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

ATA SYSTEM : 57

TITLE : WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL

BEAM FITTING AT FR.40

MODIFICATION No. : 56467S18944

This page transmits Revision No. 01 of Service Bulletin No. A340-57-4106.

ADDITIONAL WORK

Additional work is required by this revision for aircraft modified by any previous issue.

If this Service Bulletin has been accomplished per any previous issue (s) it is necessary to do the

additional work as described in this revision.

REASON

Revision No. 01 issued to extend the effectivity to aircraft post mod. No. 44360S13013 and pre mod.

No. 49202S16307 with specific Kit A03 and to amend accomplishment instruction for hole 5 without

bush installed.

The ADDITIONAL WORK is for aircraft in Config. 01 and is only necessary on those MSN on which

a crack was detected at hole 5 before oversizing of the keel beam (Refer for details to para. 3.B

(1)(b) step 3).

CHANGES

SUMMARY :

- REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Text updated. Price of Kit A01 updated. Kit A01S01 and A03 added in evaluation table.

- EFFECTIVITY

. Operators AJM, ALK, CAL, CCA, OAL, S3R, SAS and THT added. Operators updated. Note

updated.

- MATERIAL INFORMATION

. Kit A01S01, A03 and Config. 02 added.

PLANNING INFORMATION :

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 1 of 3

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- EFFECTIVITY

. Para. 1.A. Effectivity extended and updated. Notes updated.

- REASON

. Para. 1.C. Text updated.

- DESCRIPTION

. Para. 1.D. Config. 02 and ADDITIONAL WORK added.

- COMPLIANCE

. Para. 1.E. Sentence added.

- MANPOWER

. Para. 1.G. Manpower for Config. 02 added.

MATERIAL INFORMATION :

- MATERIAL - PRICE AND AVAILABILITY

. Para. 2.A. Price and availability of Kit A01 updated. Kit A01S01 and Kit A03 added.

- LIST OF COMPONENTS

. Para. 2.C. Kit A01 updated. Kits A0S01 and A03 added.

- LIST OF MATERIALS - OPERATOR SUPPLIED

. Para. 2.D. MAT No. 09-005, 09-016B, 09-028A, 16-001B and 16-002C added.

ACCOMPLISHMENT INSTRUCTIONS :

- Preparation

. Para. 3.A.(1) Config. 02 added.

- MODIFICATION

. Para. 3.B. Note added. Para. (1)(b)3b, rotating probe inspection added. Config. 02 added.

Alternative bolt EN6115-5-13 and EN6115-5-14 added. ADDITIONAL WORK added.

- TESTS

. Para. 3.C. Config. 02 added.

- CLOSE-UP

. Para. 3.D. Config. 02 added.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- ILLUSTRATIONS

. Figure 3, Sheets 03 and 04 updated.

. Figure 4, Sheets 03 and 04 updated.

. Figure 5 added.

. Figure 6 added.

. Figure 7 added.

. Figure 8 added.

APPENDIX 1 :

- Figure 1

. Inspection report 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

No previous revisions.

REVISION SEQUENCE

ORIGINAL : Aug 30/07

REVISION No. : 01 - Jul 31/09

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 3

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A340

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 4

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

ATA SYSTEM : 57

TITLE : WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL

BEAM FITTING AT FR.40

MODIFICATION No. : 56467S18944

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During a structural A330 aircraft fatigue test, cracks appeared in the keel beam fitting at FR40, initiating at

the first fastener hole aft of FR40 datum. The test bench was in post Mod. No. 41652S12091 (WINGS -

SECTION 15/21 - MODIFY KEEL FITTING BEAM/FORWARD LOWER FUSELAGE JOINT) production

solution configuration.

The intention of the production solution was also proposed by Service Bulletin A340-57-4036 for retrofit.

The structural analysis has led to the issue of the Inspection Service Bulletin A340-57-4089 (WINGS -

CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED

AIRCRAFT)).

The Inspection Service Bulletin requires a detailed inspection on A340 aircraft pre Mod. No. 49202S16307

(FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION 15/21) including mandatory and

recommended thresholds and repetitive inspection intervals.

This Service Bulletin recommends to modify the fasteners installation in the junction of the keel beam fitting at

FR40.

Accomplishment of this Service Bulletin cancels the inspection requirements of Service Bulletin A340-57-4089

for aircraft on which Mod. No. 41652S11819 (FUSELAGE-STRUCTURE A340 COMMONALITY ITEMS)

is embodied and Mod. No. 44360S13013 (WING-CENTER WING-MODIFY FR40 AND FRONT SPAR)

is not embodied and for aircraft on which Mod. 44360S13013 (WING-CENTER WING-MODIFY FR40

AND FRONT SPAR) is embodied and Mod. No. 49202S16307 (FUSELAGE - CENTER FUSELAGE -

REINFORCE SECTION 15/21) is not embodied.

ALI 57.11.63 is created for Post Mod. SB configuration (Post Mod. No. 56467S18944).

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 1 of 6

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

SUMMARY

EVALUATION TABLE

COMPLIANCE Recommended CANCELS INSPECTION SB Yes

POTENTIAL AD No A/C OPERATION AFFECTED No

RELIABILITY AFFECTED No PAX COMFORT AFFECTED No

COST SAVING No ETOPS AFFECTED No

STRUCTURAL LIFE EXTN Yes VENDOR SB INVOLVED No

KIT PRICE (USD) A01R02 304 KIT PRICE (USD) A03R03 2,243

KIT PRICE (USD) A01S01 83

MODIFICATION CLASSIFICATION

MAJOR 56467S18944

MINOR None

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 these operators :

AAW ACA AFR ALK CAL CCA CES CPA DLH ETD GFA IBE LAN MAU MSR OAL PAL S3R SAS SWR

THT THY UAE VIR

NOTE : This Service Bulletin is only applicable to aircraft on which modification No. 41652S11819

(FUSELAGE - STRUCTURE - INTRODUCE A340 COMMONALITY ITEMS) is embodied and

modification No. 49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION

15/21) is not embodied.

CONCURRENT REQUIREMENTS

None

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 2

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A340

SERVICE BULLETIN

SUMMARY

REFERENCES/REPERCUSSIONS

TFU : 57.11.00.005

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

OBRM : NO

MANPOWER

Config. 01

TOTAL MANHOURS 53.0

ELAPSED TIME (HOURS) 38.0

Config. 02

TOTAL MANHOURS 58.5

ELAPSED TIME (HOURS) 42.0

MATERIAL INFORMATION

AIRCRAFT DATA

Config. 01

Kit 574106A01R02

Bolts, nuts and washer

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 3

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A340

SERVICE BULLETIN

SUMMARY

Config. 01

Kit 574106A01S01

Bolts

Config. 02

Kit 574106A03R03

Plugs, bolts, nuts and washers

APPENDICES

Appendix 1 - REPORT

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 4

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

SUMMARY

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 5

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

SUMMARY

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 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

ATA SYSTEM : 57

TITLE : WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL

BEAM FITTING AT FR.40

MODIFICATION No. : 56467S18944

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

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

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

it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby

delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any

manner (except for the purposes of performing the tasks described hereunder and provided that any recipient

of such document shall comply with the conditions herein), without AIRBUS’ prior written consent.

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Models

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

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft MSN :

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 0429 0430 0433-0435 0438 0442 0446 0447 0450

0459 0467 0470 0474 0483

NOTE : This Service Bulletin is only applicable to aircraft on which modification

No. 41652S11819 (FUSELAGE - STRUCTURE - INTRODUCE

A340 COMMONALITY ITEMS) is embodied and modification No.

49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE

SECTION 15/21) is not embodied.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 1 of 76

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A340

SERVICE BULLETIN

(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

AAW 0151

ACA 0273 0278

AFR 0168 0174 0186 0207 0210 0237 0245 0246 0260 0307 0310

0319 0373 0377 0399

ALK 0367 0374

CAL 0402 0406 0411 0415 0433

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

DLH 0135 0158 0213 0233 0252 0274 0297 0304 0321 0325 0327 0335

0347 0352 0354 0355 0379 0390 0434 0447

ETD 0117

GFA 0133 0212 0215 0282

IBE 0125 0134 0145 0146 0170 0193 0197 0217 0221 0302 0318 0329

0332 0378 0387 0414 0459 0474 0483

LAN 0167 0359 0363 0429 0442

MAU 0152 0194 0268

MSR 0156 0159 0178

OAL 0235 0239 0280 0292

PAL 0173 0176 0187 0196

S3R 0204

SAS 0413 0424 0430 0435 0450 0467 0470

SWR 0150 0154 0169 0175 0179 0263

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 2

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A340

SERVICE BULLETIN

OPERATOR MSN

THT 0385 0395 0438 0446

THY 0115 0180 0216 0257 0270 0331

UAE 0139 0149 0163 0166 0185 0190 0202 0236

VIR 0114 0164 0214 0225

(c) Effectivity by MSN and Kit/Configuration

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

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 0173-0175

KIT No. QTY PER A/C CONFIGURATION

574106A01R02 2 01

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

0176 0178-0180 0182 0185-0187 0190 0192-0194 0196-0197 0199 0201-0202 0204

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

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

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

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

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

0446-0447 0450 0459 0467 0470 0474 0483

KIT No. QTY PER A/C CONFIGURATION

574106A03R03 2 02

NOTE : Config. 01 concerns aircraft on which modification No. 44360S13013

(WING - CENTER WING - MODIFY FR40 AND FRONT SPAR) is

not embodied.

NOTE : Config. 02 concerns aircraft on which modification No. 44360S13013

(WING - CENTER WING - MODIFY FR40 AND FRONT SPAR) is

embodied.

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 3

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A340

SERVICE BULLETIN

C. REASON

(1) History

During a structural A330 aircraft fatigue test, cracks appeared in the keel beam fitting at

FR40, initiating at the first fastener hole aft of FR40 datum. The test bench was in post Mod.

No. 41652S12091 (WINGS - SECTION 15/21 - MODIFY KEEL FITTING BEAM/FORWARD

LOWER FUSELAGE JOINT) production solution configuration.

The intention of the production solution was also proposed by Service Bulletin

A340-57-4036 for retrofit.

The structural analysis has led to the issue of the Inspection Service Bulletin A340-57-4089

(WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FASTENER HOLES AT

FRAME 40 (UNREPAIRED AIRCRAFT)).

The Inspection Service Bulletin requires a detailed inspection on A340 aircraft pre Mod.

No. 49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE SECTION 15/21)

including mandatory and recommended thresholds and repetitive inspection intervals.

(2) Objective/Action

This Service Bulletin recommends to modify the fasteners installation in the junction of

the keel beam fitting at FR40.

(3) Advantages

Accomplishment of this Service Bulletin cancels the inspection requirements of

Service Bulletin A340-57-4089 for aircraft on which Mod. No. 41652S11819

(FUSELAGE-STRUCTURE A340 COMMONALITY ITEMS) is embodied and Mod. No.

44360S13013 (WING-CENTER WING-MODIFY FR40 AND FRONT SPAR) is not embodied

and for aircraft on which Mod. 44360S13013 (WING-CENTER WING-MODIFY FR40

AND FRONT SPAR) is embodied and Mod. No. 49202S16307 (FUSELAGE - CENTER

FUSELAGE - REINFORCE SECTION 15/21) is not embodied.

ALI 57.11.63 is created for Post Mod. SB configuration (Post Mod. No. 56467S18944).

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

(1) Config. 01

(a) On the LH and RH sides, remove (only if necessary) the ducts between FR39.1

and FR40, for access.

(b) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel

beam fasteners for aircraft without bush installed on hole 5.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 4

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A340

SERVICE BULLETIN

(c) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel

beam fasteners, for aircraft with bush installed on hole 5.

(d) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40.

(2) Config. 02

(a) On the LH and RH sides, remove (only if necessary) the ducts between FR39.1

and FR40, for access.

(b) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel

beam fasteners for aircraft without bush installed on hole 5.

(c) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel

beam fasteners for aircraft with bush with a diameter < or = to 13mm (0.512in.)

installed on hole 5.

(d) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel

beam fasteners for aircraft with bush with a diameter > 13mm (0.512in.) and < or =

15mm (0.591in.) installed on hole 5.

(e) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40.

(3) ADDITIONAL WORK

(a) ADDITIONAL WORK concerns aircraft on which this Service Bulletin has been

accomplished at the original issue and on which a crack was found at first rototest

inspection (before keel beam reaming - Refer for details to Paragraph. 3.B (1)(b)

step 3).

For the accomplishment of the ADDITIONAL WORK, the operator must contact

AIRBUS to get instructions.

E. COMPLIANCE

(1) Classification

Recommended

(2) Accomplishment Timescale

(a) For aircraft in Config. 01

AIRBUS strongly recommends not to perform modification before the FC/FH values

given in the table below. In case of early embodiment, additional inspection of CWB

lower panel might be required before DSG or ISG.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 5

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Aircraft A340-300 A340-200 Post Mod.

No. 41652S11819 and pre Mod.

No. 44360S13013

A340-300 Post Mod. No.

41652S11819 and pre Mod. No.

44360S13013

Recommended NOT before FC or

FH

Recommended NOT before FC or

FH

Proposed Compliance

11,170FC / 40,390FH 11,170FC / 40,390FH

(b) For aircraft in Config. 02

AIRBUS strongly recommends not to perform modification before the FC/FH values

given in the table below. In case of early embodiment, additional inspection of CWB

lower panel might be required before DSG or ISG.

Aircraft A340-300 A340-200 Post Mod.

No. 44360S13013 and pre Mod.

No. 49202S16307

A340-300 Post Mod. No.

44360S13013 and pre Mod. No.

49202S16307 WV027

Proposed Compliance Recommended NOT before FC or FH

11,170FC / 40,390FH 16,350 FC / 32,700FH

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 operator’s circumstances. The estimates do not include the

time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying

times for paints, sealants, etc, and general administration work are also not included.

Config. 01

Get access 12.0

Removal of the ducts 6.0

Removal of fastener, hole 5 1.0

Rotating probe inspection hole 5 1.0

Installation of the fastener, hole 5 2.5

Removal of fasteners, holes 6 and 7 2.0

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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A340

SERVICE BULLETIN

Rotating probe inspection holes 6 and 7 1.5

Cold expansion hole 6 1.5

Installation of fasteners, holes 6 and 7 2.5

Installation of the ducts 6.0

Test 2.0

Close-up 15.0

TOTAL MANHOURS 53.0

ELAPSED TIME (HOURS) 38.0

Config. 02

Get access 12.0

Removal of the ducts 6.0

Removal of fastener, hole 5 1.0

Rotating probe inspection hole 5 1.0

Installation of the plug (if necessary) 3.0

Installation of the fastener, hole 5 2.5

Removal of fasteners, holes A, 6 and 7 3.0

Rotating probe inspection holes A, 6, 7 2.0

Cold expansion holes A and 6 2.0

Installation of fasteners, holes A, 6, 7 3.0

Installation of the ducts 6.0

Test 2.0

Close-up 15.0

TOTAL MANHOURS 58.5

ELAPSED TIME (HOURS) 42.0

H. WEIGHT AND BALANCE

Not changed

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 7

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A340

SERVICE BULLETIN

I. ELECTRICAL LOAD DATA

Not changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) : 06-41-53 12-34-24 20-21-11 21-20-00

21-53-18 27-84-45 28-25-00 32-12-00

36-12-41 53-35-13 57-17-11

Consumable Material List (CML)

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

Non destructive Testing Manual (NTM) : 51-10-01 51-10-18

Service Information Letter (SIL) : 51-012

Structural Repair Manual (SRM) : 51-42-11 51-43-00 51-44-11 51-48-00

51-76-12

PMS 01-05-05

Service Bulletin No. A340-57-4036

Service Bulletin No. A340-57-4089

Appendix 1

K. PUBLICATIONS AFFECTED

Not changed

L. INTERCHANGEABILITY/MIXABILITY

Not applicable

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 8

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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

SPARES SUPPORT AND SERVICES

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 574106A01R02

Cost : 304.00 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 574106A01S01

Cost : 83.00 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.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 9

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Kit Held by the Operator Supplementary Kits

Required

Latest Status of Kit INST/DISP

574106A01R01 574106A01S01 574106A01R02

574106A01R02 NONE 574106A01R02

NOTE : Kit 574106A01R02 does not require an Kit 574106A01S01 because Kit

574106A01S01 is included in Kit 574106A01R02.

Kit 574106A03R03

Cost : 2,243.00 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.

B. INDUSTRY SUPPORT INFORMATION

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

C. LIST OF COMPONENTS

Kit 574106A01R02

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

25 EN6115-6Y-20 1 Bolt

26 NSA5368-616D 1 Washer

27 ASNA2531-6 1 Nut

31 ASNA2531-5 1 Nut

32 EN6115-5-12 1 Bolt

33 ASNA2529-6 1 Nut

34 EN6115V6Y-16 1 Bolt

35 F5332433420000 1 Washer

42 NSA5368PD616D 1 Washer

51 EN6115-5-13 1 Bolt

52 EN6115-5-14 1 Bolt

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 574106A01S01

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

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REVISION No. : 01 - Jul 31/09 Page : 10

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A340

SERVICE BULLETIN

51 EN6115-5-13 1 Bolt

52 EN6115-5-14 1 Bolt

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 574106A03R03

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

27 ASNA2531-6 2 Nut

28 EN6115-6Y-16 1 Bolt

29 EN6115-6Y-10 1 Bolt

30 EN6115-6Y-8 1 Bolt

31 ASNA2531-5 1 Nut

32 EN6115-5-12 1 Bolt

33 ASNA2529-6 1 Nut

35 F5332433420000 1 Washer

36 EN6115V6X-6 1 Bolt

37 F5332433520000 1 Plug

38 F5332433520200 1 Plug

39 F5332433520400 1 Plug

40 F5332433520600 1 Plug

42 NSA5368PD616D 1 Washer

50 NSA5372-616D 2 Washer

51 EN6115-5-13 1 Bolt

52 EN6115-5-14 1 Bolt

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.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

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

MAT No.

Fuel Tank Sealant Polysulfide Mat. No. 09-002B As required

Corrosion Inhibitive Interfay Sealant Mat. No. 09-005 As required

Corrosion Inhibiting Brush

Consistency

Mat. No. 09-013B As required

Corrosion Inhibiting Fillet

Consistency

Mat. No. 09-016B As required

Adhesion Promoter For Polysulfide

Sealant

Mat. No. 09-028A As required

Solvent General Purpose Mat. No. 11-026 As required

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 11

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A340

SERVICE BULLETIN

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

MAT No.

Chemical Conversion Coating Yellow

Aluminum

Mat. No. 13-002 As required

Polyurethane Primer Mat. No. 16-001B As required

Internal Top Coat Mat. No. 16-002C As required

(2) Components

None

E. PARTS TO BE RE-IDENTIFIED BY THE OPERATOR

None

F. TOOLING - PRICE AND AVAILABILITY

(1) To accomplish this Service Bulletin, it is necessary to use the following tools and equipment.

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

(b) Equipment and materials for the check of the holes as per NTM 51-10-18 Part 6.

(2) Fatigue Technology Incorporated (FTI) has allocated the following tool kit numbers for

cold working :

NOTE : For definition of capital, durable and expendable tools, refer to SIL 51-012.

- Capital tooling : ref. FTI-A340-57-4106-1

This tool reference include all capital, durable and expendable tooling kits regardless of

effectivity but capital tooling is normally already and previously bought by the operator as

a long term investment or loaned from FTI.

- Durable tooling : ref. DK-A340-57-4106-1

NOTE : In this durable tool, there is the minimum quantity necessary to accomplish

this Service Bulletin on one aircraft. In case of accomplishment of this

Service Bulletin on more than one aircraft, operator can define the quantity

of durable tool to be ordered by reference to SIL 51-012.

- Expendable tooling : ref. EK-A340-57-4106-1

NOTE : In this expendable tool, there is the minimum quantity necessary to

accomplish this Service Bulletin on one aircraft. One expendable tool has to

be ordered for each aircraft where this Service Bulletin is accomplished.

Operators interested in obtaining the FTI tool kit should contact :

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 12

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SERVICE BULLETIN

Fatigue Technology Inc.

401 Andover Park West

SEATTLE, WA 98188-7605

USA

E.Mail : sales@fatiguetech.com

E.Mail : aog@fatiguetech.com

Phone : (1) 206 2462010

Fax : (1) 206 2449886

G. SPECIAL TOOLS

None

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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A340

SERVICE BULLETIN

This Page Intentionally Left Blank

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY

SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR

MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND

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

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER

CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND

DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

(1) Preparation

(a) Config. 01 thru Config. 02

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

2 Put the access platform(s) in position.

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

block 201).

4 Do the preparation procedure as specified in removal/installation of the

air-conditioning distribution ducts (Refer to AMM 21-20-00, Page block 201).

5 Do the preparation procedure as specified in removal/installation of the pack

discharge temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18,

Page block 401).

6 Do the preparation procedure as specified in removal/installation of the APU

bleed-air ducts (Refer to AMM 36-12-41, Page block 401).

7 Remove the access panels 191FB for the LH side and 192GB for the RH side

(Refer to AMM 53-35-13, Page block 401 and AMM 06-41-53).

8 Remove the access covers 147AZ and 148AZ (Refer to AMM 57-17-11, Page

block 401).

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

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SERVICE BULLETIN

10 Remove the torque shaft assies 5010CW and 5070CW (Refer to AMM 27-84-45,

Page block 401).

11 Get access to the work area.

(2) Standard Practices

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

(b) Clean the surfaces to be sealed with Solvent General Purpose (Mat. No. 11-026).

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

General Purpose (Mat. No. 11-026).

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

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

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

fasteners to be installed (wet assembly).

(g) For the oversize and alternative fasteners (Refer to SRM 51-43-00).

(h) Torque the standard threaded fasteners (Refer to AMM 20-21-11, Page block 201).

(i) Do the cold expansion of the holes (Refer to SRM 51-48-00).

(j) Apply the sealant (Refer to SRM 51-76-12).

(k) Install the plug with liquid nitrogen (Refer to PMS 01-05-05).

B. MODIFICATION

NOTE : For aircraft on which temporary repair (covered by Repair Design Approval Sheet

(RAS)) have been done following accomplishment of Inspection Service Bulletin

A340-57-4089, the operator must contact AIRBUS repair office in order to issue

definitive RAS after embodiment of this Modification Service Bulletin.

(1) Config. 01

(a) On the LH and RH sides, remove (only if necessary) the ducts between FR39.1

and FR40, for access.

Refer to Figures 1 and 2

1 On RH side, remove the air conditioning duct.

Refer to Figure 1

a Remove :

1 Duct Item (8) Retain

1 Insulation Item (9) Retain

1 Nut Item (10) Retain

1 Bolt Item (11) Retain

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A340

SERVICE BULLETIN

1 Washer Item (12) Retain

2 Screw Item (13) Retain

2 Washer Item (14) Retain

2 Nut Item (15) Retain

1 Clamp Item (16) Retain

1 Clamp Item (17) Retain

NOTE(01) Disconnect and move the rod Items (18) and (19) without

removal.

NOTE(02) Remove the Insulation Item (9) with associated clamp Item (17)

from the duct Item (8) only if necessary.

NOTE(03) For the removal of the sensor 542HH (Refer to AMM 21-53-18,

Page block 401).

2 On RH side, remove the air ventilation duct.

Refer to Figure 2

a Remove :

1 Duct Item (20) Retain

8 Clamp Item (21) Retain

4 Clamp Item (22) Retain

2 Sleeve Item (23) Retain

1 Sleeve Item (24) Retain

3 On LH side, remove the necessary APU bleed air system ducts between FR39.1

and FR40 (Refer to AMM 36-12-41, Page block 401).

4 Put the blanking plugs on the disconnected line ends.

(b) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel

beam fasteners for aircraft without bush installed on hole 5.

Refer to Kit 574106A01R02

Refer to Figure 3

NOTE : Description below is given for one side of the aircraft, two Kit

574106A01R02 are necessary to modify one aircraft.

1 Inspect the hole 5.

Refer to Figure 3, Sheets 1 and 2

a Remove :

1 Bolt Item (41) Discard

1 Nut Item (4) Discard

b Remove the sealant and clean the hole.

c Do a rotating probe inspection (Refer to NTM 51-10-01) through all the

layers.

- If no crack is detected, do the operations given in paragraph (1)(b)2.

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SERVICE BULLETIN

- If crack is detected do the operations given in paragraph (1)(b)3.

2 No crack, oversize the hole 5 in the keel beam.

Refer to Figure 3, Sheets 1, 3 and 4

a Ream the hole at the level of the keel beam only to a diameter comprised

between 17mm (0.669in.) and 17.2mm (0.677in.) with a radius of 2mm

(0.079in.). Admissible reaming depth in the CWB lower panel is comprised

between 1mm (0.039in.) and 1.2mm (0.047in.).

b Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm

(0.669in.).

c Oversize the hole 5 through all the layers to a diameter comprised between

10.177mm (0.401in.) and 10.219mm (0.402in.).

d Clean the drilled area.

e Install :

1 Bolt EN6115V6Y-16 Item 34

1 Washer F5332433420000 Item 35

1 Nut ASNA2529-6 Item 33

1 Washer NSA5368PD616D Item 42

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut and washer with Fuel Tank Sealant Polysulfide

(Mat. No. 09-002B).

3 Crack detected, oversize the hole 5 in the keel beam.

Refer to Figure 3, Sheets 1, 3 and 4

a Ream the hole 5 at the level of the keel beam only to a diameter comprised

between 15mm (0.591in.) and 15.2mm (0.598in.) with a radius of 2mm

(0.079in.). Admissible reaming depth in the CWB lower panel is comprised

between 0.5mm (0.02in.) and 0.7mm (0.028in.).

b Do a rotating probe inspection at the level of the keel beam only (Refer

to NTM 51-10-18).

- Crack finding, contact AIRBUS.

- No crack finding, oversize the hole in the keel beam only to a diameter

comprised between 17mm (0.669in.) and 17.2mm (0.677in.) with a radius

of 2mm (0.079in.). Admissible reaming depth in the CWB lower panel is

comprised between 1mm (0.039in.) and 1.2mm (0.047in.).

- Do a rotating probe inspection through all the layers of hole 5 (Refer

to NTM 51-10-01)

. Crack finding, contact AIRBUS.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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A340

SERVICE BULLETIN

. No crack finding, do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on

the hole dia. 17mm (0.669in.).

. Oversize the hole 5 through all the layers to a diameter comprised

between 10.177mm (0.401in.) and 10.219mm (0.402in.)

. Install :

1 Bolt EN6115V6Y-16 Item 34

1 Washer F5332433420000 Item 35

1 Nut ASNA2529-6 Item 33

1 Washer NSA5368PD616D Item 42

NOTE(01) Before installation of the fasteners, apply Corrosion

Inhibiting Brush Consistency (Mat. No. 09-013B) (wet

assembly).

NOTE(02) Coat the nut and washer with Fuel Tank Sealant

Polysulfide (Mat. No. 09-002B).

4 Inspect holes 6 and 7

Refer to Figure 3, Sheets 1 and 2

a Remove :

1 Nut Item (2) Discard

1 Nut Item (4) Discard

1 Bolt Item (1) Discard

1 Bolt Item (3) Discard

b Remove the sealant and clean the holes.

c Do a rotating probe inspection through all the layers of holes 6 and 7 (Refer

to NTM 51-10-01).

- If a crack is detected, contact AIRBUS.

- If no crack is detected, do the operations given in paragraphes (1)(b)5

and 6.

5 Do the cold working of the hole 6.

Refer to Figure 3, Sheets 1, 3 and 4

a Ream the hole to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A340-57-4106-1.

b Clean the drilled area.

c Do the cold working of the hole (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1.

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SERVICE BULLETIN

d Ream the hole to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A340-57-4106-1.

e Clean the drilled area.

f Install :

1 Bolt EN6115-6Y-20 Item 25

1 Nut ASNA2531-6 Item 27

1 Washer NSA5368-616D Item 26

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

6 Install the fastener in hole 7.

Refer to Figure 3, Sheets 1, 3 and 4

a Oversize the hole to a diameter comprised between 7.809mm (0.307in.)

and 7.849mm (0.309in.).

b Install :

1 Bolt EN6115-5-12 Item 32

or depending on the thickness of the structure :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

NOTE(03) If necessary, contact AIRBUS for a specific washer solution.

7 For the report after modification, refer to Appendix 1.

(c) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel

beam fasteners, for aircraft with bush installed on hole 5.

Refer to Figure 4

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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A340

SERVICE BULLETIN

NOTE(01) Description below is given for one side of the aircraft, two Kit

574106A01R02 are necessary to modify one aircraft.

NOTE(02) If the diameter of the bush is >13mm (0.512in.) or if the bush is installed

in other layers than keel beam fitting only, contact AIRBUS.

1 Inspect the hole 5.

Refer to Figure 4, Sheets 1 and 2

a Remove :

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

1 Bush Item (5) Discard

b Remove the sealant and clean the hole.

c Do a rotating probe inspection (Refer to NTM 51-10-18) through all the

layers.

- If crack is detected, contact AIRBUS.

- If no crack is detected, do the operations given in paragraph (1)(c)2.

2 No crack finding, oversize the hole in the keel beam.

Refer to Figure 4, Sheets 1, 3 and 4

a Ream the hole at the level of the keel beam only to a diameter comprised

between 17mm (0.669in.) and 17.2mm (0.677in.) with a radius of 2mm

(0.079in.). Admissible reaming depth in the CWB lower panel is comprised

between 1mm (0.039in.) and 1.2mm (0.047in.)

b Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm

(0.669in.).

c Oversize the hole through all the layers to a diameter comprised between

10.177mm (0.401in.) and 10.219mm (0.402in.)

d Install :

1 Bolt EN6115V6Y-16 Item 34

1 Washer F5332433420000 Item 35

1 Nut ASNA2529-6 Item 33

1 Washer NSA5368PD616D Item 42

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut and washer with Fuel Tank Sealant Polysulfide

(Mat. No. 09-002B).

3 Inspect holes 6 and 7.

Refer to Figure 4, Sheets 1 and 2

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SERVICE BULLETIN

a Remove :

1 Nut Item (2) Discard

1 Nut Item (4) Discard

1 Bolt Item (1) Discard

1 Bolt Item (41) Discard

b Remove the sealant and clean the holes.

c Do a rotating probe inspection through all the layers of holes 6 and 7 (Refer

to NTM 51-10-01).

- If a crack is detected, contact AIRBUS.

- If no crack is detected, do the operations given in the paragraphes

(1)(c)4 and 5.

4 Do the cold working of the hole 6.

Refer to Figure 4, Sheets 1, 3 and 4

a Ream the hole to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A340-57-4106-1.

Clean the drilled area.

b Do the cold working of the hole (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1.

c Ream the hole to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A340-57-4106-1.

d Clean the drilled area.

e Install :

1 Bolt EN6115-6Y-20 Item 25

1 Nut ASNA2531-6 Item 27

1 Washer NSA5368-616D Item 26

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

5 Install the fastener in hole 7.

Refer to Figure 4, Sheets 1, 3 and 4

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SERVICE BULLETIN

a Oversize the hole to a diameter comprised between 7.809mm (0.307in.)

and 7.849mm (0.309in.).

b Install :

1 Bolt EN6115-5-12 Item 32

or depending on the thickness of the structure :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

NOTE(03) If necessary, contact AIRBUS for a specific washer solution.

6 For the report after modification, refer to Appendix 1.

(d) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40.

Refer to Figures 1 and 2

1 Remove the blanking plugs on the disconnected line ends.

2 On LH side, install (if removed) the APU bleed air system ducts between FR39.1

and FR40 (Refer to AMM 36-12-41, Page block 401).

3 On RH side, install (if removed) the air ventilation duct.

Refer to Figure 2

a Install :

1 Duct Item (20)

8 Clamp Item (21)

4 Clamp Item (22)

2 Sleeve Item (23)

1 Sleeve Item (24)

NOTE : Items (20) thru (24) were retained at removal.

4 On RH side, install (if removed) the air conditioning duct.

Refer to Figure 1

a Install :

1 Duct Item (8)

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SERVICE BULLETIN

1 Insulation Item (9)

1 Nut Item (10)

1 Bolt Item (11)

1 Washer Item (12)

2 Screw Item (13)

2 Washer Item (14)

2 Nut Item (15)

1 Clamp Item (16)

1 Clamp Item (17)

NOTE(01) Reconnect the rod Items (18) and (19).

NOTE(02) For the installation of the sensor 542HH (Refer to AMM

21-53-18, Page block 401).

NOTE(03) Items (8) thru (17) were retained at removal.

(2) Config. 02

NOTE : Refer to paragraph E.(2) Accomplishment Timescale for Config. 02

embodiment recommendation.

(a) On the LH and RH sides, remove (only if necessary) the ducts between FR39.1

and FR40, for access.

Refer to Figures 1 and 2

1 On RH side, remove the air conditioning duct.

Refer to Figure 1

a Remove :

1 Duct Item (8) Retain

1 Insulation Item (9) Retain

1 Nut Item (10) Retain

1 Bolt Item (11) Retain

1 Washer Item (12) Retain

2 Screw Item (13) Retain

2 Washer Item (14) Retain

2 Nut Item (15) Retain

1 Clamp Item (16) Retain

1 Clamp Item (17) Retain

NOTE(01) Disconnect and move the rod Items (18) and (19) without

removal.

NOTE(02) Remove the Insulation Item (9) with associated clamp Item (17)

from the duct Item (8) only if necessary.

NOTE(03) For the removal of the sensor 542HH (Refer to AMM 21-53-18,

Page block 401).

2 On RH side, remove the air ventilation duct.

Refer to Figure 2

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A340

SERVICE BULLETIN

a Remove :

1 Duct Item (20) Retain

8 Clamp Item (21) Retain

4 Clamp Item (22) Retain

2 Sleeve Item (23) Retain

1 Sleeve Item (24) Retain

3 On LH side, remove the necessary APU bleed air system ducts between FR39.1

and FR40 (Refer to AMM 36-12-41, Page block 401).

4 Put the blanking plugs on the disconnected line ends.

(b) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel

beam fasteners for aircraft without bush installed on hole 5.

Refer to Kit 574106A03R03

Refer to Figures 5 and 6

NOTE(01) Description below is given for one side of the aircraft, two Kit

574106A03R03 are necessary to modify one aircraft.

1 Inspect the hole 5.

Refer to Figure 5, Sheets 1 and 2

a Remove :

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

b Remove the sealant and clean the hole.

c Do a rotating probe inspection through all the layers of hole 5 (Refer

to NTM 51-10-01).

- If no crack is detected, do the operations given in paragraph (2)(b)2.

- If a crack is detected, do the operations given in paragraph (2)(b)6.

2 No crack, oversize the hole 5 in the keel beam.

Refer to Figure 5, Sheets 1, 3 and 4

a Ream the hole 5 at the level of the keel beam only to a diameter comprised

between 17mm (0.669in.) and 17.2mm (0.677in.) with a radius of 2mm

(0.079in.). Admissible reaming depth in the CWB lower panel is comprised

between 1mm (0.039in.) and 1.2mm (0.047in.).

b Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the hole dia. 17mm

(0.669in.).

c Oversize the hole 5 through all the layers to a diameter comprised between

9.784mm (0.385in.) and 9.823mm (0.387in.)

d Install :

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 25

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A340

SERVICE BULLETIN

1 Bolt EN6115V6X-6 Item 36

1 Washer F5332433420000 Item 35

1 Washer NSA5368PD616D Item 42

1 Nut ASNA2529-6 Item 33

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut and washer with Fuel Tank Sealant Polysulfide

(Mat. No. 09-002B).

3 Inspect holes A, 6 and 7.

Refer to Figure 5, Sheets 1 and 2

a Remove :

1 Nut Item (2) Discard

1 Nut Item (4) Discard

1 Nut Item (6) Discard

1 Bolt Item (1) Discard

1 Bolt Item (3) Discard

1 Bolt Item (7) Discard

b Remove the sealant and clean the holes.

c Do a rotating probe inspection through all the layers of holes A, 6 and 7

(Refer to NTM 51-10-01).

- If a crack is detected, contact AIRBUS.

- If no crack is detected, do the operations given in the paragraphes

(2)(b)4 and 5.

4 Do the cold working of the holes A and 6.

Refer to Figure 5, Sheets 1, 3 and 4

a Ream the holes A and 6 to the starting hole diameter for the cold working

comprised between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A340-57-4106-1.

b Clean the drilled area.

c Do the cold working of the holes A and 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1.

d Ream the holes A and 6 to the final hole diameter comprised between

10.177mm (0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A340-57-4106-1.

e Clean the drilled area.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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A340

SERVICE BULLETIN

f Install :

1 Bolt EN6115-6Y-16 Item 28

1 Bolt EN6115-6Y-8 Item 30

2 Nut ASNA2531-6 Item 27

2 Washer NSA5372-616D Item 50

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nuts with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

5 Install the fastener in hole 7.

Refer to Figure 5, Sheets 1, 3 and 4

a Oversize the hole to a diameter comprised between 7.809mm (0.307in.)

and 7.849mm (0.309in.).

b Install :

1 Bolt EN6115-5-12 Item 32

or depending on the thickness of the structure :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

6 Crack detected at existing diameter.

Refer to Figure 6, Sheets 1, 3 thru 5

a Ream the hole 5 through all the layer at diameter 9.5mm (0.374in.).

b Perform a rotating probe inspection through all the layers of hole 5.(Refer

to NTM 51-10-01).

- If no crack is detected, do the operations given in paragraph (2)(b)7.

- If a crack is detected at diameter 9.5mm (0.374in.), do the operations

given in paragraph (2)(b)11.

7 No crack detected at diameter 9.5mm (0.374in.) for hole 5.

Refer to Figure 6, Sheets 1, 3 thru 5

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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A340

SERVICE BULLETIN

a Remove the fastener of hole 6.

- Remove:

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

b Ream the hole 6 to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A340-57-4106-1.

c Clean the drilled area.

d Do the cold working of the hole 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1.

e Ream the hole 6 to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A340-57-4106-1.

f Clean the drilled area.

g Ream the hole 5 through all the layers to a diameter comprised between

11.5mm (0.4528in.) and 11.518mm (0.4535in.)

h Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5.

i Protect the hole 5 with Chemical Conversion Coating Yellow Aluminum

(Mat. No. 13-002).

j Install :

1 Plug F5332433520000 Item 37

1 Bolt EN6115-6Y-10 Item 29

1 Washer NSA5372-616D Item 50

1 Nut ASNA2531-6 Item 27

NOTE(01) Install the plug Item 37 with liquid nitrogen (Refer to PMS

01-05-05).

NOTE(02) Apply Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005)

between the plug Item 37 and the structure.

NOTE(03) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(04) Apply Polyurethane Primer (Mat. No. 16-001B) andInternal Top

Coat (Mat. No. 16-002C) after assembly in the hole.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 28

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A340

SERVICE BULLETIN

NOTE(05) Do a seal bead with Corrosion Inhibiting Fillet Consistency (Mat.

No. 09-016B) in the hole on the edge of the plug Item 37.

NOTE(06) Do a seal bead on the external edge of the plug Item 37

withFuel Tank Sealant Polysulfide (Mat. No. 09-002B) and

Adhesion Promoter For Polysulfide Sealant (Mat. No. 09-028A).

NOTE(07) Coat the nut and washer with Fuel Tank Sealant Polysulfide

(Mat. No. 09-002B).

8 Inspect holes A and 7.

Refer to Figure 6, Sheets 1 and 2

a Remove :

1 Nut Item (2) Discard

1 Nut Item (6) Discard

1 Bolt Item (1) Discard

1 Bolt Item (7) Discard

b Remove the sealant and clean the holes.

c Do a rotating probe inspection through all the layers of holes A and 7

(Refer to NTM 51-10-01).

- If a crack is detected, contact AIRBUS.

- If no crack is detected, do the operations given in the paragraphes

(2)(b)9 and 10.

9 Do the cold working of the hole A.

Refer to Figure 6, Sheets 1, 3 and 4

a Ream the hole A to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A340-57-4106-1.

b Clean the drilled area.

c Do the cold working of the hole A (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1.

d Ream the hole A to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A340-57-4106-1.

e Clean the drilled area.

f Install :

1 Bolt EN6115-6Y-16 Item 28

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 29

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A340

SERVICE BULLETIN

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616D Item 50

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

10 Install the fastener in hole 7.

Refer to Figure 6, Sheets 1, 3 and 4

a Oversize the hole to a diameter comprised between 7.809mm (0.307in.)

and 7.849mm (0.309in.).

b Install :

1 Bolt EN6115-5-12 Item 32

or depending on the thickness of the structure :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

11 Crack detected at diameter 9.5mm (0.374in.) for hole 5.

a Ream the hole 5 through all the layers at diameter 11.1mm (0.437in.).

b Perform a rotating probe inspection through all the layers of hole 5.(Refer

to NTM 51-10-01).

- If no crack is detected, do the operations given in paragraph (2)(b)12.

- If a crack is detected, do the operations given in paragraph (2)(b)16.

12 No crack detected at diameter 11.1mm (0.437in.) for hole 5.

Refer to Figure 6, Sheets 1, 3 thru 5

a Remove the fastener of hole 6.

- Remove:

1 Bolt Item (3) Discard

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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A340

SERVICE BULLETIN

1 Nut Item (4) Discard

b Ream the hole 6 to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A340-57-4106-1.

c Clean the drilled area.

d Do the cold working of the hole 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1.

e Ream the hole 6 to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A340-57-4106-1.

f Clean the drilled area.

g Ream the hole 5 through all the layers to a diameter comprised between

13.1mm (0.5157in.) and 13.118mm (0.5165in.).

h Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5.

i Protect the hole 5 with Chemical Conversion Coating Yellow

AluminumChemical Conversion Coating Yellow Aluminum (Mat. No.

13-00213-002).

j Install :

1 Plug F5332433520200 Item 38

1 Bolt EN6115-6Y-10 Item 29

1 Washer NSA5372-616D Item 50

1 Nut ASNA2531-6 Item 27

NOTE(01) Install the plug Item 38 with liquid nitrogen (Refer to PMS

01-05-05).

NOTE(02) Apply Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005)

between the plug Item 38 and the structure.

NOTE(03) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(04) Apply Polyurethane Primer (Mat. No. 16-001B) andInternal Top

Coat (Mat. No. 16-002C) after assembly in the hole.

NOTE(05) Do a seal bead withCorrosion Inhibitingfillet

ConsistencyCorrosion Inhibiting Fillet Consistency (Mat. No.

09-016B09-016B) in the hole on the edge of the plug Item 38.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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A340

SERVICE BULLETIN

NOTE(06) Do a seal bead on the external edge of the plug Item 38

withFuel Tank Sealant Polysulfide (Mat. No. 09-002B) and

Adhesion Promoter For Polysulfide Sealant (Mat. No. 09-028A).

NOTE(07) Coat the nut and washer with Fuel Tank Sealant Polysulfide

(Mat. No. 09-002B).

13 Inspect holes A and 7.

Refer to Figure 6, Sheets 1 and 2

a Remove :

1 Nut Item (2) Discard

1 Nut Item (6) Discard

1 Bolt Item (1) Discard

1 Bolt Item (7) Discard

b Remove the sealant and clean the holes.

c Do a rotating probe inspection through all the layers of holes A and 7

(Refer to NTM 51-10-01).

- If a crack is detected, contact AIRBUS.

- If no crack is detected, do the operations given in the paragraphes

(2)(b)14 and 15.

14 Do the cold working of the hole A.

Refer to Figure 6, Sheets 1, 3 and 4

a Ream the hole A to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A340-57-4106-1.

b Clean the drilled area.

c Do the cold working of the hole A (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1.

d Ream the hole A to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A340-57-4106-1.

e Clean the drilled area.

f Install :

1 Bolt EN6115-6Y-16 Item 28

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616D Item 50

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 32

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A340

SERVICE BULLETIN

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

15 Install the fastener in hole 7.

Refer to Figure 6, Sheets 1, 3 and 4

a Oversize the hole to a diameter comprised between 7.809mm (0.307in.)

and 7.849mm (0.309in.).

b Install :

1 Bolt EN6115-5-12 Item 32

or depending on the thickness of the structure :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

16 Crack detected at diameter 11.1mm (0.437in.) for hole 5.

a Ream the hole 5 through all the layers at diameter 13.1mm (0.516in.).

b Perform a rotating probe inspection through all the layers of hole 5.(Refer

to NTM 51-10-01).

- If no crack is detected, do the operations given in paragraph (2)(b)17.

- If crack is detected, do the operations given in paragraph (2)(b)21.

17 No crack detected at diameter 13.1mm (0.516in.) for hole 5.

a Remove the fastener of hole 6.

- Remove:

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

b Ream the hole 6 to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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SERVICE BULLETIN

Use tool list No. DK-A340-57-4106-1.

c Clean the drilled area.

d Do the cold working of the hole 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1.

e Ream the hole 6 to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A340-57-4106-1.

f Clean the drilled area.

g Ream the hole 5 through all the layers to a diameter comprised between

15mm (0.5906in.) and 15.018mm (0.5913in.).

h Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5.

i Protect the hole 5 with Chemical Conversion Coating Yellow Aluminum

(Mat. No. 13-002).

j Install :

1 Plug F5332433520400 Item 39

1 Bolt EN6115-6Y-10 Item 29

1 Washer NSA5372-616D Item 50

1 Nut ASNA2531-6 Item 27

NOTE(01) Install the plug Item 39 with liquid nitrogen (Refer to PMS

01-05-05).

NOTE(02) Apply Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005)

between the plug Item 39 and the structure.

NOTE(03) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(04) Apply Polyurethane Primer (Mat. No. 16-001B) andInternal Top

Coat (Mat. No. 16-002C) after assembly in the hole.

NOTE(05) Do a seal bead withCorrosion Inhibiting Fillet Consistency (Mat.

No. 09-016B) in the hole on the edge of the plug Item 39.

NOTE(06) Do a seal bead on the external edge of the plug Item 39

withFuel Tank Sealant Polysulfide (Mat. No. 09-002B) and

Adhesion Promoter For Polysulfide Sealant (Mat. No. 09-028A).

NOTE(07) Coat the nut and washer with Fuel Tank Sealant Polysulfide

(Mat. No. 09-002B).

18 Inspect holes A and 7.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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A340

SERVICE BULLETIN

Refer to Figure 6, Sheets 1 and 2

a Remove :

1 Nut Item (2) Discard

1 Nut Item (6) Discard

1 Bolt Item (1) Discard

1 Bolt Item (7) Discard

b Remove the sealant and clean the holes.

c Do a rotating probe inspection through all the layers of holes A and 7

(Refer to NTM 51-10-01).

- If a crack is detected, contact AIRBUS.

- If no crack is detected, do the operations given in the paragraphes

(2)(b)19 and 20.

19 Do the cold working of the hole A.

Refer to Figure 6, Sheets 1, 3 and 4

a Ream the hole A to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A340-57-4106-1.

b Clean the drilled area.

c Do the cold working of the hole A (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1.

d Ream the hole A to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A340-57-4106-1.

e Clean the drilled area.

f Install :

1 Bolt EN6115-6Y-16 Item 28

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616D Item 50

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

20 Install the fastener in hole 7.

Refer to Figure 6, Sheets 1, 3 and 4

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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A340

SERVICE BULLETIN

a Oversize the hole to a diameter comprised between 7.809mm (0.307in.)

and 7.849mm (0.309in.).

b Install :

1 Bolt EN6115-5-12 Item 32

or depending on the thickness of the structure :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

21 Crack detected at diameter 13.1mm (0.516in.) for hole 5.

a Ream the hole 5 through all the layers at diameter of 15mm (0.591in.).

b Perform a rotating probe inspection through all the layers of hole 5.(Refer

to NTM 51-10-01).

- If no crack is detected, do the operations given in paragraph (2)(b)22.

- If crack is detected, contact AIRBUS.

22 No crack detected at diameter 15mm (0.591in.) for hole 5.

a Remove the fastener of hole 6.

- Remove:

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

b Ream the hole 6 to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A340-57-4106-1.

c Clean the drilled area.

d Do the cold working of the hole 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1.

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SERVICE BULLETIN

e Ream the hole 6 to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A340-57-4106-1.

f Clean the drilled area.

g Ream the hole 5 through all the layers to a diameter comprised between

17mm (0.6693in.) and 17.018mm (0.67in.).

h Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5.

i Protect the hole 5 with Chemical Conversion Coating Yellow Aluminum

(Mat. No. 13-002).

j Install :

1 Plug F5332433520600 Item 40

1 Bolt EN6115-6Y-10 Item 29

1 Washer NSA5372-616D Item 50

1 Nut ASNA2531-6 Item 27

NOTE(01) Install the plug Item 40 with liquid nitrogen (Refer to PMS

01-05-05).

NOTE(02) Apply Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005)

between the plug Item 40 and the structure.

NOTE(03) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(04) Apply Polyurethane Primer (Mat. No. 16-001B) andInternal Top

Coat (Mat. No. 16-002C) after assembly in the hole.

NOTE(05) Do a seal bead withCorrosion Inhibiting Fillet Consistency (Mat.

No. 09-016B) in the hole on the edge of the plug Item 40.

NOTE(06) Do a seal bead on the external edge of the plug Item 40

withFuel Tank Sealant Polysulfide (Mat. No. 09-002B) and

Adhesion Promoter For Polysulfide Sealant (Mat. No. 09-028A).

NOTE(07) Coat the nut and washer with Fuel Tank Sealant Polysulfide

(Mat. No. 09-002B).

23 Inspect holes A and 7.

Refer to Figure 6, Sheets 1 and 2

a Remove :

1 Nut Item (2) Discard

1 Nut Item (6) Discard

1 Bolt Item (1) Discard

1 Bolt Item (7) Discard

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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SERVICE BULLETIN

b Remove the sealant and clean the holes.

c Do a rotating probe inspection through all the layers of holes A and 7

(Refer to NTM 51-10-01).

- If a crack is detected, contact AIRBUS.

- If no crack is detected, do the operations given in the paragraphes

(2)(b)24 and 25.

24 Do the cold working of the hole A.

Refer to Figure 6, Sheets 1, 3 and 4

a Ream the hole A to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A340-57-4106-1.

b Clean the drilled area.

c Do the cold working of the hole A (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1.

d Ream the hole A to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A340-57-4106-1.

e Clean the drilled area.

f Install :

1 Bolt EN6115-6Y-16 Item 28

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616D Item 50

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

25 Install the fastener in hole 7.

Refer to Figure 6, Sheets 1, 3 and 4

a Oversize the hole to a diameter comprised between 7.809mm (0.307in.)

and 7.849mm (0.309in.).

b Install :

1 Bolt EN6115-5-12 Item 32

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

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SERVICE BULLETIN

or depending on the thickness of the structure :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

(c) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel

beam fasteners for aircraft with bush with a diameter < or = to 13mm (0.512in.)

installed on hole 5.

Refer to Kit 574106A03R03

Refer to Figure 7

NOTE(01) Description below is given for one side of the aircraft, two Kit

574106A03R03 are necessary to modify one aircraft.

1 Inspect the hole 5.

Refer to Figure 7, Sheets 1 and 2

a Remove :

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

1 Bush Item (5) Discard

b Remove the sealant and clean the hole.

c Do a rotating probe inspection through all the layers of hole 5 (Refer

to NTM 51-10-18).

- If no crack is detected, do the operations given in paragraph (2)(c)2.

- If a crack is detected, contact AIRBUS.

2 No crack detected at original diameter on hole 5.

Refer to Figure 7, Sheets 1 and 2

a Remove the fastener of hole 6.

- Remove:

1 Bolt Item (41) Discard

1 Nut Item (4) Discard

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 39

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A340

SERVICE BULLETIN

b Ream the hole 6 to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A340-57-4106-1.

c Clean the drilled area.

d Do the cold working of the hole 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1.

e Ream the hole 6 to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A340-57-4106-1.

f Clean the drilled area.

g Ream the hole 5 through all the layers to a diameter comprised between

15mm (0.5905in.) and 15.018mm (0.5913in.).

h Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5.

i Protect the hole 5 with Chemical Conversion Coating Yellow Aluminum

(Mat. No. 13-002).

j Install :

1 Plug F5332433520400 Item 39

1 Bolt EN6115-6Y-10 Item 29

1 Washer NSA5372-616D Item 50

1 Nut ASNA2531-6 Item 27

NOTE(01) Install the plug Item 39 with liquid nitrogen (Refer to PMS

01-05-05).

NOTE(02) Apply Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005)

between the plug Item 39 and the structure.

NOTE(03) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(04) Apply Polyurethane Primer (Mat. No. 16-001B) andInternal Top

Coat (Mat. No. 16-002C) after assembly in the hole.

NOTE(05) Do a seal bead withCorrosion Inhibiting Fillet Consistency (Mat.

No. 09-016B) in the hole on the edge of the plug Item 39.

NOTE(06) Do a seal bead on the external edge of the plug Item 39

withFuel Tank Sealant Polysulfide (Mat. No. 09-002B) and

Adhesion Promoter For Polysulfide Sealant (Mat. No. 09-028A).

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 40

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A340

SERVICE BULLETIN

NOTE(07) Coat the nut and washer with Fuel Tank Sealant Polysulfide

(Mat. No. 09-002B).

3 Inspect holes A and 7.

Refer to Figure 7, Sheets 1 and 2

a Remove :

1 Nut Item (2) Discard

1 Nut Item (6) Discard

1 Bolt Item (1) Discard

1 Bolt Item (7) Discard

b Remove the sealant and clean the holes.

c Do a rotating probe inspection through all the layers of holes A and 7

(Refer to NTM 51-10-01).

- If a crack is detected, contact AIRBUS.

- If no crack is detected, do the operations given in the paragraphes

(2)(c)4 and 5.

4 Do the cold working of the hole A.

Refer to Figure 7, Sheets 1, 3 and 4

a Ream the hole A to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A340-57-4106-1.

b Clean the drilled area.

c Do the cold working of the hole A (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1.

d Ream the hole A to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A340-57-4106-1.

e Clean the drilled area.

f Install :

1 Bolt EN6115-6Y-16 Item 28

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616D Item 50

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 41

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A340

SERVICE BULLETIN

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

5 Install the fastener in hole 7.

Refer to Figure 7, Sheets 1, 3 and 4

a Oversize the hole to a diameter comprised between 7.809mm (0.307in.)

and 7.849mm (0.309in.).

b Install :

1 Bolt EN6115-5-12 Item 32

or depending on the thickness of the structure :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

(d) On the LH and RH sides of aircraft between FR40 and STGR1, replace the keel

beam fasteners for aircraft with bush with a diameter > 13mm (0.512in.) and < or =

15mm (0.591in.) installed on hole 5.

Refer to Kit 574106A03R03

Refer to Figure 8

NOTE(01) Description below is given for one side of the aircraft, two Kit

574106A03R03 are necessary to modify one aircraft.

1 Inspect the hole 5.

Refer to Figure 8, Sheets 1 and 2

a Remove :

1 Bolt Item (3) Discard

1 Nut Item (4) Discard

1 Bush Item (5) Discard

b Remove the sealant and clean the hole.

c Do a rotating probe inspection through all the layers of hole 5 (Refer

to NTM 51-10-18).

- If no crack is detected, do the operations given in paragraph (2)(d)2.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 42

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A340

SERVICE BULLETIN

- If a crack is detected, contact AIRBUS.

2 No crack detected at original diameter for hole 5

Refer to Figure 8, Sheets 1 and 2

a Remove the fastener of hole 6.

- Remove:

1 Bolt Item (41) Discard

1 Nut Item (4) Discard

b Ream the hole 6 to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A340-57-4106-1.

c Clean the drilled area.

d Do the cold working of the hole 6 (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1.

e Ream the hole 6 to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A340-57-4106-1.

f Clean the drilled area.

g Ream the hole 5 through all the layers to a diameter comprised between

17mm (0.6693in.) and 17.018mm (0.67in.).

h Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5.

i Protect the hole with Chemical Conversion Coating Yellow Aluminum (Mat.

No. 13-002).

j Install :

1 Plug F5332433520600 Item 40

1 Bolt EN6115-6Y-10 Item 29

1 Washer NSA5372-616D Item 50

1 Nut ASNA2531-6 Item 27

NOTE(01) Install the plug Item 40 with liquid nitrogen (Refer to PMS

01-05-05).

NOTE(02) Apply Corrosion Inhibitive Interfay Sealant (Mat. No. 09-005)

between the plug Item 40 and the structure.

NOTE(03) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 43

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A340

SERVICE BULLETIN

NOTE(04) Apply Polyurethane Primer (Mat. No. 16-001B) andInternal Top

Coat (Mat. No. 16-002C) after assembly in the hole.

NOTE(05) Do a seal bead with Corrosion Inhibiting Fillet Consistency (Mat.

No. 09-016B) in the hole on the edge of the plug Item 40.

NOTE(06) Do a seal bead on the external edge of the plug Item 40

withFuel Tank Sealant Polysulfide (Mat. No. 09-002B) and

Adhesion Promoter For Polysulfide Sealant (Mat. No. 09-028A).

NOTE(07) Coat the nut and washer with Fuel Tank Sealant Polysulfide

(Mat. No. 09-002B).

3 Inspect holes A and 7.

Refer to Figure 8, Sheets 1 and 2

a Remove :

1 Nut Item (2) Discard

1 Nut Item (6) Discard

1 Bolt Item (1) Discard

1 Bolt Item (7) Discard

b Remove the sealant and clean the holes.

c Do a rotating probe inspection through all the layers of holes A and 7

(Refer to NTM 51-10-01).

- If a crack is detected, contact AIRBUS.

- If no crack is detected, do the operations given in the paragraphes

(2)(d)4 and 5.

4 Do the cold working of the hole A.

Refer to Figure 8, Sheets 1, 3 and 4

a Ream the hole A to the starting hole diameter for the cold working comprised

between 9.53mm (0.375in.) and 9.6mm (0.378in.).

Use tool list No. DK-A340-57-4106-1.

b Clean the drilled area.

c Do the cold working of the hole A (Refer to SRM 51-48-00).

Use FTI tool list kit No. FTI-A340-57-4106-1 and EK-A340-57-4106-1.

d Ream the hole A to the final hole diameter comprised between 10.177mm

(0.401in.) and 10.219mm (0.402in.).

Use tool list No. DK-A340-57-4106-1.

e Clean the drilled area.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 44

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A340

SERVICE BULLETIN

f Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02in.) on the upper side of hole 5.

g Install :

1 Bolt EN6115-6Y-16 Item 28

1 Nut ASNA2531-6 Item 27

1 Washer NSA5372-616D Item 50

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

5 Install the fastener in hole 7.

Refer to Figure 8, Sheets 1, 3 and 4

a Oversize the hole to a diameter comprised between 7.809mm (0.307in.)

and 7.849mm (0.309in.).

b Install :

1 Bolt EN6115-5-12 Item 32

or depending on the thickness of the structure :

1 Bolt EN6115-5-13 Item 51

or

1 Bolt EN6115-5-14 Item 52

1 Nut ASNA2531-5 Item 31

NOTE(01) Before installation of the fasteners, apply Corrosion Inhibiting

Brush Consistency (Mat. No. 09-013B) (wet assembly).

NOTE(02) Coat the nut with Fuel Tank Sealant Polysulfide (Mat. No.

09-002B).

(e) On the LH and RH sides, install (if removed) the ducts between FR39.1 and FR40.

Refer to Figures 1 and 2

1 Remove the blanking plugs on the disconnected line ends.

2 On LH side, install (if removed) the APU bleed air system ducts between FR39.1

and FR40 (Refer to AMM 36-12-41, Page block 401).

3 On RH side, install (if removed) the air ventilation duct.

Refer to Figure 2

a Install :

1 Duct Item (20)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 45

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

8 Clamp Item (21)

4 Clamp Item (22)

2 Sleeve Item (23)

1 Sleeve Item (24)

NOTE : Items (20) thru (24) were retained at removal.

4 On RH side, install (if removed) the air conditioning duct.

Refer to Figure 1

a Install :

1 Duct Item (8)

1 Insulation Item (9)

1 Nut Item (10)

1 Bolt Item (11)

1 Washer Item (12)

2 Screw Item (13)

2 Washer Item (14)

2 Nut Item (15)

1 Clamp Item (16)

1 Clamp Item (17)

NOTE(01) Reconnect the rod Items (18) and (19).

NOTE(02) For the installation of the sensor 542HH (Refer to AMM

21-53-18, Page block 401).

NOTE(03) Items (8) thru (17) were retained at removal.

(3) ADDITIONAL WORK

(a) Aircraft which has got the task Paragraph 3.B (1)(b) step 3 accomplished at the

original Service Bulletin issue contact AIRBUS for advise on the ADDITIONAL

WORK.

C. TEST

(1) Config. 01 thru Config. 02

(a) Preparation

1 Install the access covers 147AZ and 148AZ (Refer to AMM 57-17-11, Page

block 401).

2 Refuel the center tank (Refer to AMM 28-25-00, Page block 301).

3 Install the torque shaft assies 5010CW and 5070CW (Refer to AMM 27-84-45,

Page block 201).

4 Install the removed air-conditioning distribution ducts (Refer to AMM 21-20-00,

Page block 201).

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 46

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

(b) Tests

1 Do the test after the removal/installation of the pack discharge

temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18, Page block

401).

2 Do the test after the removal/installation of the APU bleed air ducts (Refer

to AMM 36-12-41, Page block 401).

3 Do the test after the removal/installation of the covers (147AZ and 148AZ) (Refer

to AMM 57-17-11, Page block 401).

4 Do the test after the removal/installation of the torque shaft assy (5010CW and

5070CW)(Refer to AMM 27-84-45, Page block 401).

5 Do the test after the removal/installation of the air conditioning distribution ducts

(Refer to AMM 21-20-00, Page block 201).

D. CLOSE UP

(1) Config. 01 thru Config. 02

(a) Do the close-up procedure as specified in removal/installation of the pack discharge

temperature-sensor (541HH and 542HH) (Refer to AMM 21-53-18, Page block 401).

(b) Do the close-up procedure as specified in removal/installation of the APU bleed-air

ducts (Refer to AMM 36-12-41, Page block 401).

(c) Install the access panels 191FB for the LH side and 192GB for the RH side (Refer to

AMM 53-35-13, Page block 401 and AMM 06-41-53).

(d) Close the Main Landing Gear (MLG) doors (Refer to AMM 32-12-00, Page block 201).

(e) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(f) Remove the access platform(s).

(g) Restore the systems and the aircraft to normal operating condition.

E. DOCUMENTATION

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

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 47

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 1, Sheet 1

Config. 01 thru 02 : Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40, for Access.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 48

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 2, Sheet 1

Config. 01 thru 02 : Removal/Installation of the Ventilation ducts between FR39.1 and FR40, for Access.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 49

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 1

Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 without bush)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 50

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 2

Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 without bush)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 51

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 3

Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 without bush)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 52

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 4

Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 without bush)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 53

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 4, Sheet 1

Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 54

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 4, Sheet 2

Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 55

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 4, Sheet 3

Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 56

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 4, Sheet 4

Config. 01 : Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.))

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 57

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 5, Sheet 1

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 without bush, without crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 58

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 5, Sheet 2

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 without bush, without crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 59

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 5, Sheet 3

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 without bush, without crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 60

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 5, Sheet 4

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 without bush, without crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 61

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 6, Sheet 1

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 62

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 6, Sheet 2

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 63

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 6, Sheet 3

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 64

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 6, Sheet 4

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 65

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 6, Sheet 5

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 without bush, with crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 66

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 7, Sheet 1

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.)

without crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 67

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 7, Sheet 2

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.)

without crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 68

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 7, Sheet 3

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.)

without crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 69

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 7, Sheet 4

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.)

without crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 70

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

Figure 7, Sheet 5

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 with bush dia. <or= 13mm (0.512 in.)

without crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 71

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A340

SERVICE BULLETIN

Figure 8, Sheet 1

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or =

15mm (0.591 in.)) without crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 72

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A340

SERVICE BULLETIN

Figure 8, Sheet 2

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or =

15mm (0.591 in.)) without crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 73

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A340

SERVICE BULLETIN

Figure 8, Sheet 3

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or =

15mm (0.591 in.)) without crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 74

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A340

SERVICE BULLETIN

Figure 8, Sheet 4

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or =

15mm (0.591 in.)) without crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 75

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A340

SERVICE BULLETIN

Figure 8, Sheet 5

Config. 02 : Replacement of the fasteners of the Keel Beam (hole 5 with bush 13mm (0.512 in.) <dia.< or =

15mm (0.591 in.)) without crack detected)

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 76

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 : 57

TITLE : WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL

BEAM FITTING AT FR.40

MODIFICATION No. : 56467S18944

1. REPORT

The results of the accomplishment of this Service Bulletin, including no findings, replacement or actions

to be done, must be forwarded to AIRBUS Department AI/SEES1, on the attached inspection report

sheet.

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 1

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

APPENDIX 1

Figure 1, Sheet 1

Inspection Report

DATE : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

REPORTING SHEET

TITLE : WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL

BEAM FITTING AT FR.40

MODIFICATION No. : 56467S18944

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 : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 1 of 1

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

REPORTING QUALITY

TITLE : WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION IN THE JUNCTION KEEL

BEAM FITTING AT FR.40

MODIFICATION No. : 56467S18944

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 : Aug 30/07 SERVICE BULLETIN No. : A340-57-4106

REVISION No. : 01 - Jul 31/09 Page : 1 of 1

Printed in France © AIRBUS 2008 All rights reserved