37, Sheet 5).

- Install :

1 Support F5791001800200 Item 98

1 Support F5791001800300 Item 99

with

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SERVICE BULLETIN

4 Rivet ASNA2050DCJ3215 Item 35

. Put in position the bonding lead Item 28 on the support Items 98

and 99 and install :

2 Bolt NAS6603-2 Item 23

g Install the angles Item 84 on the structure between stiffener 27 and stiffener

28.

Refer to Figure 37, Sheets 1 thru 4

- Temporarily put in position the angles Item 84 on the structure at the

dimensions given on Figure 37, Sheets 2 and 3.

2 angle A2823301800500 Item 84

- Drill the structure to match the holes of the angle Item 84 to a diameter

between 3.25 mm (0.127 in.) min. and 3.35 mm (0.131 in.) max. dia.

(Refer to Figure 37, Sheet 3).

- Remove the angles.

- On the angles, do a stripping to a diameter of 10 mm (0.393 in.) (Refer

to Figure 37, Sheet 3).

- Deburr and clean the drilled area.

- On the opposite side of the structure, do a stripping to a diameter of 10

mm (0.393 in.) (Refer to Figure 37, Sheet 4).

- Install the angles :

2 Angle A2823301800500 Item 84

with

4 Rivet ASNA2050DCJ3215 Item 35

NOTE : Before installation of the angles, clean the surfaces with

Solvent (Mat. No. 11-026) and apply the Fuel Tank Sealant

Polysulfide (Mat. No. 09-002) between the structure and the

angles (Refer to Figure 37, Sheet 3).

- Put in position the bonding lead Item 117 on the angles Item 84 (Refer

to Figure 37, Sheet 2).

- Install the screw and the washer :

2 Bolt NAS6603-2 Item 23

2 Washer NAS1149D0316H Item 116

5 Modify the routing of the hydraulic pipe between FR42 and FR47.

Refer to Figure 38

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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SERVICE BULLETIN

a Remove :

2 Screw Item (33) Retain

2 Block clamp Item (34) Retain

4 Rivet Item (35) Discard

1 Support Item (36) Discard

1 Screw Item (37) Retain

1 Screw Item (38) Retain

1 Washer Item (39) Retain

1 Nut Item (3) Discard

1 Bonding-Lead Item (43) Retain

1 Nut Item (40) Discard

1 Clamp Item (44) Retain

b On the new support Item 36, do a stripping to a diameter of 12 mm (0.472

in.) and on the opposite side of the structure, do a stripping to a diameter of

12 mm (0.472 in.) (Refer to Figure 38, Sheet 2).

c Install :

2 Screw Item (33)

2 Block clamp Item (34)

1 Screw Item (37)

1 Screw Item (38)

1 Washer Item (39)

1 Bonding-Lead Item (43)

1 Clamp Item (44)

4 Rivet ASNA2050DCJ3215 Item 35

1 Support F5791036900100 Item 36

4 Screw NAS1096-3-8 Item 37

1 Screw NAS1096-3-9 Item 38

1 Washer NAS1149F0332P Item 39

5 Nut MS35650-302 Item 40

5 Nut NSA5050-3 Item 3

1 Clamp NSA5575-8A Item 41

3 Clamp NSA5575-11 Item 42

2 Bonding-Lead E0088-10-63 Item 28

2 Bonding-Lead E0088-10-80 Item 45

NOTE : Items (33), (34), (37), (38), (39), (43) and (44) were retained

at removal.

(b) Test

1 Preparation

a Check of the electrical bonding (for bonding points where bonding has

been reworked).

- Do the check of the electrical bonding of the fluid systems (Refer to

AMM 20-28-00, Page block 501).

NOTE : Fuel safety precautions required.

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- Close the access doors 147AZ and 148AZ and remove the safety clips

and tags and close the circuit breakers as specified after the installation of

the covers 147AZ and 148AZ (Refer to AMM 57-17-11, Page block 401).

2 Test

a Do the test after the installation of the access doors 147AZ and 148AZ

(Refer to AMM 57-17-11, Page block 401).

(c) Close-up

1 Refuel the center fuel tank (Refer to AMM 28-25-00, Page block 301).

NOTE : Do a fuel leak check at the work areas (Refer to AMM 28-11-00,

Page block 601).

2 Close the MLG doors (Refer to AMM 32-12-00, Page block 201).

3 Remove the access platforms.

4 Restore the systems and the aircraft to normal operating conditions.

(12) Config. 02 , Config. 03 ADDITIONAL WORK

NOTE : This ADDITIONAL WORK is only applicable to operators who have already

embodied the Revision 03 or any previous revision of this Service Bulletin

and their operator records confirm that the electrical bonding of the Water

Drain System and electrical bonding of the Ventilation Intake System were

not completed.

WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND 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 THE SAFETY AREA, DO

NOT: - SMOKE - MAKE SPARKS OR FIRE - USE ANY EQUIPMENT THAT

IS NOT APPROVED FOR REFUEL/DEFUEL PROCEDURES.

CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE).WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL

WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS

POSSIBLE. TO DO THIS:

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

NECESSARY ON WIRING AND COMPONENTS

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF

CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING

INSTALLATION

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

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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SERVICE BULLETIN

(a) Do electrical bonding on Water Drain System and on Ventilation Intake System.

Kit 284097C02S01

Refer to figure 46

Refer to figure 48

1 Preparation

a Install access platforms to gain access to zone 319 and zone 346.

b Open the access panel 312AR.

c Defuel the THS trim tank. (Refer to AMM 28-25-00, Page block 301).

d Put the warning notices in position:

- On the HYD/FUEL control panel 245VU, to tell persons not to refuel

the aircraft.

- On the refuel/defuel control panel 990VU, to tell persons not to refuel

the aircraft.

e Trim the horizontal tail plane back to the full up position. (Refer to AMM

27-40-00).

f Open the access panel 319DR and 319BL. (Refer to AMM 55-11-14,

Page block 401).

g Remove the trim tank transfer pump housing. (Refer to AMM 28-27-56,

Page block 401).

h Open the NACA vent intake panel 346AB. (Refer to AMM 28-12-48,

Page block 401).

2 Standard Practices

a For information on tightening torques for standard threaded fasteners. (Refer

to AMM 20-21-11, Page block 201).

b For information on electrical bonding. (Refer to AMM 20-28-00, Page

block 201).

c Clean the work area with cleaning agent (Mat. No. 11-010).

d For material specification given in this Service Bulletin refer to CML.

3 Modification

a Do the electrical bonding of the structure and the equipment as listed in

Table 1.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 82

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Table 1

AREA EQUIPMENT &

SYSTEM

ELECTRICAL

BONDING

METHOD

Figure Kit No

Rib 2-3 Water Drain Install the bonding

lead. Bond the pipe

clamp to the pipe.

Bond the bolt to the

structure.

Refer to figure 46,

Sheet 1 and Sheet

2

C02S01

Rib 18-19 (RH) Ventilation Intake

System

Bond the contact

surfaces between

Elbow and Flame

arrestor. Bond two

of the unions of the

Elbow and Flame

arrestor.

Refer to figure 48,

Sheet 1

None

b Do electrical bonding on Water Drain System.

Refer to figure 46.

- Remove from its position the support showed in figure 46 Sheet 2.

2 screw Item (1) Retain

2 washer Item (2) Retain

4 rivet Item (3) Discard

- Remove the surface protection of the water drain tube and the support

in the marked area (Refer to AMM 20-28-00).

- Clean the holes of the support and the holes of the structure to eliminate

surface protection (Refer to AMM 20-28-00).

- Install the support and the new bonding lead item 4.

4 rivet MS20470AD5-10A Item 3

2 bonding lead F2818007601200 Item 4

2 screw Item (1)

2 washer Item (2)

2 clamp NSA5519-4B Item 7

2 screw NAS1096-1-7 Item 5

2 washer NAS1149DN632K Item 6

2 washer NAS1149DN616H Item 8

2 nut MS21042-06 Item 9

- Apply Sealant (Mat. No. 09-001) and varnish (Mat. No. 07-001D) over

the electrical bonding (Refer to AMM 20-28-00).

c Do electrical bonding on Ventilation Intake System.

Refer to figure 48 Sheet 1.

- Remove the elbow from the flame arrestor.

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4 bolt Item (15) Retain

4 washer Item (16) Retain

4 nut Item (17) Retain

1 O-ring Item (18) Retain

- Remove the surface protection on all the surface between the elbow and

the flame arrestor (Refer to AMM 20-28-00).

- Remove the surface protection in the marked area of two of the four bolts

item 15 (Refer to AMM 20-28-00).

- Install the elbow on the flame arrestor.

4 bolt Item (15)

4 washer Item (16)

4 nut Item (17)

1 O-ring Item (18)

- Apply Sealant (Mat. No. 09-001) and varnish (Mat. No. 07-001D) over

the electrical bonding (Refer to AMM 20-28-00).

4 Test

a Make a fuel leak test of the THS Trim Tank (Refer to AMM 28-11-00).

b All new bonding leads are to be tested in accordance with AMM 20-28-00,

Page block 501).

5 Close-up

a Make certain that the work areas are clean of tools and miscellaneous

items of equipment.

b Close the NACA vent intake panel. (Refer to AMM 28-12-48, Page block

401).

c Install the trim tank transfer pump housing. (Refer to AMM 28-27-56,

Page block 401).

d Close the access panels 319DR and 319BL. (Refer to AMM 55-11-14,

Page block 401).

e Remove the warning notices.

f Close the access panel 312AR.

g Remove the access platforms.

6 Documentation

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

this Service Bulletin.

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C. TEST

(1) Config. 04 Only

(a) Preparation

1 Check of the electrical bonding (for bonding points modified).

a Do the check of the electrical bonding of the fluid systems (Refer to AMM

20-28-00, Page block 501).

NOTE : Fuel safety precautions are necessary.

2 Close the access doors 147AZ and 148AZ and remove the safety clips and tags

and close the circuit breakers as specified after the installation of the covers

147AZ and 148AZ (Refer to AMM 57-17-11, Page block 401).

(b) Test

1 Do the test after the removal/installation of the access doors 147AZ and 148AZ

(Refer to AMM 57-17-11, Page block 401).

(2) Config. 01 thru Config. 03

(a) Preparation

1 Check of the electrical bonding (for bonding points where bonding has been

reworked).

a Do the check of the electrical bonding of the fluid systems (Refer to AMM

20-28-00, Page block 501).

NOTE : Fuel safety precautions are necessary.

2 Close the access doors 147AZ and 148AZ and remove the safety clips and tags

and close the circuit breakers as specified after the installation of the covers

147AZ and 148AZ (Refer to AMM 57-17-11, Page block 401).

3 Close the collector cell, center spar and rib9 access panels 541AZ, 541BZ,

641AZ and 641BZ (Refer to AMM 57-27-11, Page block 401).

4 Close the under wing tank access panels 541AB and 641AB and remove

the safety clips and tags and close the circuit breakers as specified after the

installation of the under wing tank access panels 541AB and 641AB (Refer

to AMM 57-27-11, Page block 401).

5 Remove the safety clips and tags and close the circuit breakers as specified

after the installation of the belly fairing access panels 191KB and 192PB (Refer

to AMM 53-35-13, Page block 401).

6 Remove the safety clips and tags and close the circuit breakers as specified

after the installation of the passenger seats, if removed (Refer to AMM 25-21-41,

Page block 401).

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7 Remove the safety clips and tags and close the circuit breakers as specified

after the installation of the center tank harnesses 91QT and 92QT, if installed

(Refer to AMM 28-42-44, Page block 401).

(b) Test

1 If electrical harness 91QT and 92QT are installed and if necessary:

a Do the test after the removal/installation of the access doors 147AZ and

148AZ (Refer to AMM 57-17-11, Page block 401).

b If removed, do the test after installation of the passenger seat (Refer to

AMM 25-21-41, Page block 401).

c Do the test after removal/installation of the center tank harnesses (91QT

and 92QT) (Refer to AMM 28-42-44, Page block 401).

d Do the test after installation of the under wing tank access panels 541AB

and 641AB (Refer to AMM 57-27-11, Page block 401).

e Do the test after installation of the collector cell, center spar and RIB9

access panels 541AZ, 541BZ, 641AZ and 641BZ (Refer to AMM 57-27-11,

Page block 401).

2 If electrical harness 91QT and 92QT are not installed :

a Do the test after the removal/installation of the access doors 147AZ and

148AZ (Refer to AMM 57-17-11, Page block 401).

b Do the check of the electrical bonding of the fluid systems (Refer to AMM

20-28-00, Page block 501).

c Do the test after removal/installation of the access panels 541AB, 541AZ,

541BZ, 641AB, 641AZ and 641BZ (Refer to AMM 57-27-11, Page block 401).

(c) Install the access panels 191KB and 192PB (Refer to AMM 53-35-14, Page block

401).

(d) Refuel the aircraft (Refer to AMM 12-11-28, Page block 301).

(e) Do a fuel leak check at the work areas (Refer to AMM 28-11-00, Page block 601).

(3) Config. 07

(a) Preparation

1 Check of the electrical bonding (for bonding points where bonding has been

reworked).

a Do the check of the electrical bonding of the fluid systems (Refer to AMM

20-28-00, Page block 501).

NOTE : Fuel safety precautions required.

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2 Close the access doors 147AZ and 148AZ and remove the safety clips and tags

and close the circuit breakers as specified after the installation of the covers

147AZ and 148AZ (Refer to AMM 57-17-11, Page block 401).

(b) Test

1 Do the test after the installation of the access doors 147AZ and 148AZ (Refer

to AMM 57-17-11, Page block 401).

(4) Config. 05 ADDITIONAL WORK (Introduced at revision 03)

(a) Preparation

1 Check of the electrical bonding (for bonding points modified).

a Do the check of the electrical bonding of the fluid systems (Refer to AMM

20-28-00, Page block 501).

NOTE : Fuel safety precautions are necessary.

2 Close the access panels 541AB(641AB), 541BB(641BB), 541AZ(641AZ) and

541CZ(641CZ) (Refer to AMM 57-27-11, Page block 401).

3 Do the test after removal/installation the access panels 541AB(641AB),

541BB(641BB), 541AZ(641AZ) and 541CZ(641CZ) (Refer to AMM 57-27-11,

Page block 401).

(b) Refuel the aircraft (Refer to AMM 12-11-28, Page block 301).

(c) Do a fuel leak check at the work areas (Refer to AMM 28-11-00, Page block 601).

(5) Config. 06 ADDITIONAL WORK (Introduced at revision 03)

(a) Preparation

1 Check of the electrical bonding (for bonding points modified).

a Do the check of the electrical bonding of the fluid systems (Refer to AMM

20-28-00, Page block 501).

NOTE : Fuel safety precautions are necessary.

2 Close the access panels 541AB(641AB) and 541AZ(641AZ) (Refer to AMM

57-27-11, Page block 401).

3 Do the test after removal/installation the access panels 541AB(641AB) and

541AZ(641AZ) (Refer to AMM 57-27-11, Page block 401).

(b) Refuel the aircraft (Refer to AMM 12-11-28, Page block 301).

(c) Do a fuel leak check at the work areas (Refer to AMM 28-11-00, Page block 601).

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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D. CLOSE UP

(1) Config. 04 Only

(a) Refuel the center fuel tank (Refer to AMM 28-25-00, Page block 301).

NOTE : Do a fuel leak check at the work areas (Refer to AMM 28-11-00, Page

block 601).

(b) Close the MLG doors (Refer to AMM 32-12-00, Page block 201).

(c) Remove the access platforms.

(d) Restore the systems and the aircraft to normal operating conditions.

(2) Config. 01 thru Config. 03

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the flap track fairings 534AB (634AB) and 534CB (634CB) (Refer to AMM

57-56-11, Page block 401).

(c) Engage the insulation on the FR47 (Refer to AMM 25-80-00, Page block 001).

(d) Install the floor panel 251WF between FR40 and FR42 (Refer to AMM 53-00-00,

Page block 201) (If necessary).

(e) Install the panels 251WW and 252WW (Refer to AMM 06-41-53, Page block 001)

(If necessary).

(f) Install the passenger seat between FR40 and FR40.2 (Refer to AMM 25-21-41,

Page block 401).

(g) Close the MLG doors (Refer to AMM 32-12-00, Page block 201).

(h) Close the NACA vent intake panel (Refer to AMM 28-12-48, Page block 401).

(i) If removed, install the trim tank transfer-pump housing (Refer to AMM 28-27-56,

Page block 401).

(j) Close these access panels:

- Config. 01 ; 319BR and 319BL (Refer to AMM 55-11-14, Page block 401)

- Config. 02 thru Config. 03 ; 319DR and 319BL (Refer to AMM 55-11-14, Page

block 401)

(k) Close the access door 312AR.

(l) Close all the access panels.

(m) Remove the warning notices.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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(n) Remove the access platforms.

(o) Disconnect the aircraft electrical ground-connection (Refer to AMM 12-34-24, Page

block 201).

(p) Restore the systems and the aircraft to normal operating conditions.

(3) Config. 07

(a) Refuel the center fuel tank (Refer to AMM 28-25-00, Page block 301).

NOTE : Do a fuel leak check at the work areas (Refer to AMM 28-11-00, Page

block 601).

(b) Close the MLG doors (Refer to AMM 32-12-00, Page block 201).

(c) Remove the access platforms.

(d) Restore the systems and the aircraft to normal operating conditions.

(4) Config. 05 thru Config. 06 ADDITIONAL WORK (Introduced at revision 03)

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Remove the warning notices.

(c) Remove the access platforms.

(d) Disconnect the aircraft electrical ground-connection (Refer to AMM 12-34-24, Page

block 201).

(e) Restore the systems and the aircraft to normal operating conditions.

(5) Config. 07 ADDITIONAL WORK

(a) Refuel the center fuel tank (Refer to AMM 28-25-00, Page block 301).

NOTE : Do a fuel leak check at the work areas (Refer to AMM 28-11-00, Page

block 601).

(b) Close the MLG doors (Refer to AMM 32-12-00, Page block 201).

(c) Remove the access platforms.

(d) Restore the systems and the aircraft to normal operating conditions.

E. DOCUMENTATION

Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 89

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A340

SERVICE BULLETIN

Figure 1, Sheet 1

Config. 04 : Decomposition of the Center Tank

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REVISION No. : 05 - Jun 03/10 Page : 90

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A340

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Figure 2, Sheet 1

Config. 04 : Location of the Bonding Points at FR42 (View Looking FWD)

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REVISION No. : 05 - Jun 03/10 Page : 91

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A340

SERVICE BULLETIN

Figure 2, Sheet 2

Config. 04 : Location of the Bonding Points at FR42 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 92

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SERVICE BULLETIN

Figure 3, Sheet 1

Config. 01 : Bonding Points to Check at FR42 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 93

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A340

SERVICE BULLETIN

Figure 4, Sheet 1

Config. 02 : Decomposition of the Center Tank DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 94

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A340

SERVICE BULLETIN

Figure 5, Sheet 1

Config. 01 thru 03 : Location of the Bonding Points at RH Rib 1 (View Looking Inside)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 95

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A340

SERVICE BULLETIN

Figure 5, Sheet 2

Config. 01 thru 03 : Location of the Bonding Points at RH Rib 1 (View Looking Inside)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 96

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A340

SERVICE BULLETIN

Figure 5, Sheet 3

Config. 01 thru 03 : Location of the Bonding Points at RH Rib 1 (View Looking Inside)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 97

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A340

SERVICE BULLETIN

Figure 5, Sheet 4

Config. 01 thru 03 : Location of the Bonding Points at RH Rib 1 (View Looking Inside)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 98

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A340

SERVICE BULLETIN

Figure 5, Sheet 5

Config. 01 thru 03 : Location of the Bonding Points at RH Rib 1 (View Looking Inside)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 99

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A340

SERVICE BULLETIN

Figure 6, Sheet 1

Config. 01 thru 03 : Bonding Points to Check at RH Rib 1 (View Looking Inside)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 100

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A340

SERVICE BULLETIN

Figure 7, Sheet 1

Config. 01 thru 03 : Location of the Bonding Points at RH Rib 1 (View Looking Right)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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SERVICE BULLETIN

Figure 7, Sheet 2

Config. 01 thru 03 : Location of the Bonding Points at RH Rib 1 (View Looking Right)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

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SERVICE BULLETIN

Figure 7, Sheet 3

Config. 01 thru 03 : Location of the Bonding Points at RH Rib 1 (View Looking Right)

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REVISION No. : 05 - Jun 03/10 Page : 103

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Figure 7, Sheet 4

Config. 01 thru 03 : Location of the Bonding Points at RH Rib 1 (View Looking Right)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 104

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 8, Sheet 1

Config. 01 thru 03 : Bonding Points to Check at RH Rib 1 (View Looking Right)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 105

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 9, Sheet 1

Config. 01 thru 03: Location of the Bonding Points on the Lower Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 106

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 9, Sheet 2

Config. 01 thru 03: Location of the Bonding Points on the Lower Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 107

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 9, Sheet 3

Config. 01 thru 03: Location of the Bonding Points on the Lower Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 108

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 9, Sheet 4

Config. 01 thru 03: Location of the Bonding Points on the Lower Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 109

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 9, Sheet 5

Config. 01 thru 03: Location of the Bonding Points on the Lower Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 110

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 9, Sheet 6

Config. 01 thru 03: Location of the Bonding Points on the Lower Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 111

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 9, Sheet 7

Config. 01 thru 03: Location of the Bonding Points on the Lower Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 112

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 9, Sheet 8

Config. 01 thru 03: Location of the Bonding Points on the Lower Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 113

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 9, Sheet 9

Config. 01 thru 03: Location of the Bonding Points on the Lower Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 114

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 10, Sheet 1

Config. 01 thru 03 : Bonding Points to Check on the Lower Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 115

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 11, Sheet 1

Config. 02 : Location of the Bonding Points on the Upper Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 116

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 11, Sheet 2

Config. 02 : Location of the Bonding Points on the Upper Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 117

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 11, Sheet 3

Config. 02 : Location of the Bonding Points on the Upper Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 118

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 11, Sheet 4

Config. 02 : Location of the Bonding Points on the Upper Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 119

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 11, Sheet 5

Config. 02 : Location of the Bonding Points on the Upper Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 120

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 11, Sheet 6

Config. 02 : Location of the Bonding Points on the Upper Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 121

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 11, Sheet 7

Config. 02 : Location of the Bonding Points on the Upper Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 122

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 11, Sheet 8

Config. 02 : Location of the Bonding Points on the Upper Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 123

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 12, Sheet 1

Config. 01 thru 03 : Bonding Points to Check on the Upper Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 124

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 12, Sheet 2

Config. 01 thru 03 : Bonding Points to Check on the Upper Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 125

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 12, Sheet 3

Config. 01 thru 03 : Bonding Points to Check on the Upper Panel

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 126

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 13, Sheet 1

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking FWD) DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 127

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 13, Sheet 2

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 128

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 13, Sheet 3

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 129

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 13, Sheet 4

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 130

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 13, Sheet 5

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 131

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 13, Sheet 6

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 132

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 13, Sheet 7

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 133

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 13, Sheet 8

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 134

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 13, Sheet 9

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 135

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 13, Sheet 10

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 136

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 13, Sheet 11

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 137

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 13, Sheet 12

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 138

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 13, Sheet 13

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 139

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 14, Sheet 1

Config. 01 thru 03 : Bonding Points to Check at FR47 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 140

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 14, Sheet 2

Config. 01 thru 03 : Bonding Points to Check at FR47 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 141

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 15, Sheet 1

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking Aft)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 142

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 15, Sheet 2

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking Aft)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 143

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 15, Sheet 3

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking Aft)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 144

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 15, Sheet 4

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking Aft)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 145

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 15, Sheet 5

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking Aft)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 146

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 15, Sheet 6

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking Aft)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 147

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 15, Sheet 7

Config. 01 thru 03: Location of the Bonding Points at FR47 (View Looking Aft)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 148

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 16, Sheet 1

Config. 01 thru 03 : Bonding Points to Check at FR47 (View Looking Aft)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 149

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 17, Sheet 1

Config. 01 thru 03: Location of the Bonding Points at LH Rib 1 (View Looking Inside)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 150

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 17, Sheet 2

Config. 01 thru 03: Location of the Bonding Points at LH Rib 1 (View Looking Inside)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 151

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 17, Sheet 3

Config. 01 thru 03: Location of the Bonding Points at LH Rib 1 (View Looking Inside)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 152

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 17, Sheet 4

Config. 01 thru 03: Location of the Bonding Points at LH Rib 1 (View Looking Inside)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 153

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 17, Sheet 5

Config. 01 thru 03: Location of the Bonding Points at LH Rib 1 (View Looking Inside)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 154

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 17, Sheet 6

Config. 01 thru 03: Location of the Bonding Points at LH Rib 1 (View Looking Inside)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 155

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 18, Sheet 1

Config. 01 thru 03 : Bonding Points to Check at LH Rib 1 (View Looking Inside)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 156

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 19, Sheet 1

Config. 01 thru 03: Location of the Bonding Points at FR42 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 157

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 19, Sheet 2

Config. 01 thru 03: Location of the Bonding Points at FR42 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 158

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 20, Sheet 1

Config. 01 thru 03 : Bonding Points to Check at FR42 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 159

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 21, Sheet 1

Config. 01 thru 03: Modification of the Pipe from Filling Fuel Between FR46 and FR47, Kit 284097A01R06

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 160

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 21, Sheet 2

Config. 01 thru 03: Modification of the Pipe from Filling Fuel Between FR46 and FR47, Kit 284097A01R06

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 161

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 21, Sheet 3

Config. 01 thru 03: Modification of the Pipe from Filling Fuel Between FR46 and FR47, Kit 284097A01R06

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 162

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 22, Sheet 1

Config. 01 thru 03: Modification of the Feed Pipe Between the Restrictor Valve FIN 5506QA and the Pressure

Switch FIN 53QU, Kit 284097A01R06 DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 163

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 22, Sheet 2

Config. 01 thru 03: Modification of the Feed Pipe Between the Restrictor Valve FIN 5506QA and the Pressure

Switch FIN 53QU, Kit 284097A01R06 DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 164

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 23, Sheet 1

Config. 01 thru 03: Modification of the Feed Pipes of the Fuel Canisters FIN 5600QA1 and FIN 5600QA2, Kit

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097 284097A01R06

REVISION No. : 05 - Jun 03/10 Page : 165

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 23, Sheet 2

Config. 01 thru 03: Modification of the Feed Pipes of the Fuel Canisters FIN 5600QA1 and FIN 5600QA2, Kit

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097 284097A01R06

REVISION No. : 05 - Jun 03/10 Page : 166

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 23, Sheet 3

Config. 01 thru 03: Modification of the Feed Pipes of the Fuel Canisters FIN 5600QA1 and FIN 5600QA2, Kit

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097 284097A01R06

REVISION No. : 05 - Jun 03/10 Page : 167

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 23, Sheet 4

Config. 01 thru 03: Modification of the Feed Pipes of the Fuel Canisters FIN 5600QA1 and FIN 5600QA2, Kit

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097 284097A01R06

REVISION No. : 05 - Jun 03/10 Page : 168

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 23, Sheet 5

Config. 01 thru 03: Modification of the Feed Pipes of the Fuel Canisters FIN 5600QA1 and FIN 5600QA2, Kit

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097 284097A01R06

REVISION No. : 05 - Jun 03/10 Page : 169

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 24, Sheet 1

Config. 01 thru 03: Modification of the Routing of the Hydraulic Pipe, between FR42 and FR47, Kit

284097A01R06

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 170

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 24, Sheet 2

Config. 01 thru 03: Modification of the Routing of the Hydraulic Pipe, between FR42 and FR47, Kit

284097A01R06

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 171

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 24, Sheet 3

Config. 01 thru 03: Modification of the Routing of the Hydraulic Pipe, between FR42 and FR47, Kit

284097A01R06

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 172

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 25, Sheet 1

Config. 01 thru 03: Modification of the Pipe of the ACT Plumbing Fuel System, Kit 284097A01R06

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 173

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 25, Sheet 2

Config. 01 thru 03: Modification of the Pipe of the ACT Plumbing Fuel System, Kit 284097A01R06

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 174

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 26, Sheet 1

Config. 01 thru 03: Modification of the Pipe of the Plumbing Refuel System Between FR46 and FR47, Kit

284097A01R06

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 175

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 26, Sheet 2

Config. 01 thru 03: Modification of the Pipe of the Plumbing Refuel System Between FR46 and FR47, Kit

284097A01R06

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 176

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 26, Sheet 3

Config. 01 thru 03: Modification of the Pipe of the Plumbing Refuel System Between FR46 and FR47, Kit

284097A01R06

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 177

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 27, Sheet 1

Config. 01 thru 03: Modification of the supports and the Angles on the Rib 1, RH Side, Between FR45

and FR46, Kit 284097A01R06

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 178

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 27, Sheet 2

Config. 01 thru 03: Modification of the supports and the Angles on the Rib 1, RH Side, Between FR45

and FR46, Kit 284097A01R06

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 179

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 28, Sheet 1

Config. 07 : Decomposition of the Center Tank

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 180

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 29, Sheet 1

Config. 07 : Location of the Bonding Points at FR42 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 181

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 29, Sheet 2

Config. 07 : Location of the Bonding Points at FR42 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 182

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 30, Sheet 1

Config. 07 : Bonding Points to Check at FR42 (View Looking FWD)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 183

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 31, Sheet 1

Config. 07 : Modification of the Pipe from Filling Fuel Between FR46 and FR47

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 184

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 31, Sheet 2

Config. 07 : Modification of the Pipe from Filling Fuel Between FR46 and FR47

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 185

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 31, Sheet 3

Config. 07 : Modification of the Pipe from Filling Fuel Between FR46 and FR47

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 186

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 32, Sheet 1

Config. 07 : Modification of the Feed Pipe Between the Restrictor Valve FIN 5506QA and the Pressure

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097 Switch FIN 53QU

REVISION No. : 05 - Jun 03/10 Page : 187

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 32, Sheet 2

Config. 07 : Modification of the Feed Pipe Between the Restrictor Valve FIN 5506QA and the Pressure

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097 Switch FIN 53QU

REVISION No. : 05 - Jun 03/10 Page : 188

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 33, Sheet 1

Config. 07 : Modification of the Feed Pipes of the Fuel Canisters FIN 5600QA1 and FIN 5600QA2

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 189

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 33, Sheet 2

Config. 07 : Modification of the Feed Pipes of the Fuel Canisters FIN 5600QA1 and FIN 5600QA2

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 190

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 33, Sheet 3

Config. 07 : Modification of the Feed Pipes of the Fuel Canisters FIN 5600QA1 and FIN 5600QA2

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 191

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 33, Sheet 4

Config. 07 : Modification of the Feed Pipes of the Fuel Canisters FIN 5600QA1 and FIN 5600QA2

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 192

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 33, Sheet 5

Config. 07 : Modification of the Feed Pipes of the Fuel Canisters FIN 5600QA1 and FIN 5600QA2

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 193

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 34, Sheet 1

Config. 07 : Modification of the Routing of the Hydraulic Pipe, between FR42 and FR47

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 194

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 34, Sheet 2

Config. 07 : Modification of the Routing of the Hydraulic Pipe, between FR42 and FR47

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 195

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 34, Sheet 3

Config. 07 : Modification of the Routing of the Hydraulic Pipe, between FR42 and FR47

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 196

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 35, Sheet 1

Config. 07 : ADDITIONAL WORK, Modification of the Pipe from Filling Fuel Between FR46 and FR47

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 197

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 35, Sheet 2

Config. 07 : ADDITIONAL WORK, Modification of the Pipe from Filling Fuel Between FR46 and FR47

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 198

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 35, Sheet 3

Config. 07 : ADDITIONAL WORK, Modification of the Pipe from Filling Fuel Between FR46 and FR47

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 199

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 36, Sheet 1

Config. 07 : ADDITIONAL WORK, Modification of the Feed Pipe Between the Restrictor Valve FIN 5506QA

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097 and the Pressure Switch FIN 53QU

REVISION No. : 05 - Jun 03/10 Page : 200

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 36, Sheet 2

Config. 07 : ADDITIONAL WORK, Modification of the Feed Pipe Between the Restrictor Valve FIN 5506QA

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097 and the Pressure Switch FIN 53QU

REVISION No. : 05 - Jun 03/10 Page : 201

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 37, Sheet 1

Config. 07 : ADDITIONAL WORK, Modification of the Feed Pipes of the Fuel Canisters FIN 5600QA1

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097 and FIN 5600QA2

REVISION No. : 05 - Jun 03/10 Page : 202

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 37, Sheet 2

Config. 07 : ADDITIONAL WORK, Modification of the Feed Pipes of the Fuel Canisters FIN 5600QA1

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097 and FIN 5600QA2

REVISION No. : 05 - Jun 03/10 Page : 203

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 37, Sheet 3

Config. 07 : ADDITIONAL WORK, Modification of the Feed Pipes of the Fuel Canisters FIN 5600QA1

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097 and FIN 5600QA2

REVISION No. : 05 - Jun 03/10 Page : 204

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 37, Sheet 4

Config. 07 : ADDITIONAL WORK, Modification of the Feed Pipes of the Fuel Canisters FIN 5600QA1

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097 and FIN 5600QA2

REVISION No. : 05 - Jun 03/10 Page : 205

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 37, Sheet 5

Config. 07 : ADDITIONAL WORK, Modification of the Feed Pipes of the Fuel Canisters FIN 5600QA1

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097 and FIN 5600QA2

REVISION No. : 05 - Jun 03/10 Page : 206

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 38, Sheet 1

Config. 07 : ADDITIONAL WORK, Modification of the Routing of the Hydraulic Pipe, between FR42 and FR47

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 207

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 38, Sheet 2

Config. 07 : ADDITIONAL WORK, Modification of the Routing of the Hydraulic Pipe, between FR42 and FR47

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 208

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 38, Sheet 3

Config. 07 : ADDITIONAL WORK, Modification of the Routing of the Hydraulic Pipe, between FR42 and FR47

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 209

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 39, Sheet 1

Config. 01 thru 03: Electrical Bonding of the Wing Skin Panels (Rib Attachment Holes Omitted)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 210

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 39, Sheet 2

Config. 01 thru 03: Electrical Bonding of the Wing Skin Panels (Rib Attachment Holes Omitted)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 211

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 39, Sheet 3

Config. 01 thru 03: Electrical Bonding of the Wing Skin Panels (Rib Attachment Holes Omitted)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 212

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 39, Sheet 4

Config. 01 thru 03: Electrical Bonding of the Wing Skin Panels (Rib Attachment Holes Omitted)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 213

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 39, Sheet 5

Config. 01 thru 03: Electrical Bonding of the Wing Skin Panels (Rib Attachment Holes Omitted)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 214

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 39, Sheet 6

Config. 01 thru 03: Electrical Bonding of the Wing Skin Panels (Rib Attachment Holes Omitted)

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 215

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 40, Sheet 1

Config. 01 thru 03: Electrical Bonding of the Equipment in the Inner Fuel Tanks

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 216

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 40, Sheet 2

Config. 01 thru 03: Electrical Bonding of the Equipment in the Inner Fuel Tanks

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 217

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 40, Sheet 3

Config. 01 thru 03: Electrical Bonding of the Equipment in the Inner Fuel Tanks

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 218

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 40, Sheet 4

Config. 01 thru 03: Electrical Bonding of the Equipment in the Inner Fuel Tanks

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 219

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 40, Sheet 5

Config. 01 thru 03: Electrical Bonding of the Equipment in the Inner Fuel Tanks

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 220

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 40, Sheet 6

Config. 01 thru 03: Electrical Bonding of the Equipment in the Inner Fuel Tanks

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 221

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 41, Sheet 1

Config. 01 thru 03: Electrical Bonding of the Water Drains

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 222

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 41, Sheet 2

Config. 01 thru 03: Electrical Bonding of the Water Drains

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 223

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 41, Sheet 3

Config. 01 thru 03: Electrical Bonding of the Water Drains

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 224

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 41, Sheet 4

Config. 01 thru 03: Electrical Bonding of the Water Drains

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 225

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 41, Sheet 5

Config. 01 thru 03: Electrical Bonding of the Water Drains

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 226

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 42, Sheet 1

Config. 01 thru 03: Electrical Bonding of the Water Drains

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 227

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 42, Sheet 2

Config. 01 thru 03: Electrical Bonding of the Water Drains

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 228

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 42, Sheet 3

Config. 01 thru 03: Electrical Bonding of the Water Drains

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 229

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 43, Sheet 1

Config. 01 thru 03: Electrical Bonding of the Fuel Diffusers

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 230

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 44, Sheet 1

Config. 01 thru 03: Electrical Bonding of the Fuel Pumps

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 231

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 45, Sheet 1

Config. 01 thru 03: Electrical Bonding of the Fuel Pipes

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 232

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 45, Sheet 2

Config. 01 thru 03: Electrical Bonding of the Fuel Pipes

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 233

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 45, Sheet 3

Config. 01 thru 03: Electrical Bonding of the Fuel Pipes

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 234

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 46, Sheet 1

Config. 01 thru 03: Electrical Bonding Installation. Water Drain System

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 235

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 46, Sheet 2

Config. 01 thru 03: Electrical Bonding Installation. Water Drain System

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 236

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 47, Sheet 1

Config. 01 thru 03: Electrical Bonding Installation. Drainage Line

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 237

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 47, Sheet 2

Config. 01 thru 03: Electrical Bonding Installation. Drainage Line

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 238

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 48, Sheet 1

Config. 01 thru 03: Electrical Bonding Installation. Ventilation Intake System

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 239

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 240

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

APPENDIX 1

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

ATA SYSTEM : 28

TITLE : FUEL - GENERAL - REVISE THE ELECTRICAL BONDING OF THE EQUIPMENT IN THE

FUEL TANKS

MODIFICATION No. : 49135H14088, 50104S16539, 51825S16856

NOTE : Table to show the different configuration with the related points to be checked.

1. Config. 01 and Config. 03

A. Items 46 and 47, valid for MSN 0474, 0483, 0528, 0538, 0541, 0545 and 0546.

Refer to Figure 1

2. Config. 02

A. Items 1 thru 123, 128 thru 146, valid for MSN 0002 thru 0470.

Refer to Figure 2

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 1

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

APPENDIX 1

Figure 1, Sheet 1

Config. 01 and Config. 02 : Table for Aircraft Configuration

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

APPENDIX 1

Figure 2, Sheet 1

Config. 02 : Table for Aircraft Configuration

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 3

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

APPENDIX 1

This Page Intentionally Left Blank

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 4

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

REPORTING SHEET

TITLE : FUEL - GENERAL - REVISE THE ELECTRICAL BONDING OF THE EQUIPMENT IN THE

FUEL TANKS

MODIFICATION No. : 49135H14088, 50104S16539, 51825S16856

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 embodiement:

.............................................................................................................................................................................

.............................................................................................................................................................................

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 : Advance data................................................................................... YES/NO

Or : Intermediate/Temporary 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: SEDCC1 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 : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 1 of 1

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

REPORTING QUALITY

TITLE : FUEL - GENERAL - REVISE THE ELECTRICAL BONDING OF THE EQUIPMENT IN THE

FUEL TANKS

MODIFICATION No. : 49135H14088, 50104S16539, 51825S16856

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 futher 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 4 3 2 1

-Quality rating of the Accomplishment Instructions 4 3 2 1

-Quality rating of the Illustrations 4 3 2 1

-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 X Mod/Inspection

X Manpower Operator Supplied 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: SEMB Service Bulletins Management

FAX: (+33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE : Jun 14/04 SERVICE BULLETIN No. : A340-28-4097

REVISION No. : 05 - Jun 03/10 Page : 1 of 1

Printed in France © AIRBUS 2008 All rights reserved