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 : 53

TITLE : FUSELAGE - REAR FUSELAGE - INTRODUCE STRUCTURAL CHANGES DUE TO EF3 TEST

RESULTS IN SECTION 19 (RETRO SOLUTION) - INSTALLATION OF REINFORCEMENT

DOUBLERS AND COLD WORKING ON FASTENER HOLES AT FR80 BETWEEN STGR 2A AND

5A AND BETWEEN FR84 - FR87 AT STGR 2 AND STGR 5 LH/RH.

MODIFICATION No. : 53222D44560

This page transmits Revision No. 01 of Service Bulletin No. A340-53-4172

ADDITIONAL WORK

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

The equivalent of this Service Bulletin has been updated to include all new information from the

validation on the A330 MSN 229.

NOTE : For the delivered kits 534172D01R03, four new nuts, with part number ASNA2528-3A have

to be ordered FOC by sending a purchase order to AIRBUS.

CHANGES

SUMMARY :

- REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Validation sentence added.

- MANPOWER

. Men hours updated.

PLANNING INFORMATION :

- REASON

- History

. 1.C.(1) Validation sentence added.

- MANPOWER

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 1 of 4

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

. 1.G. Men hours updated.

- REFERENCES

. 1.J. References updated.

MATERIAL INFORMATION :

- MATERIAL - PRICE AND AVAILABILITY

- Material

. 2.A.(1) Address for ordering updated.

- Price and Availability

. 2.A.(2) Price and availability updated.

- LIST OF COMPONENTS

. 2.C. Part Number ASNA2528-3A with item 126 added and quantity of item 50 corrected. Quantity

of the over and under size kits reduced.

ACCOMPLISHMENT INSTRUCTIONS :

- GENERAL

- Preparation

. 3.A.(1)(a)9 Removal of the Bleed Air pipe sense line added.

. 3.A.(1)(a)10 Removal of the Bleed Air pipe added.

. 3.A.(1)(a)11 Removal of Galley Ceiling added.

. 3.A.(1)(a)12 Removal of the AFT galley added.

- Standard Practices

. 3.A.(2)(k) Reference to SRM 51-46-12 spot facing of fastener holes added.

. 3.A.(2)(l) SRM reference for countersinking of fastener holes added.

. 3.A.(2)(m) Standard application for sealant added.

. 3.A.(2)(n) Standard installation of rivets, pins and collars added.

. 3.A.(2)(o) Application procedure of fillet seals added.

. 3.A.(2)(p) Standard procedure for sealant added.

. 3.A.(2)(q) Standard application of surface protection added.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 2

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- MODIFICATION

. 3.B.(1)(b) Inspection area description updated.

. 3.B.(1)(b)1 Note added.

. 3.B.(1)(c)1 Inspection area description updated.

. 3.B.(1)(d)1 Use of the SRM 51-47-00 reference clarified.

. 3.B.(1)(f)1b Countersinking of the rivet hole for rivet, item 75 added.

. 3.B.(1)(f)1f Transfer drill the fastener holes with a suitable drill bush added.

. 3.B.(1)(f)1u Final installation of the doubler and the shim transferred to the new position.

. 3.B.(1)(f)1w Nut ASNA2528-3A, item 126 added and quantity of nut ASNA2528-3, item 50

corrected.

. 3.B.(1)(f)2d Transfer drill the fastener holes using a suitable drill bush added.

. 3.B.(1)(f)2q Final installation of the doubler and the shim transferred to the new position.

. 3.B.(1)(f)2r Nut ASNA2528-3A, item 126 added and quantity of nut ASNA2528-3, item 50

corrected.

. 3.B.(1)(f)3i Transfer drill the fastener holes using a suitable drill bush added.

. 3.B.(1)(f)3s Spot facing of two fastener holes for doubler, item 3 added.

. 3.B.(1)(f)3w Final installation of the doubler and shim transferred to the new position.

. 3.B.(1)(f)4i Transfer drill using a suitable drill bush added.

. 3.B.(1)(f)4s Spot facing of two fastener holes for doubler, item 4 added.

. 3.B.(1)(f)4w Final installation of the doubler and shim transferred to the new position.

. 3.B.(1)(g)1j Transfer drill the fastener holes using a suitable drill bush added.

. 3.B.(1)(g)1w Final installation of the doubler and shim transferred to the new position.

. 3.B.(1)(g)2i Transfer drill the faster holes using a suitable drill bush added.

. 3.B.(1)(g)2v Final installation of the doubler and shim transferred to the new position.

. 3.B.(1)(g)3d Transfer drill the fastener holes using a suitable drill bush added.

. 3.B.(1)(g)3q Final installation of the doubler and shim transferred to the new position.

. 3.B.(1)(g)3r Nut ASNA2528-3A, item 126 added and quantity of nut ASNA2528-3, item 50

corrected.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 3

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

. 3.B.(1)(g)4d Transfer drill the fastener holes using a suitable drill bush added.

. 3.B.(1)(g)4q Final installation of the doubler and shim transferred to the new position.

. 3.B.(1)(g)4r Nut ASNA2528-3A, item 126 added and quantity of nut ASNA2528-3, item 50

corrected.

- CLOSE-UP

. 3.D.(1)(b) Reinstallation of the Bleed Air pipe added.

. 3.D.(1)(c) Reinstallation of the Bleed Air pipe sense line added.

. 3.D.(1)(d) Reinstallation of the galley added.

. 3.D.(1)(f) Installation of the AFT Galley Ceiling added.

- Figure 1

. Figure updated to follow the new illustration rules.

- Figure 2

. Figure updated to correct the fastener table and to follow the new illustration rules.

- Figure 3

. Minor corrections incorporated and updated to follow the new illustration rules.

- Figure 4

. Minor corrections incorporated and updated to follow the new illustration rules.

- Figure 5

. Minor corrections incorporated and updated to follow the new illustration rules.

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 : Jul 10/07

REVISION No. : 01 - Jul 08/09

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 4

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is

not approved for modification of the aircraft

MANDATORY MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 53

TITLE : FUSELAGE - REAR FUSELAGE - INTRODUCE STRUCTURAL CHANGES DUE TO EF3 TEST

RESULTS IN SECTION 19 (RETRO SOLUTION) - INSTALLATION OF REINFORCEMENT

DOUBLERS AND COLD WORKING ON FASTENER HOLES AT FR80 BETWEEN STGR 2A AND

5A AND BETWEEN FR84 - FR87 AT STGR 2 AND STGR 5 LH/RH.

MODIFICATION No. : 53222D44560

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During long life structure tests on the A340-600, damage was found in the upper shell structure between

FR84 and FR86. This damage occurred between 58341 and 72891 simulated Flight Cycles (FC). Under

consideration of the Design Service Goal (DSG) of 16600 FC for A340-600 aircraft, no action is required.

Nevertheless, due to the higher DSG of 20000 FC / 30000 FC and different design (e.g. skin thickness) for

A340-300 aircraft, this damage is considered relevant for these models.

Structure improvements have to be embodied.

The equivalent of this Service Bulletin has been validated on A330 aircraft MSN 0229.

This Service Bulletin has been issued to inform the operator to improve the upper shell structure between

FR84 and FR87 as follows :

- removal/installation of the vertical stabilizer for access reason.

NOTE : If any difficulties accrue to the removal/installation of the vertical stabilizer please contact

AIRBUS SER2 (working parties group).

- do a rototest inspection of fastener holes and a eddy current high frequency inspection between the

fastener rows in the upper shell area of FR80, FR84 and FR86.

- install new reinforcement T-doublers on the upper shell fuselage skin in the area of FR84 and FR86

between STGR5A LH and STGR5A RH,

- do a cold working with interference fit at FR80, FR84, FR85 and FR86,

- replace static electrical bonding brackets at FR84, STGR3 and FR86, STGR4 LH/RH,

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 1 of 5

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

SUMMARY

- install a system angle between FR85 and FR86 and between STGR2 and STGR3 LH/RH.

- replace a system angle between FR83 and FR84, at STGR3 LH/RH.

The accomplishment of this Service Bulletin will ensure the structural integrity of the upper shell structure

between FR84 to FR87 up the DSG of 30000 FC for A340-300 aircraft.

EVALUATION TABLE

COMPLIANCE Mandatory CANCELS INSPECTION SB No

POTENTIAL AD Yes A/C OPERATION AFFECTED No

RELIABILITY AFFECTED No PAX COMFORT AFFECTED No

COST SAVING No ETOPS AFFECTED No

STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED No

KIT PRICE (USD) See SB

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 53222D44560

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

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

are major changes.

EFFECTIVITY

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

CCA

CONCURRENT REQUIREMENTS

None

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 2

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

SUMMARY

REFERENCES/REPERCUSSIONS

TFU : None

OEB : None

AOT : None

SIL : 51-012

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

OTHERS : OIT SE999.0124/06

NATURE OF THE WORK

AIRCRAFT : Yes

EQUIPMENT : No

HARD : No

SOFT : No

OBRM : No

MANPOWER

Config. 01

TOTAL MANHOURS 185.00

ELAPSED TIME (HOURS) 91.50

NOTE : The elapsed time has been calculated as follows :

- Removal/installation of the vertical stabilizer has to be done by four mechanics in the elapsed time

of 20.00 h.

- Installation of the reinforcement doubler and cold working can be done by two mechanics in the

elapsed time of 50.00 h.

- Rototest inspection of Area A,B and C done by one mechanic in the elapsed time of 1.50 h.

- HFEC inspection of Area B and C done by one mechanic in the elapsed time of 2.50 h.

- Fastener edge clearance check done by one mechanic in the elapsed time of 1.50 h.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 3

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

SUMMARY

MATERIAL INFORMATION

AIRCRAFT DATA

Config. 01

Doublers, shims, pins, collars, rivets, bolts and nuts.

APPENDICES

None

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 4

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

SUMMARY

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 5

Printed in France © AIRBUS 2007 All rights reserved

A340

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 53

TITLE : FUSELAGE - REAR FUSELAGE - INTRODUCE STRUCTURAL CHANGES DUE TO EF3 TEST

RESULTS IN SECTION 19 (RETRO SOLUTION) - INSTALLATION OF REINFORCEMENT

DOUBLERS AND COLD WORKING ON FASTENER HOLES AT FR80 BETWEEN STGR 2A AND

5A AND BETWEEN FR84 - FR87 AT STGR 2 AND STGR 5 LH/RH.

MODIFICATION No. : 53222D44560

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

340-313

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft MSN :

0242 0243 0264

(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.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 1 of 89

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

OPERATOR MSN

CCA 0242 0243 0264

NOTE : This Service Bulletin is applicable only for A340-300 aircraft (WV027

aircraft only) on which MOD 44205D40465 has already been embodied,

and MOD 52974D44611 and 53223D44586 have NOT been embodied

in production.

(c) Effectivity by MSN and Kit/Configuration

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

0242-0243 0264

KIT No. QTY PER A/C CONFIGURATION

534172D01R04 1 01

534172D02R01 1 01

534172D03R01 1 01

NOTE(01) Kit 534172D01 should be used for the standard fastener installation.

NOTE(02) Kit 534172D02 should be used for the installation of the first oversize

fasteners, if the fasteners of kit 534172D01 do not fit.

NOTE(03) Kit 534172D03 should be used for the installation of smaller fastener, if

the fastener edge clearance of the standard fastener installation of kit

534172D01 does not match the minimum distance.

NOTE : Config. 01 is valid for all the aircraft given in the effectivity of this

Service Bulletin.

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During long life structure tests on the A340-600, damage was found in the upper shell

structure between FR84 and FR86. This damage occurred between 58341 and 72891

simulated Flight Cycles (FC). Under consideration of the Design Service Goal (DSG) of

16600 FC for A340-600 aircraft, no action is required.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 2

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Nevertheless, due to the higher DSG of 20000 FC / 30000 FC and different design (e.g.

skin thickness) for A340-300 aircraft, this damage is considered relevant for these models.

Structure improvements have to be embodied.

The equivalent of this Service Bulletin has been validated on A330 aircraft MSN 0229.

(2) Objective/Action

This Service Bulletin has been issued to inform the operator to improve the upper shell

structure between FR84 and FR87 as follows :

- removal/installation of the vertical stabilizer for access reason.

NOTE : If any difficulties accrue to the removal/installation of the vertical stabilizer

please contact AIRBUS SER2 (working parties group).

- do a rototest inspection of fastener holes and a eddy current high frequency inspection

between the fastener rows in the upper shell area of FR80, FR84 and FR86.

- install new reinforcement T-doublers on the upper shell fuselage skin in the area of FR84

and FR86 between STGR5A LH and STGR5A RH,

- do a cold working with interference fit at FR80, FR84, FR85 and FR86,

- replace static electrical bonding brackets at FR84, STGR3 and FR86, STGR4 LH/RH,

- install a system angle between FR85 and FR86 and between STGR2 and STGR3 LH/RH.

- replace a system angle between FR83 and FR84, at STGR3 LH/RH.

(3) Advantages

The accomplishment of this Service Bulletin will ensure the structural integrity of the upper

shell structure between FR84 to FR87 up the DSG of 30000 FC for A340-300 aircraft.

(4) Operational/Maintenance Consequences

This Service Bulletin is based on the aircraft configuration as known by Airbus (first aircraft

delivery configuration and modified by the reported incorporation of Airbus SBs). Prior to

Service Bulletin embodiment, the operator is reminded to pay specific attention to structural

damage which may exist and to repairs which were performed on the aircraft because they

may be affected by the Service Bulletin. Operators must verify that all allowable damage

limits and repairs performed (both in accordance with the SRM and outside of the SRM)

are still applicable and effective to the new Service Bulletin configuration. There may be

additional or modified maintenance requirements, such as temporary limits or additional

inspections, that apply with respect to the Service Bulletin configuration. Airbus disclaims

any liability for the effect which the Service Bulletin may have on repairs performed on the

aircraft before embodiment of the Service Bulletin. If the post Service Bulletin repair

status is no more covered by the SRM and for repairs outside of the SRM covered by a

RAS issued by Airbus, the operator should contact Airbus Customer Services Repair

Engineering Support (SER1). Repair review will be done by Airbus at conditions of the

Customer Services Catalogue.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 3

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

(1) Config. 01

(a) Remove the fasteners in the upper fuselage shell between FR80 and FR87.

(b) Do the Eddy Current Rotating Probe Testing of Area A FR80, Area B FR84 and

Area C FR86 to find cracks around the fastener holes.

(c) Do the eddy current high frequency inspection of Area B FR84 and Area C FR86 to

find cracks between the fastener rows.

(d) Do a check of the fastener position to make sure that the edge clearance of all

existing fastener holes is correct.

(e) Install 6 fasteners with cold working in the upper fuselage shell at FR80 between

STGR2A LH/RH and STGR5A LH/RH.

(f) Install reinforcement doublers and shims with cold working on the upper fuselage

shell at FR86.

(g) Install reinforcement doublers and shims with cold working on the upper fuselage

shell at FR84.

(h) Install fasteners with cold working in the upper fuselage skin at FR85

(i) Apply surface protection to the modification area.

E. COMPLIANCE

(1) Classification

Mandatory

(2) Accomplishment Timescale

AIRBUS recommends the accomplishment of this Service Bulletin before 14200 FC.

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

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

(EASA). It is anticipated that the AD will confirm the (thresholds and/or intervals and/or

date) given above but reference should be made to the AD for confirmation of the mandated

accomplishment timescale.

F. APPROVAL

Approved under the 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

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 4

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

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 2.00

Removal of AFT Galley 11.00

Removal of Vertical Stabilizer 32.00

Rototest inspection 1.50

HFEC inspection 2.50

Fastener Edge Clearance Check 1.50

Modification of structure at FR80 1.50

Modification of structure at FR86 42.00

Modification of structure at FR84 33.50

Modification of structure at FR85 1.50

Installation of AFT Galley 15.00

Installation of Vertical Stabilizer 28.00

Operational Test 9.00

Close-up 4.00

TOTAL MANHOURS 185.00

ELAPSED TIME (HOURS) 91.50

NOTE : The elapsed time has been calculated as follows :

- Removal/installation of the vertical stabilizer has to be done by four mechanics in the

elapsed time of 20.00 h.

- Installation of the reinforcement doubler and cold working can be done by two

mechanics in the elapsed time of 50.00 h.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 5

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

- Rototest inspection of Area A,B and C done by one mechanic in the elapsed

time of 1.50 h.

- HFEC inspection of Area B and C done by one mechanic in the elapsed time of 2.50 h.

- Fastener edge clearance check done by one mechanic in the elapsed time of 1.50 h.

H. WEIGHT AND BALANCE

Config. 01

Manufacturers Empty Weight : +5.81 kg (+12.81 lb)

Effect on Balance : +361.49 kgm (+2614.66 lb.ft)

I. ELECTRICAL LOAD DATA

Not changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) : 06-31-53 06-41-53 12-12-29 12-34-24

25-33-48 25-33-52 25-33-53 25-33-54

27-51-18 29-00-00 29-14-00 52-10-00

55-31-11

Elec. Std. Practices Manual (ESPM)

20-51-20 : 20-55-00

Service Information Letter (SIL) : 51-012

Structural Repair Manual (SRM) : 51-23-00 51-24-00 51-42-11 51-43-00

51-44-11 51-47-00 51-48-00

Non destructive Test Manual (NTM) : 51-10-01, Procedure A 51-10-08

AIRBUS Standards Manual (SM)

Consumable Materials List (CML)

K. PUBLICATIONS AFFECTED

Structural Repair Manual (SRM) : 53-51-11

L. INTERCHANGEABILITY/MIXABILITY

Not applicable

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 6

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

2. MATERIAL INFORMATION

A. MATERIAL - PRICE AND AVAILABILITY

(1) Material

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

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

AIRBUS

MATERIAL, LOGISTIC AND SUPPLIERS

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

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

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

For ordering SPARES by fax: +49 40 50 76 40 12

(2) Price and Availability

Config. 01 Kit 534172D01R04

Cost : 14240.00 US dollars

Availability : 90 calendar days from receipt of order

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

order. If you require the Kit(s) before this time, please include a retrofit planning schedule

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

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

at the issue date of the Service Bulletin.

Config. 01 Kit 534172D02R01

Cost : 9270.00 US dollars

Availability : 90 calendar days from receipt of order

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

order. If you require the Kit(s) before this time, please include a retrofit planning schedule

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

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

at the issue date of the Service Bulletin.

Config. 01 Kit 534172D03R01

Cost : 4030.00 US dollars

Availability : 90 calendar days from receipt of order

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 7

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

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

Airbus will provide a 15% percent reduction to the applicable sales prices given in paragraph 2A(2)

for orders placed before 31 December 2018.

C. LIST OF COMPONENTS

Kit 534172D01R04

NOTE : For operators having already received kit 534172D01R03, the four nuts, item 126,

with part number ASNA2528-3A have to be ordered FOC by sending a purchase

order to AIRBUS.

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

1 F5357716920000 1 DOUBLER

2 F5357716920100 1 DOUBLER

3 F5357716920200 1 DOUBLER

4 F5357716920300 1 DOUBLER

5 F5357798920000 1 SHIM

6 F5357798920100 1 SHIM

7 F5357798920200 1 SHIM

8 F5357798920300 1 SHIM

9 A5398525620600 1 ANGLE

10 F5357716921800 1 DOUBLER

11 F5357716921900 1 DOUBLER

12 F5357716922100 1 DOUBLER

13 F5357716922000 1 DOUBLER

14 F5357798921200 1 SHIM

15 F5357798921400 1 SHIM

16 F5357798921700 1 SHIM

17 F5357798921600 1 SHIM

18 DAN5-5-4 2 PIN

19 DAN5-6-3 14 PIN

20 DAN5-6-4 2 PIN

21 DAN5-6-5 10 PIN

22 DAN5-6-6 20 PIN

23 DAN5-6-7 8 PIN

24 DAN5-6-8 16 PIN

25 DAN5-6-10 8 PIN

26 DAN7-8-9 4 PIN

27 DAN7-8-10 4 PIN

28 DAN7-8-11 12 PIN

29 DAN7-10-11 8 PIN

30 DAN7-10-12 6 PIN

31 DAN7-10-17 4 PIN

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

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

32 DAN5-6-7X 4 PIN

33 DAN5-6-10X 4 PIN

34 DAN7-6-11Y 2 PIN

35 DAN7-8-13Y 6 PIN

36 DAN7-8-15Y 6 PIN

37 DAN7-8-16Y 6 PIN

38 EN6115K4Y7 20 BOLT

39 EN6115K4Y8 6 BOLT

40 EN6115K4Y10 8 BOLT

41 EN6115K4Y11 8 BOLT

42 EN6115K4Y12 14 BOLT

43 EN6115K4Y15 2 BOLT

44 EN6115K4Y16 2 BOLT

45 NSA5075-5 2 COLLAR

46 NSA5075-6 78 COLLAR

47 DAN12-6Y 2 COLLAR

48 DAN12-8 20 COLLAR

49 DAN12-10 18 COLLAR

50 ASNA2528-3 60 NUT

51 ASNA2528-4 60 NUT

52 ASNA2528-5 40 NUT

53 NSA5330-6 6 COLLAR

54 DAN12-8Y 72 COLLAR

55 DAN12-8X 2 COLLAR

56 DAN11-6X 8 COLLAR

57 DAN5-6-7Y 2 PIN

58 DAN5-6-8Y 4 PIN

59 DAN7-8-12X 2 PIN

60 DAN7-8-10Y 20 PIN

61 DAN7-8-11Y 20 PIN

62 DAN7-8-12Y 14 PIN

63 EN6115K3-3 10 BOLT

64 EN6115K3-4 10 BOLT

65 EN6115K3-5 22 BOLT

66 EN6115K3-7 10 BOLT

67 EN6115K3-8 8 BOLT

68 EN6115K5-10 8 BOLT

69 EN6115K5-11 8 BOLT

70 EN6115K5-12 8 BOLT

71 EN6115K5-17 8 BOLT

72 EN6115K5-19 8 BOLT

73 LN9198-4012CF 1 RIVET

74 LN9198-4014CF 1 RIVET

75 EN6080D5-06 1 RIVET

76 LN9198-4812CF 2 RIVET

77 LN9198-4814CF 8 RIVET

124 EN6115K3A7 2 BOLT

125 EN6115K3A8 2 BOLT

126 ASNA2528-3A 4 NUT

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SERVICE BULLETIN

NOTE : The Kit 534172D01R04 contains all fasteners for the standard installation. For

oversize fastener refer to Kit Kit 534172D02R01 and for undersize fastener refer

to Kit 534172D03R01.

NOTE : Refer to the AIRBUS Standard Manual (SM) if you find part numbers of hardware

components in the related kit(s) which you can not identify in the LIST OF

COMPONENTS of this Service Bulletin. The SM will give you the correct part number

to the part number relationship.

Kit 534172D02R01

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

20 DAN5-6-4 2 PIN

28 DAN7-8-11 2 PIN

29 DAN7-10-11 5 PIN

30 DAN7-10-12 5 PIN

32 DAN5-6-7X 5 PIN

33 DAN5-6-10X 5 PIN

46 NSA5075-6 2 COLLAR

48 DAN12-8 2 COLLAR

49 DAN12-10 5 COLLAR

50 ASNA2528-3 5 NUT

51 ASNA2528-4 4 NUT

52 ASNA2528-5 10 NUT

53 NSA5330-6 5 COLLAR

54 DAN12-8Y 2 COLLAR

55 DAN12-8X 5 COLLAR

56 DAN11-6X 5 COLLAR

57 DAN5-6-7Y 4 PIN

62 DAN7-8-12Y 2 PIN

68 EN6115K5-10 5 BOLT

69 EN6115K5-11 5 BOLT

70 EN6115K5-12 5 BOLT

78 DAN5-6-3X 5 PIN

79 DAN5-6-4X 2 PIN

80 DAN5-6-5X 5 PIN

81 DAN5-6-6X 5 PIN

82 DAN5-6-8X 5 PIN

83 DAN7-8-9X 4 PIN

84 DAN7-8-10X 4 PIN

85 DAN7-8-11X 5 PIN

86 DAN7-10-11X 5 PIN

87 DAN7-10-12X 5 PIN

88 DAN7-10-17X 4 PIN

89 DAN5-6-10Y 4 PIN

90 DAN7-10-13 5 PIN

91 DAN7-10-15 5 PIN

92 DAN7-10-16 5 PIN

93 EN6115K5-7 5 BOLT

94 EN6115K5-8 5 BOLT

95 EN6115K5-15 2 BOLT

96 EN6115K5-16 2 BOLT

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SERVICE BULLETIN

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

97 DAN12-10X 5 COLLAR

98 NSA5075-8 5 COLLAR

99 DAN5-8-7 2 PIN

100 DAN5-8-8 4 PIN

101 DAN7-10-10 5 PIN

102 EN6115K3X3 5 BOLT

103 EN6115K3X4 5 BOLT

104 EN6115K3X5 5 BOLT

105 EN6115K4-7 2 BOLT

106 EN6115K3X7 5 BOLT

107 EN6115K3X8 5 BOLT

108 EN6115K4-8 2 BOLT

109 EN6115K5X10 5 BOLT

110 EN6115K5X11 5 BOLT

111 EN6115K5X12 5 BOLT

112 EN6115K5X17 5 BOLT

113 EN6115K5X19 5 BOLT

NOTE : The Kit 534172D02R01 contains all the oversize fasteners. These oversize fasteners

should be used when the installation of the standard fasteners (Kit 534172D01R04) is

not possible anymore.

NOTE : Refer to the AIRBUS Standard Manual (SM) if you find part numbers of hardware

components in the related kit(s) which you can not identify in the LIST OF

COMPONENTS of this Service Bulletin. The SM will give you the correct part number

to the part number relationship.

Kit 534172D03R01

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

32 DAN5-6-7X 2 PIN

34 DAN7-6-11Y 5 PIN

40 EN6115K4Y10 5 BOLT

41 EN6115K4Y11 5 BOLT

42 EN6115K4Y12 5 BOLT

47 DAN12-6Y 5 COLLAR

51 ASNA2528-4 5 NUT

54 DAN12-8Y 5 COLLAR

55 DAN12-8X 5 COLLAR

56 DAN11-6X 5 COLLAR

59 DAN7-8-12X 5 PIN

61 DAN7-8-11Y 5 PIN

62 DAN7-8-12Y 5 PIN

82 DAN5-6-8X 4 PIN

84 DAN7-8-10X 5 PIN

85 DAN7-8-11X 5 PIN

114 DAN7-6-9Y 4 PIN

115 DAN7-6-10Y 2 PIN

116 DAN7-8-17Y 4 PIN

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SERVICE BULLETIN

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

117 DAN7-6-11X 2 PIN

118 DAN7-8-13X 5 PIN

119 DAN7-8-15X 5 PIN

120 DAN7-8-16X 5 PIN

121 DAN12-6X 2 COLLAR

122 EN6115K4Y17 5 BOLT

123 EN6115K4Y19 5 BOLT

NOTE : The Kit 534172D03R01 contains all the undersize fasteners. These undersize

fasteners should be used when the fastener edge clearance of the standard fastener

installation (Kit 534172D01R04) is less than required.

NOTE : Refer to the AIRBUS Standard Manual (SM) if you find part numbers of hardware

components in the related kit(s) which you can not identify in the LIST OF

COMPONENTS of this Service Bulletin. The SM will give you the correct part number

to the part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

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

MAT No.

sealant Mat. No. 09-005 As required

sealant Mat. No. 09-013 As required

sealant Mat. No. 09-016 As required

cleaning agent Mat. No. 11-026 As required

corrosion preventive Mat. No. 15-005 As required

polyurethane primer Mat. No. 16-001 As required

polyurethane top coat Mat. No. 16-018 As required

wash primer Mat. No. 16-020 As required

lint-free cloth Mat. No. 19-003 As required

(2) Components

To accomplish this Service Bulletin, it is necessary to use parts and tools listed in AMM

55-31-11.

E. PARTS TO BE RE-IDENTIFIED BY THE OPERATOR

None

F. TOOLING - PRICE AND AVAILABILITY

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

working :

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

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

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SERVICE BULLETIN

- Capital tool kit No.: FTI-A330-53-4172-1

The capital tools provided in this kit are not specific to this Service Bulletin and are normally

already available in operators’ stock as a long term investment or can be loaned from FTI.

- Durable tool kit No.: DK-A330-53-4172-1

The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the

Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one

aircraft, the number of durable kits required can be established by SIL 51-012.

- Expendable tool kit No.: EK-A330-53-4172-1

The expendable tool kit contains the quantity of expendable tools necessary to accomplish

the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which

this Service Bulletin is to be accomplished.

Operators interested in obtaining the FTI tool kits should contact :

Fatigue Technology Inc.

401 ANDOVER PARK EAST

SEATTLE, WA 98188-7605

USA

EMail: www.fatiguetech.com

Phone: +(1) 206 2462010

Fax : +(1) 206 2449886

G. SPECIAL TOOLS

None

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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.

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

IN POSITION BEFORE YOU START A TASK ON OR NEAR:

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND THE RELATED DOORS

- COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS.

CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY

SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR

MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND

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

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

NECESSARY ON WIRING AND COMPONENTS.

REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER

CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND

DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

(1) Preparation

(a) Config. 01

1 Make sure that the aircraft is electrically grounded, refer to AMM 12-34-24,

Page block 201).

2 Put the access platform(s) in position in the REAR fuselage area and at the

FWD passenger/crew doors.

3 Open the access door 312AR in the REAR fuselage area.

4 Open the FWD passenger/crew doors (1L/1R), refer to AMM 52-10-00, Page

block 201.

5 Depressurize the Green, the Blue and the Yellow hydraulic systems, refer

to AMM 29-00-00, Page block 201.

6 Depressurize the Green, the Blue and the Yellow hydraulic reservoirs, refer

to AMM 29-14-00, Page block 201.

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SERVICE BULLETIN

7 Put warning notices in position to tell persons not to pressurize the hydraulic

systems :

- in the cockpit on the hydraulic section 40VU of the overhead panel,

- on the ground service panel of each hydraulic system.

8 Open, safety and tag the circuit breaker(s) which are listed in :

- AMM 27-51-18, Page block 401.

9 Remove the Bleed Air pipe sense line between FR85 and FR87, refer to AMM

36-22-17, Page block 401.

10 Remove the Bleed Air pipe between FR85 and FR87, refer to AMM 36-12-41,

Page block 401.

11 Remove the AFT galley ceiling refer to AMM 25-33-54, Page block 401 or the

AFT galley pelmet refer to AMM 25-33-48, Page block 401.

12 If necessary remove the AFT galley, refer to AMM 25-33-52, Page block 401 and

AMM 25-33-53, Page block .

13 Remove the vertical stabilizer, as given in AMM 55-31-11, Page block 401.

(2) Standard Practices

(a) Refer to the AIRBUS Standards Manual (SM) if you find part numbers for the

hardware components in the related kit(s) which you can not identify in the LIST

OF COMPONENTS of this Service Bulletin. The SM will give you the correct part

number to part number relationship.

(b) For the specification of the consumable materials, refer to the Consumable Materials

List (CML) .

(c) For the identification of access panels, refer to AMM 06-41-53, Page block 001.

(d) For the Station/Frame (STA/FR) identification, refer to AMM 06-31-53, Page block

001.

(e) Remove old sealant with non-metallic scraper and a stiff brush.

(f) For fastener removal/installation, refer to SRM 51-42-11.

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

(h) To transfer drill holes, use a pilot drill and a drill bush.

(i) Make sure you have the correct edge clearance before you drill the holes.

(j) For alternative and substitute fasteners, refer to SRM 51-43-00.

(k) For spot facing of fastener holes refer to SRM 51-46-12.

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(l) For countersinking of fastener holes refer to SRM 51-46-11, Page block 001.

(m) Before the installation of structural items, applysealant (Mat. No. 09-005) on the

mating surfaces.

(n) Wet install rivets, pins and collars with sealant (Mat. No. 09-005).

(o) After installation of structural items, apply fillet seal around the edges withsealant

(Mat. No. 09-013) or sealant (Mat. No. 09-016).

(p) For the procedure to use sealant refer to SRM 51-24-00.

(q) After rework, apply wash primer (Mat. No. 16-020), polyurethane primer (Mat.

No. 16-001) and polyurethane top coat (Mat. No. 16-018) to the rivet heads and

tails (Refer to SRM 51-23-00).

B. MODIFICATION

(1) Config. 01

(a) Remove the fasteners in the upper fuselage shell between FR80 and FR87.

Refer to Figure 2

1 At FR80 between STGR2 LH/RH and STGR5 LH/RH remove as given in Figure

2, Sheet 1 and 3, Detail C:

6 pin DAN5-8-8 Item (39) discard

6 collar NAS5075-8 Item (51) discard

2 At FR84 at STGR3 LH/RH and at STGR6 LH/RH remove as given in Figure

2, Sheet 1 and 2, Detail B :

12 pin DAN5-6-5 Item (36) discard

8 pin DAN5-8-10 Item (40) discard

2 pin DAN5-6-7 Item (37) discard

8 pin DAN5-8-11 Item (41) discard

52 pin DAN5-8-7 Item (38) discard

4 rivet LN9198-4800CF Item (44) discard

2 rivet LN9198-4000CF Item (43) discard

14 collar NSA5075-6 Item (54) discard

68 collar NSA5075-8 Item (51) discard

1 angle A53985256206 Item (130) retain

2 angle F53577990000 Item (131) retain

3 At FR85 at STGR3 LH/RH and at STGR6 LH/RH remove as given in Figure

2, Sheet 1 and 2, Detail B :

4 pin DAN5-8-10 Item (40) discard

4 pin DAN5-8-11 Item (41) discard

4 pin DAN5-8-7 Item (38) discard

12 collar NSA5075-8 Item (51) discard

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4 At FR86 at STGR3 LH/RH and at STGR6 LH/RH remove as given in Figure

2, Sheet 1 and 2, Detail B :

16 pin DAN5-6-5 Item (36) discard

12 pin DAN5-8-11 Item (41) discard

8 pin DAN5-8-14 Item (42) discard

82 pin DAN5-8-7 Item (38) discard

4 pin DAN5-8-10 Item (40) discard

4 rivet LN9198-4800CF Item (44) discard

2 rivet LN9198-4000CF Item (43) discard

16 collar NSA5075-6 Item (54) discard

106 collar NSA5075-8 Item (51) discard

2 angle F53577990000 Item (131) retain

1 angle A53985256206 Item (132) discard

(b) Do the Eddy Current Rotating Probe Testing of Area A FR80, Area B FR84 and Area

C FR86 to find cracks around the holes of the previous removed fasteners.

Refer to Figure 5

Refer to NTM 51-10-01, Procedure A

1 Do the Eddy Current Rotating Probe Testing as per NTM 51-10-01, Procedure A

and refer to Figure 5, Sheet 1, Sheet 2, 3, 4 and Sheet 5.

NOTE : Check only the fastener holes for the fasteners which have been

removed to accomplish this modification.

a In case of no crack finding, continue with the accomplishment of the

modification.

b In case of crack finding, contact AIRBUS for repair.

(c) Do the eddy current high frequency inspection of Area B FR84 and Area C FR86 to

find cracks between the fastener rows.

Refer to Figure 5

NTM 51-10-08

1 Do a eddy current high frequency inspection from the fuselage outside, refer

to NTM 51-10-08, Page block 601 and refer to Figure 5, Sheet 1, Sheet 2, 3,

4 and Sheet 5.

a In case of no crack finding, continue with the accomplishment of the

modification.

b In case of crack finding, contact AIRBUS for repair.

CAUTION : MAKE SURE THAT THE FASTENER HOLE EDGE CLEARANCE IS

CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO

AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION AREA.

(d) Do a check of the fastener position to make sure that the edge clearance of all

existing fastener holes is correct.

Refer to Figure 1

Refer to Figure 2

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Refer to Figure 4

1 Check the edge clearance of all fastener holes from the outside and from the

inside of the fuselage shell as given in Figure 2, Sheet 1, 2 and 4. If the edge

clearance is very close for the current fasteners, try to rework the fastener holes

to keep the minimum distance to the structure edge after re-drilling to the final

fastener hole diameter as shown in Figure 1, Sheet 1 and 2. For the correct edge

clearance refer to the SRM 51-47-00. Only in the case that the fastener hole can

not be moved to keep the correct edge clearance, an undersize fastener of Kit

534172D03R01 should be installed, refer to Figure 4, Sheet 1 thru 10.

NOTE : In accordance with the SRM 51-47-00, Edge Distance for Milling

Steps, the additional distance of 1.0 mm (0.039 in) to the edge

margin for higher milling steps than 1.0 mm is not applicable for

these fastener holes.

NOTE : The installation of undersize fastener is limited by five fastener per

reinforcement bracket with a maximum of two fastener adjacent to

each other.

(e) Install 6 fasteners with cold working in the upper fuselage shell at FR80 between

STGR2A LH/RH and STGR5A LH/RH.

Refer to Kit 534172D01R04, Kit 534172D02R01

Refer to Figure 3

Refer to Figure 4

Refer to SRM 51-48-00

1 Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00, Page block 001 and Figure

4, Sheet 6.

2 Drill the fastener holes with the correct start drill as given in Figure 4, Sheet 7.

3 Ream the fastener holes with the correct start reamer as given in Figure

4, Sheet 7.

4 Expand the fastener holes as described in the SRM 51-48-00, Page block 001.

5 Ream the fastener holes with the correct gage finish reamer as given in Figure

4, Sheet 7.

6 At the FR80 in the upper fuselage install as given in Figure 3, Sheet 1 and

2, Detail C and Figure 4, Sheet 7 :

NOTE : If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables in Figure 4 to find the

correct bolt or pin with the associated nut or collar which is part

of Kit 534172D02R01.

6 bolt EN6115K4Y8 Item 39

6 nut ASNA2528-4 Item 51

or next bigger size (part of Kit 534172D02R01)

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6 bolt EN6115K5-8 Item 94

6 nut ASNA2528-5 Item 52

(f) Install reinforcement doublers and shims with cold working on the upper fuselage

shell at FR86.

Refer to Kit 534172D01R04, Kit 534172D02R01, Kit 534172D03R01

Refer to Figure 3

Refer to Figure 4,

Refer to SRM 51-47-00

Refer to SRM 51-48-00

Refer to ESPM 20-51-20

1 Install the reinforcement doublers and shims with cold working at FR86 at

STGR2B L/H.

a Clean the working area with cleaning agent (Mat. No. 11-026) and remove

parts of sealant from the structure corners to get a perfect fit of the shim,

item 5 and the doubler, item 1 to the fuselage structure.

b Countersink (100 DEG) the rivet hole, previously used to fit the angle, item

(132), as given on Figure 3, Sheet 3.

c Close one rivet hole, previously used to fit the angle, item (132), as given on

Figure 3, Sheet 3 and 4 and Figure 4, Sheet 6 with :

1 rivet EN6080D5-06 Item 75

NOTE : Install the rivet, item 75, with sealant (Mat. No. 09-005).

d Put the shim, item 5 and the doubler, item 1 in the final position on the

fuselage structure as given in Figure 3, Sheet 3.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

e Transfer drill the pilot holes from the shim, item 5 and from the doubler, item

1 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

f Transfer drill the existing fastener holes from the fuselage structure to the

doubler, item 1, using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

g Mark the fastener holes with a soft felt pen which have to be expand by cold

working, refer to Figure 3, Sheet 4.

h Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00, Page block 001 for cold

working and Figure 4, Sheet 1 thru 10 for all fastener holes.

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i Check the edge clearance of the fastener holes as described in paragraph

(1) (d) 1 to define the correct fastener dimension, refer to SRM 51-47-00.

If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 534172D01R04, use a smaller fastener (part of Kit

534172D03R01) as given in the fastener table in Figure 4, Sheet 1 thru 10 .

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

j Drill the marked fastener holes for cold working with the correct start drill, as

given in Figure 4, Sheet 7 thru 10.

k Ream the marked fastener holes for cold working with the correct start

reamer, as given in Figure 4, Sheet 7 thru 10.

l Expand the marked fastener holes in accordance with the SRM 51-48-00,

Page block 001.

m Ream the marked fastener holes with the correct gage finish reamer, as

given in Figure 4, Sheet 7 thru 10.

n Put the angle, item 9, in position, as given in Figure 3, Sheet 3.

o Check the edge clearance of the unmarked fastener holes as described in

paragraph (1) (d) 1 to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 534172D01R04, use a smaller fastener

(part of Kit 534172D03R01) as given in the fastener table in Figure 4,

Sheet 1 thru 10 .

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

p Drill the unmarked fastener holes to the correct dimension as given in Figure

3, Sheet 4 and Figure 4, Sheet 1 thru 5.

q Remove the angle, item 9, from the fuselage skin.

r Remove the doubler, item 1 and the shim, item 5 from the fuselage structure.

s Deburr the fastener holes.

t Clean the shim, item 5, the doubler, item 1 and the fuselage structure with

cleaning agent (Mat. No. 11-026).

u With sealant (Mat. No. 09-005) to the mating surfaces and screw pins install

as shown on Figure 3, Sheet 3 :

1 doubler F5357716920000 Item 1

1 shim F5357798920000 Item 5

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A340

SERVICE BULLETIN

v Put in position, with sealant (Mat. No. 09-005) and secured with screw

pins, as given in Figure 3, Sheet 3 :

1 angle A5398525620600 Item 9

w To the fuselage skin, the doubler, item 1 and the shim, item 5, install with

sealant (Mat. No. 09-005), as given in Figure 3, Sheet 4 and Figure 4,

Sheet 1 thru 10 :

NOTE : If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables in Figure 4 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 534172D02R01.

NOTE : For the following fasteners, refer to Figure 4, Sheet 1.

2 pin DAN5-5-4 Item 18

3 pin DAN5-6-3 Item 19

2 pin DAN5-6-5 Item 21

4 pin DAN5-6-6 Item 22

2 pin DAN5-6-8 Item 24

NOTE : For the following fasteners, refer to Figure 4, Sheet 2.

1 pin DAN7-8-9 Item 26

1 pin DAN7-8-10 Item 27

2 pin DAN7-8-11 Item 28

4 pin DAN7-10-11 Item 29

NOTE : For the following fasteners, refer to Figure 4, Sheet 3.

3 pin DAN7-10-12 Item 30

2 pin DAN7-10-17 Item 31

NOTE : For the following fasteners, refer to Figure 4, Sheet 5.

1 pin DAN5-6-7Y Item 57

2 pin DAN5-6-8Y Item 58

2 pin DAN7-8-10Y Item 60

2 pin DAN7-8-11Y Item 61

NOTE : For the following fasteners, refer to Figure 4, Sheet 6.

1 pin DAN7-8-12Y Item 62

NOTE : For the following fasteners, refer to Figure 4, Sheet 7.

3 bolt EN6115K4Y7 Item 38

2 bolt EN6115K4Y10 Item 40

2 bolt EN6115K4Y11 Item 41

6 bolt EN6115K4Y12 Item 42

NOTE : For the following fasteners, refer to Figure 4, Sheet 8.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

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A340

SERVICE BULLETIN

2 bolt EN6115K3-3 Item 63

2 bolt EN6115K3-4 Item 64

2 bolt EN6115K3-5 Item 65

1 bolt EN6115K3A7 Item 124

NOTE : For the following fasteners, refer to Figure 4, Sheet 9.

4 bolt EN6115K5-17 Item 71

with

4 nut ASNA2528-5 Item 52

13 nut ASNA2528-4 Item 51

6 nut ASNA2528-3 Item 50

5 collar DAN12-8Y Item 54

11 collar NSA5075-6 Item 46

3 collar NSA5330-6 Item 53

2 collar NSA5075-5 Item 45

4 collar DAN12-8 Item 48

9 collar DAN12-10 Item 49

1 nut ASNA2528-3A Item 126

x Clean the repair area with cleaning agent (Mat. No. 11-026) and lint-free

cloth (Mat. No. 19-003).

2 Install the reinforcement doublers and shims with cold working at FR86 at

STGR2B R/H.

a Clean the working area with cleaning agent (Mat. No. 11-026) and remove

parts of sealant from the structure corners to get a perfect fit of the shim,

item 6 and the doubler, item 2 to the fuselage structure.

b Put the shim, item 6 and the doubler, item 2 in the final position on the

fuselage structure as given in Figure 3, Sheet 5.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

c Transfer drill the pilot holes from the shim, item 6 and from the doubler, item

2 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

d Transfer drill the fastener holes from the fuselage structure to the doubler,

item 2, using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

e Mark the fastener holes with a soft felt pen which have to be expand by cold

working, refer to Figure 3, Sheet 6.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 23

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A340

SERVICE BULLETIN

f Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00, Page block 001 for cold

working and Figure 4, Sheet 1 thru 10 for all fastener holes.

g Check the edge clearance of the fastener holes as described in paragraph

(1) (d) 1 to define the correct fastener dimension, refer to SRM 51-47-00.

If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 534172D01R04, use a smaller fastener (part of Kit

534172D03R01) as given in the fastener table in Figure 4, Sheet 1 thru 10 .

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

h Drill the marked fastener holes for cold working with the correct start drill, as

given in Figure 4, Sheet 7 thru 10.

i Ream the marked fastener holes for cold working with the correct start

reamer, as given in Figure 4, Sheet 7 thru 10.

j Expand the marked fastener holes in accordance with the SRM 51-48-00,

Page block 001.

k Ream the marked fastener holes with the correct gage finish reamer, as

given in Figure 4, Sheet 7 thru 10.

l Check the edge clearance of the unmarked fastener holes as described in

paragraph (1) (d) 1 to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 534172D01R04, use a smaller fastener

(part of Kit 534172D03R01) as given in the fastener table in Figure 4,

Sheet 1 thru 10 .

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

m Drill the unmarked fastener holes to the correct dimension as given in Figure

3, Sheet 6 and Figure 4, Sheet 1 thru 6.

n Remove the doubler, item 2 and the shim, item 6 from the fuselage structure.

o Deburr the fastener holes.

p Clean the shim, item 6, the doubler, item 2 and the fuselage structure with

cleaning agent (Mat. No. 11-026).

q With sealant (Mat. No. 09-005) to the mating surfaces and screw pins install

as shown on Figure 3, Sheet 5 :

1 doubler F5357716920100 Item 2

1 shim F5357798920100 Item 6

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 24

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A340

SERVICE BULLETIN

r To the fuselage skin, the doubler, item 2 and the shim, item 6, install with

sealant (Mat. No. 09-005), as given in Figure 3, Sheet 6 and Figure 4,

Sheet 1 thru 10 :

NOTE : If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables in Figure 4 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 534172D02R01.

NOTE : For the following fasteners, refer to Figure 4, Sheet 1.

5 pin DAN5-6-3 Item 19

2 pin DAN5-6-5 Item 21

4 pin DAN5-6-6 Item 22

2 pin DAN5-6-8 Item 24

NOTE : For the following fasteners, refer to Figure 4, Sheet 2.

1 pin DAN7-8-9 Item 26

1 pin DAN7-8-10 Item 27

2 pin DAN7-8-11 Item 28

NOTE : For the following fasteners, refer to Figure 4, Sheet 3.

4 pin DAN7-10-11 Item 29

3 pin DAN7-10-12 Item 30

2 pin DAN7-10-17 Item 31

NOTE : For the following fasteners, refer to Figure 4, Sheet 5.

1 pin DAN5-6-7Y Item 57

2 pin DAN5-6-8Y Item 58

2 pin DAN7-8-10Y Item 60

2 pin DAN7-8-11Y Item 61

NOTE : For the following fasteners, refer to Figure 4, Sheet 6.

1 pin DAN7-8-12Y Item 62

NOTE : For the following fasteners, refer to Figure 4, Sheet 7.

3 bolt EN6115K4Y7 Item 38

2 bolt EN6115K4Y10 Item 40

2 bolt EN6115K4Y11 Item 41

6 bolt EN6115K4Y12 Item 42

NOTE : For the following fasteners, refer to Figure 4, Sheet 8.

2 bolt EN6115K3-3 Item 63

2 bolt EN6115K3-4 Item 64

2 bolt EN6115K3-5 Item 65

1 bolt EN6115K3A7 Item 124

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A340

SERVICE BULLETIN

NOTE : For the following fasteners, refer to Figure 4, Sheet 9.

4 bolt EN6115K5-17 Item 71

with

4 nut ASNA2528-5 Item 52

13 nut ASNA2528-4 Item 51

6 nut ASNA2528-3 Item 50

5 collar DAN12-8Y Item 54

13 collar NSA5075-6 Item 46

3 collar NSA5330-6 Item 53

4 collar DAN12-8 Item 48

9 collar DAN12-10 Item 49

1 nut ASNA2528-3A Item 126

s Clean the repair area with cleaning agent (Mat. No. 11-026) and lint-free

cloth (Mat. No. 19-003).

3 Install the reinforcement doublers and shims with cold working at FR86 at

STGR5A L/H.

a Clean the working area with cleaning agent (Mat. No. 11-026) and remove

parts of sealant from the structure corners to get a perfect fit of the shim,

item 7 and the doubler, item 3 to the fuselage structure.

b Mark the new hole for the angle, item (131) as shown on Figure 3, Sheet 7,

Detail J.

c Drill with a 4.8 mm (0.19 in.) DIA drill the new hole with the angle, item (131).

d Remove the angle, item (131) from the fuselage skin and deburr the rivet

hole.

e Remove the surface protection around the rivet holes of angle, item (131),

for electrical bonding.

f With sealant (Mat. No. 09-005) to the mating surfaces install as shown on

Figure 3, Sheet 7 and Sheet 8 and Figure 4, Sheet 6 :

1 angle F53577990000 Item (131) retained

1 rivet LN9198-4812CF Item 76

2 rivet LN9198-4814CF Item 77

NOTE : Install the angle, item (131), as electrical bonding point, refer to

ESPM 20-51-20.

g Put the shim, item 7 and the doubler, item 3 in the final position on the

fuselage structure as given in Figure 3, Sheet 7.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 26

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A340

SERVICE BULLETIN

h Transfer drill the pilot holes from the shim, item 7 and from the doubler, item

3 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

i Transfer drill the fastener holes from the fuselage structure to the doubler,

item 3, using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

j Mark the fastener holes which have to be expand by cold working with a soft

felt pen, refer to Figure 3, Sheet 8.

k Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00, Page block 001 for cold

working and Figure 4, Sheet 1 thru 10 for all fastener holes.

l Check the edge clearance of the fastener holes as described in paragraph

(1) (d) 1 to define the correct fastener dimension, refer to SRM 51-47-00.

If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 534172D01R04, use a smaller fastener (part of Kit

534172D03R01) as given in the fastener table in Figure 4, Sheet 1 thru 10 .

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

m Drill the marked fastener holes for cold working with the correct start drill, as

given in Figure 4, Sheet 7 thru 10.

n Ream the marked fastener holes for cold working with the correct start

reamer, as given in Figure 4, Sheet 7 thru 10.

o Expand the marked fastener holes in accordance with the SRM 51-48-00,

Page block 001.

p Ream the marked fastener holes with the correct gage finish reamer, as

given in Figure 4, Sheet 7 thru 10.

q Check the edge clearance of the unmarked fastener holes as described in

paragraph (1) (d) 1 to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 534172D01R04, use a smaller fastener

(part of Kit 534172D03R01) as given in the fastener table in Figure 4,

Sheet 1 thru 10 .

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

r Drill the unmarked fastener holes to the correct dimension as given in Figure

3, Sheet 8 and Figure 4, Sheet 1 thru 6.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 27

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A340

SERVICE BULLETIN

s Do a spot facing of two fastener holes to a diameter of 13 mm (0.51 in)

to maximum of 16 mm (0.63 in) on the doubler, item 3 located at FR86

as shown on Figure 3, Sheet 8.

t Remove the doubler, item 3 and the shim, item 7 from the fuselage structure.

u Deburr the fastener holes.

v Clean the shim, item 7, the doubler, item 3 and the fuselage structure with

cleaning agent (Mat. No. 11-026).

w With sealant (Mat. No. 09-005) to the mating surfaces and screw pins install

as shown on Figure 3, Sheet 7 :

1 doubler F5357716920200 Item 3

1 shim F5357798920200 Item 7

x To the fuselage skin, the doubler, item 3 and the shim, item 7, install with

sealant (Mat. No. 09-005), as given in Figure 3, Sheet 8 and Figure 4,

Sheet 1 thru 10 :

NOTE : If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables in Figure 4 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 534172D02R01.

NOTE : For the following fasteners, refer to Figure 4, Sheet 1.

3 pin DAN5-6-3 Item 19

1 pin DAN5-6-4 Item 20

3 pin DAN5-6-5 Item 21

6 pin DAN5-6-6 Item 22

3 pin DAN5-6-8 Item 24

NOTE : For the following fasteners, refer to Figure 4, Sheet 2.

1 pin DAN7-8-9 Item 26

1 pin DAN7-8-10 Item 27

1 pin DAN7-8-11 Item 28

NOTE : For the following fasteners, refer to Figure 4, Sheet 7.

5 bolt EN6115K4Y7 Item 38

1 bolt EN6115K4Y12 Item 42

NOTE : For the following fasteners, refer to Figure 4, Sheet 8.

3 bolt EN6115K3-3 Item 63

1 bolt EN6115K3-4 Item 64

3 bolt EN6115K3-5 Item 65

NOTE : For the following fasteners, refer to Figure 4, Sheet 9.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 28

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A340

SERVICE BULLETIN

4 bolt EN6115K5-10 Item 68

4 bolt EN6115K5-11 Item 69

4 bolt EN6115K5-12 Item 70

NOTE : For the following fasteners, refer to Figure 4, Sheet 10.

4 bolt EN6115K5-19 Item 72

with

3 collar DAN12-8 Item 48

6 nut ASNA2528-4 Item 51

7 nut ASNA2528-3 Item 50

16 nut ASNA2528-5 Item 52

16 collar NSA5075-6 Item 46

y Clean the repair area with cleaning agent (Mat. No. 11-026) and lint-free

cloth (Mat. No. 19-003).

4 Install the reinforcement doublers and shims with cold working at FR86 at

STGR5A R/H.

a Clean the working area with cleaning agent (Mat. No. 11-026) and remove

parts of sealant from the structure corners to get a perfect fit of the shim,

item 8 and the doubler, item 4 to the fuselage structure.

b Mark the new hole for the angle, item (131) as shown on Figure 3, Sheet 7,

Detail J.

c Drill with a 4.8 (0.19 in.) mm DIA drill the new hole with the angle, item (131).

d Remove the angle, item (131) from the fuselage skin and deburr the rivet

hole.

e Remove the surface protection around the rivet holes of the angle, item

(131) for electrical bonding.

f With sealant (Mat. No. 09-005) to the mating surfaces install as shown on

Figure 3, Sheet 7 and Sheet 8 and Figure 4, Sheet 6 :

1 angle F53577990000 Item (131) retained

1 rivet LN9198-4812CF Item 76

2 rivet LN9198-4814CF Item 77

NOTE : Install the angle, item (131) as electrical bonding point, refer to

ESPM 20-51-20.

g Put the shim, item 8 and the doubler, item 4 in the final position on the

fuselage structure as given in Figure 3, Sheet 7.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 29

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A340

SERVICE BULLETIN

h Transfer drill the pilot holes from the shim, item 8 and from the doubler, item

4 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

i Transfer drill the fastener holes from the fuselage structure to the doubler,

item 4, using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

j Mark the fastener holes which have to be expand by cold working with a soft

felt pen, refer to Figure 3, Sheet 8.

k Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00, Page block 001 for cold

working and Figure 4, Sheet 1 thru 10 for all fastener holes.

l Check the edge clearance of the fastener holes as described in paragraph

(1) (d) 1 to define the correct fastener dimension, refer to SRM 51-47-00.

If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 534172D01R04, use a smaller fastener (part of Kit

534172D03R01) as given in the fastener table in Figure 4, Sheet 1 thru 10 .

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

m Drill the marked fastener holes for cold working with the correct start drill, as

given in Figure 4, Sheet 7 thru 10.

n Ream the marked fastener holes for cold working with the correct start

reamer, as given in Figure 4, Sheet 7 thru 10.

o Expand the marked fastener holes in accordance with the SRM 51-48-00,

Page block 001.

p Ream the marked fastener holes with the correct gage finish reamer, as

given in Figure 4, Sheet 7 thru 10.

q Check the edge clearance of the unmarked fastener holes as described in

paragraph (1) (d) 1 to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 534172D01R04, use a smaller fastener

(part of Kit 534172D03R01) as given in the fastener table in Figure 4,

Sheet 1 thru 10 .

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

r Drill the unmarked fastener holes to the correct dimension as given in Figure

3, Sheet 8 and Figure 4, Sheet 1 thru 6.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 30

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A340

SERVICE BULLETIN

s Do a spot facing of two fastener holes to a diameter of 13 mm (0.51 in)

to maximum of 16 mm (0.63 in) on the doubler, item 4 located at FR86

as shown on Figure 3, Sheet 8.

t Remove the doubler, item 4 and the shim, item 8 from the fuselage structure.

u Deburr the fastener holes.

v Clean the shim, item 8, the doubler, item 4 and the fuselage structure with

cleaning agent (Mat. No. 11-026).

w With sealant (Mat. No. 09-005) to the mating surfaces and screw pins install

as shown on Figure 3, Sheet 7 :

1 doubler F5357716920300 Item 4

1 shim F5357798920300 Item 8

x To the fuselage skin, the doubler, item 4 and the shim, item 8, install with

sealant (Mat. No. 09-005), as given in Figure 3, Sheet 8 and Figure 4,

Sheet 1 thru 10 :

NOTE : If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables in Figure 4 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 534172D02R01.

NOTE : For the following fasteners, refer to Figure 4, Sheet 1.

3 pin DAN5-6-3 Item 19

1 pin DAN5-6-4 Item 20

3 pin DAN5-6-5 Item 21

6 pin DAN5-6-6 Item 22

3 pin DAN5-6-8 Item 24

NOTE : For the following fasteners, refer to Figure 4, Sheet 2.

1 pin DAN7-8-9 Item 26

1 pin DAN7-8-10 Item 27

1 pin DAN7-8-11 Item 28

NOTE : For the following fasteners, refer to Figure 4, Sheet 7.

5 bolt EN6115K4Y7 Item 38

1 bolt EN6115K4Y12 Item 42

NOTE : For the following fasteners, refer to Figure 4, Sheet 8.

3 bolt EN6115K3-3 Item 63

1 bolt EN6115K3-4 Item 64

3 bolt EN6115K3-5 Item 65

NOTE : For the following fasteners, refer to Figure 4, Sheet 9.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 31

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A340

SERVICE BULLETIN

4 bolt EN6115K5-10 Item 68

4 bolt EN6115K5-11 Item 69

4 bolt EN6115K5-12 Item 70

NOTE : For the following fasteners, refer to Figure 4, Sheet 10.

4 bolt EN6115K5-19 Item 72

with

6 nut ASNA2528-4 Item 51

3 collar DAN12-8 Item 48

16 nut ASNA2528-5 Item 52

7 nut ASNA2528-3 Item 50

16 collar NSA5075-6 Item 46

y Clean the repair area with cleaning agent (Mat. No. 11-026) and lint-free

cloth (Mat. No. 19-003).

(g) Install reinforcement doublers and shims with cold working on the upper fuselage

shell at FR84.

Refer to Kit 534172D01R04, Kit 534172D02R01, Kit 534172D03R01

Refer to Figure 3

Refer to Figure 4,

Refer to SRM 51-47-00

Refer to SRM 51-48-00

Refer to ESPM 20-51-20

1 Install the reinforcement doublers and shims with cold working at FR84 at

STGR2A L/H.

a Clean the working area with cleaning agent (Mat. No. 11-026) and remove

parts of sealant from the structure corners to get a perfect fit of the shim,

item 10 and the doubler, item 14 to the fuselage structure.

b Mark the new holes for the angles, item (130) and (131) as shown on

Figure 3, Sheet 9, Detail N.

c Drill with a 4.1 mm (0.16 in.) DIA drill the new holes with the angle, item

(130).

d Drill with a 4.8 (0.19 in.) mm DIA drill the new holes with the angle, item

(131).

e Remove the angles, item (130) and (131) from the fuselage skin and deburr

the rivet holes.

f Remove the surface protection around the rivet holes of the angle, item

(131), for electrical bonding.

g With sealant (Mat. No. 09-005) to the mating surfaces install as shown on

Figure 3, Sheet 9 and Sheet 10 and Figure 4, Sheet 6 :

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 32

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A340

SERVICE BULLETIN

1 angle A5398525620600 Item (130) retained

1 angle F5357799000000 Item (131) retained

1 rivet LN9198-4012CF Item 73

1 rivet LN9198-4014CF Item 74

2 rivet LN9198-4814CF Item 77

NOTE : Install the angle, item (131) as electrical bonding point, refer

to ESPM 20-51-20.

h Put the shim, item 14 and the doubler, item 10 in the final position on the

fuselage structure as given in Figure 3, Sheet 9.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

i Transfer drill the pilot holes from the shim, item 14 and from the doubler, item

10 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

j Transfer drill the fastener holes from the fuselage structure to the doubler,

item 10 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

k Mark the fastener holes which have to be expand by cold working with a soft

felt pen, refer to Figure 3, Sheet 10.

l Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00, Page block 001 for cold

working and Figure 4, Sheet 1 thru 10 for all fastener holes.

m Check the edge clearance of the fastener holes as described in paragraph

(1) (d) 1 to define the correct fastener dimension, refer to SRM 51-47-00.

If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 534172D01R04, use a smaller fastener (part of Kit

534172D03R01) as given in the fastener table in Figure 4, Sheet 1 thru 10 .

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

n Drill the marked fastener holes for cold working with the correct start drill, as

given in Figure 4, Sheet 7 thru 10.

o Ream the marked fastener holes for cold working with the correct start

reamer, as given in Figure 4, Sheet 7 thru 10.

p Expand the marked fastener holes in accordance with the SRM 51-48-00,

Page block 001.

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A340

SERVICE BULLETIN

q Ream the marked fastener holes with the correct gage finish reamer, as

given in Figure 4, Sheet 7 thru 10.

r Check the edge clearance of the unmarked fastener holes as described in

paragraph (1) (d) 1 to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 534172D01R04, use a smaller fastener

(part of Kit 534172D03R01) as given in the fastener table in Figure 4,

Sheet 1 thru 10 .

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

s Drill the unmarked fastener holes to the correct dimension as given in Figure

3, Sheet 10 and Figure 4, Sheet 1 thru 6.

t Remove the doubler, item 10 and the shim, item 14 from the fuselage

structure.

u Deburr the fastener holes.

v Clean the shim, item 14, the doubler, item 10 and the fuselage structure with

cleaning agent (Mat. No. 11-026).

w With sealant (Mat. No. 09-005) to the mating surfaces and screw pins install

as shown on Figure 3, Sheet 9 :

1 doubler F5357716921800 Item 10

1 shim F5357798921200 Item 14

x To the fuselage skin, the doubler, item 10 and the shim, item 14, install with

sealant (Mat. No. 09-005), as given in Figure 3, Sheet 10 and Figure 4,

Sheet 1 thru 10 :

NOTE : If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables in Figure 4 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 534172D02R01.

NOTE : For the following fasteners, refer to Figure 4, Sheet 1.

1 pin DAN5-6-7 Item 23

2 pin DAN5-6-8 Item 24

NOTE : For the following fasteners, refer to Figure 4, Sheet 2.

2 pin DAN5-6-10 Item 25

1 pin DAN7-8-11 Item 28

NOTE : For the following fasteners, refer to Figure 4, Sheet 3.

2 pin DAN5-6-7X Item 32

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

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A340

SERVICE BULLETIN

1 pin DAN5-6-10X Item 33

NOTE : For the following fasteners, refer to Figure 4, Sheet 4.

1 pin DAN7-6-11Y Item 34

3 pin DAN7-8-15Y Item 36

NOTE : For the following fasteners, refer to Figure 4, Sheet 5.

4 pin DAN7-8-10Y Item 60

4 pin DAN7-8-11Y Item 61

NOTE : For the following fasteners, refer to Figure 4, Sheet 6.

5 pin DAN7-8-12Y Item 62

NOTE : For the following fasteners, refer to Figure 4, Sheet 7.

1 bolt EN6115K4Y15 Item 43

NOTE : For the following fasteners, refer to Figure 4, Sheet 8.

1 bolt EN6115K3-4 Item 64

3 bolt EN6115K3-5 Item 65

3 bolt EN6115K3-7 Item 66

2 bolt EN6115K3-8 Item 67

with

5 collar NSA5075-6 Item 46

1 collar DAN12-6Y Item 47

1 collar DAN12-8 Item 48

9 nut ASNA2528-3 Item 50

1 nut ASNA2528-4 Item 51

16 collar DAN12-8Y Item 54

3 collar DAN11-6X Item 56

y Clean the repair area with cleaning agent (Mat. No. 11-026) and lint-free

cloth (Mat. No. 19-003).

2 Install the reinforcement doublers and shims with cold working at FR84 at

STGR2A R/H.

a Clean the working area with cleaning agent (Mat. No. 11-026) and remove

parts of sealant from the structure corners to get a perfect fit of the shim,

item 11 and the doubler, item 15 to the fuselage structure.

b Mark the new holes for the angle, item (131) as shown on Figure 3, Sheet

11, Detail R.

c Drill with a 4.8 (0.19 in.) mm DIA drill the new holes with the angle, item

(131).

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

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SERVICE BULLETIN

d Remove the angle, item (131) from the fuselage skin and deburr the rivet

holes.

e Remove the surface protection around the rivet holes of the angle, item

(131), for electrical bonding.

f With sealant (Mat. No. 09-005) to the mating surfaces install as shown on

Figure 3, Sheet 11 and Sheet 12 and Figure 4, Sheet 6 :

1 angle F5357799000000 Item (131) retained

2 rivet LN9198-4814CF Item 77

NOTE : Install the angle, item (131), as bonding point, refer to ESPM

20-51-20.

g Put the shim, item 15 and the doubler, item 11 in the final position on the

fuselage structure as given in Figure 3, Sheet 11.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

h Transfer drill the pilot holes from the shim, item 15 and from the doubler, item

11 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

i Transfer drill the fastener holes from the fuselage structure to the doubler,

item 11 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

j Mark the fastener holes which have to be expand by cold working with a soft

felt pen, refer to Figure 3, Sheet 12.

k Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00, Page block 001 for cold

working and Figure 4, Sheet 1 thru 10 for all fastener holes.

l Check the edge clearance of the fastener holes as described in paragraph

(1) (d) 1 to define the correct fastener dimension, refer to SRM 51-47-00.

If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 534172D01R04, use a smaller fastener (part of Kit

534172D03R01) as given in the fastener table in Figure 4, Sheet 1 thru 10 .

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

m Drill the marked fastener holes for cold working with the correct start drill, as

given in Figure 4, Sheet 7 thru 10.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

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A340

SERVICE BULLETIN

n Ream the marked fastener holes for cold working with the correct start

reamer, as given in Figure 4, Sheet 7 thru 10.

o Expand the marked fastener holes in accordance with the SRM 51-48-00,

Page block 001.

p Ream the marked fastener holes with the correct gage finish reamer, as

given in Figure 4, Sheet 7 thru 10.

q Check the edge clearance of the unmarked fastener holes as described in

paragraph (1) (d) 1 to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 534172D01R04, use a smaller fastener

(part of Kit 534172D03R01) as given in the fastener table in Figure 4,

Sheet 1 thru 10 .

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

r Drill the unmarked fastener holes to the correct dimension as given in Figure

3, Sheet 12 and Figure 4, Sheet 1 thru 6.

s Remove the doubler, item 11 and the shim, item 15 from the fuselage

structure.

t Deburr the fastener holes.

u Clean the shim, item 15, the doubler, item 11 and the fuselage structure with

cleaning agent (Mat. No. 11-026).

v With sealant (Mat. No. 09-005) to the mating surfaces and screw pins install

as shown on Figure 3, Sheet 11 :

1 doubler F5357716921900 Item 11

1 shim F5357798921400 Item 15

w To the fuselage skin, the doubler, item 11 and the shim, item 15, install with

sealant (Mat. No. 09-005), as given in Figure 3, Sheet 12 and Figure 4,

Sheet 1 thru 10 :

NOTE : If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables in Figure 4 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 534172D02R01.

NOTE : For the following fasteners, refer to Figure 4, Sheet 1.

1 pin DAN5-6-7 Item 23

2 pin DAN5-6-8 Item 24

NOTE : For the following fasteners, refer to Figure 4, Sheet 2.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

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A340

SERVICE BULLETIN

2 pin DAN5-6-10 Item 25

1 pin DAN7-8-11 Item 28

NOTE : For the following fasteners, refer to Figure 4, Sheet 3.

1 pin DAN5-6-10X Item 33

2 pin DAN5-6-7X Item 32

NOTE : For the following fasteners, refer to Figure 4, Sheet 4.

1 pin DAN7-6-11Y Item 34

3 pin DAN7-8-15Y Item 36

NOTE : For the following fasteners, refer to Figure 4, Sheet 5.

4 pin DAN7-8-10Y Item 60

4 pin DAN7-8-11Y Item 61

NOTE : For the following fasteners, refer to Figure 4, Sheet 6.

5 pin DAN7-8-12Y Item 62

NOTE : For the following fasteners, refer to Figure 4, Sheet 7.

1 bolt EN6115K4Y15 Item 43

NOTE : For the following fasteners, refer to Figure 4, Sheet 8.

1 bolt EN6115K3-4 Item 64

3 bolt EN6115K3-5 Item 65

3 bolt EN6115K3-7 Item 66

2 bolt EN6115K3-8 Item 67

with

5 collar NSA5075-6 Item 46

1 collar DAN12-6Y Item 47

1 collar DAN12-8 Item 48

9 nut ASNA2528-3 Item 50

1 nut ASNA2528-4 Item 51

16 collar DAN12-8Y Item 54

3 collar DAN11-6X Item 56

x Clean the repair area with cleaning agent (Mat. No. 11-026) and lint-free

cloth (Mat. No. 19-003).

3 Install the reinforcement doublers and shims with cold working at FR84 at

STGR5A L/H.

a Clean the working area with cleaning agent (Mat. No. 11-026) and remove

parts of sealant from the structure corners to get a perfect fit of the shim,

item 13 and the doubler, item 17 to the fuselage structure.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

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A340

SERVICE BULLETIN

b Put the shim, item 17 and the doubler, item 13 in the final position on the

fuselage structure as given in Figure 3, Sheet 13.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

c Transfer drill the pilot holes from the shim, item 17 and from the doubler, item

13 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

d Transfer drill the fastener holes from the fuselage structure to the doubler,

item 13 with a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

e Mark the fastener holes which have to be expand by cold working with a soft

felt pen, refer to Figure 3, Sheet 14.

f Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00, Page block 001 for cold

working and Figure 4, Sheet 1 thru 10 for all fastener holes.

g Check the edge clearance of the fastener holes as described in paragraph

(1) (d) 1 to define the correct fastener dimension, refer to SRM 51-47-00.

If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 534172D01R04, use a smaller fastener (part of Kit

534172D03R01) as given in the fastener table in Figure 4, Sheet 1 thru 10 .

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

h Drill the marked fastener holes for cold working with the correct start drill, as

given in Figure 4, Sheet 7 thru 10.

i Ream the marked fastener holes for cold working with the correct start

reamer, as given in Figure 4, Sheet 7 thru 10.

j Expand the marked fastener holes in accordance with the SRM 51-48-00,

Page block 001.

k Ream the marked fastener holes with the correct gage finish reamer, as

given in Figure 4, Sheet 7 thru 10.

l Check the edge clearance of the unmarked fastener holes as described in

paragraph (1) (d) 1 to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 534172D01R04, use a smaller fastener

(part of Kit 534172D03R01) as given in the fastener table in Figure 4,

Sheet 1 thru 10 .

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

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A340

SERVICE BULLETIN

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

m Drill the unmarked fastener holes to the correct dimension as given in Figure

3, Sheet 14 and Figure 4, Sheet 1 thru 6.

n Remove the doubler, item 13 and the shim, item 17 from the fuselage

structure.

o Deburr the fastener holes.

p Clean the shim, item 17, the doubler, item 13 and the fuselage structure with

cleaning agent (Mat. No. 11-026).

q With sealant (Mat. No. 09-005) to the mating surfaces and screw pins install

as shown on Figure 3, Sheet 13 :

1 doubler F5357716922000 Item 13

1 shim F5357798921600 Item 17

r To the fuselage skin, the doubler, item 13 and the shim, item 17, install with

sealant (Mat. No. 09-005), as given in Figure 3, Sheet 14 and Figure 4,

Sheet 1 thru 10 :

NOTE : If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables in Figure 4 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 534172D02R01.

NOTE : For the following fasteners, refer to Figure 4, Sheet 1.

1 pin DAN5-6-8 Item 24

3 pin DAN5-6-7 Item 23

NOTE : For the following fasteners, refer to Figure 4, Sheet 2.

2 pin DAN5-6-10 Item 25

2 pin DAN7-8-11 Item 28

NOTE : For the following fasteners, refer to Figure 4, Sheet 3.

1 pin DAN5-6-10X Item 33

NOTE : For the following fasteners, refer to Figure 4, Sheet 4.

3 pin DAN7-8-13Y Item 35

3 pin DAN7-8-16Y Item 37

NOTE : For the following fasteners, refer to Figure 4, Sheet 5.

1 pin DAN7-8-12X Item 59

4 pin DAN7-8-10Y Item 60

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 40

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A340

SERVICE BULLETIN

4 pin DAN7-8-11Y Item 61

NOTE : For the following fasteners, refer to Figure 4, Sheet 6.

1 pin DAN7-8-12Y Item 62

NOTE : For the following fasteners, refer to Figure 4, Sheet 7.

1 bolt EN6115K4Y16 Item 44

NOTE : For the following fasteners, refer to Figure 4, Sheet 8.

1 bolt EN6115K3-4 Item 64

3 bolt EN6115K3-5 Item 65

2 bolt EN6115K3-7 Item 66

2 bolt EN6115K3-8 Item 67

1 bolt EN6115K3A8 Item 125

with

6 collar NSA5075-6 Item 46

2 collar DAN12-8 Item 48

8 nut ASNA2528-3 Item 50

1 nut ASNA2528-4 Item 51

15 collar DAN12-8Y Item 54

1 collar DAN12-8X Item 55

1 collar DAN11-6X Item 56

1 nut ASNA2528-3A Item 126

s Clean the repair area with cleaning agent (Mat. No. 11-026) and lint-free

cloth (Mat. No. 19-003).

4 Install the reinforcement doublers and shims with cold working at FR84 at

STGR5A R/H.

a Clean the working area with cleaning agent (Mat. No. 11-026) and remove

parts of sealant from the structure corners to get a perfect fit of the shim,

item 12 and the doubler, item 16 to the fuselage structure.

b Put the shim, item 16 and the doubler, item 12 in the final position on the

fuselage structure as given in Figure 3, Sheet 13.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

c Transfer drill the pilot holes from the shim, item 16 and from the doubler, item

12 to the fuselage structure with a drill of 2.5 mm (0.1 in.) DIA.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

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A340

SERVICE BULLETIN

d Transfer drill the fastener holes from the fuselage structure to the doubler,

item 12 using a drill of 2.5 mm (0.1 in.) DIA and a suitable drill bush.

e Mark the fastener holes which have to be expand by cold working with a soft

felt pen, refer to Figure 3, Sheet 14.

f Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00, Page block 001 for cold

working and Figure 4, Sheet 1 thru 10 for all fastener holes.

g Check the edge clearance of the fastener holes as described in paragraph

(1) (d) 1 to define the correct fastener dimension, refer to SRM 51-47-00.

If the minimum edge clearance is not given to the standard fastener

installation (part of Kit 534172D01R04, use a smaller fastener (part of Kit

534172D03R01) as given in the fastener table in Figure 4, Sheet 1 thru 10 .

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

h Drill the marked fastener holes for cold working with the correct start drill, as

given in Figure 4, Sheet 7 thru 10.

i Ream the marked fastener holes for cold working with the correct start

reamer, as given in Figure 4, Sheet 7 thru 10.

j Expand the marked fastener holes in accordance with the SRM 51-48-00,

Page block 001.

k Ream the marked fastener holes with the correct gage finish reamer, as

given in Figure 4, Sheet 7 thru 10.

l Check the edge clearance of the unmarked fastener holes as described in

paragraph (1) (d) 1 to define the correct fastener dimension, refer to SRM

51-47-00. If the minimum edge clearance is not given to the standard

fastener installation (part of Kit 534172D01R04, use a smaller fastener

(part of Kit 534172D03R01) as given in the fastener table in Figure 4,

Sheet 1 thru 10 .

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

m Drill the unmarked fastener holes to the correct dimension as given in to

Figure 3, Sheet 14 and Figure 4, Sheet 1 thru 6.

n Remove the doubler, item 12 and the shim, item 16 from the fuselage

structure.

o Deburr the fastener holes.

p Clean the shim, item 16, the doubler, item 12 and the fuselage structure with

cleaning agent (Mat. No. 11-026).

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 42

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A340

SERVICE BULLETIN

q With sealant (Mat. No. 09-005) to the mating surfaces and screw pins install

as shown on Figure 3, Sheet 13 :

1 doubler F5357716922100 Item 12

1 shim F5357798921700 Item 16

r To the fuselage skin, the doubler, item 12 and the shim, item 16, install with

sealant (Mat. No. 09-005), as given in Figure 3, Sheet 14 and Figure 4,

Sheet 1 thru 10 :

NOTE : If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables in Figure 4 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 534172D02R01.

NOTE : For the following fasteners, refer to Figure 4, Sheet 1.

1 pin DAN5-6-8 Item 24

3 pin DAN5-6-7 Item 23

NOTE : For the following fasteners, refer to Figure 4, Sheet 2.

2 pin DAN5-6-10 Item 25

2 pin DAN7-8-11 Item 28

NOTE : For the following fasteners, refer to Figure 4, Sheet 3.

1 pin DAN5-6-10X Item 33

NOTE : For the following fasteners, refer to Figure 4, Sheet 4.

3 pin DAN7-8-13Y Item 35

3 pin DAN7-8-16Y Item 37

NOTE : For the following fasteners, refer to Figure 4, Sheet 5.

1 pin DAN7-8-12X Item 59

4 pin DAN7-8-10Y Item 60

4 pin DAN7-8-11Y Item 61

NOTE : For the following fasteners, refer to Figure 4, Sheet 6.

1 pin DAN7-8-12Y Item 62

NOTE : For the following fasteners, refer to Figure 4, Sheet 7.

1 bolt EN6115K4Y16 Item 44

NOTE : For the following fasteners, refer to Figure 4, Sheet 8.

1 bolt EN6115K3-4 Item 64

3 bolt EN6115K3-5 Item 65

2 bolt EN6115K3-7 Item 66

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 43

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A340

SERVICE BULLETIN

2 bolt EN6115K3-8 Item 67

1 bolt EN6115K3A8 Item 125

with

6 collar NSA5075-6 Item 46

2 collar DAN12-8 Item 48

8 nut ASNA2528-3 Item 50

1 nut ASNA2528-4 Item 51

15 collar DAN12-8Y Item 54

1 collar DAN12-8X Item 55

1 collar DAN11-6X Item 56

1 nut ASNA2528-3A Item 126

s Clean the repair area with cleaning agent (Mat. No. 11-026) and lint-free

cloth (Mat. No. 19-003).

(h) Install fasteners with cold working in the upper fuselage skin at FR85

Refer to Kit 534172D01R04, Kit 534172D02R01, Kit 534172D03R01

Refer to Figure 3

Refer to Figure 4,

Refer to SRM 51-47-00

Refer to SRM 51-48-00

Refer to ESPM 20-51-20

1 Install the fasteners with cold working at FR85 between STGR2B L/H and

STGR5A L/H.

a Clean the working area with cleaning agent (Mat. No. 11-026).

b Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00, Page block 001 for cold

working and Figure 4, Sheet 1 thru 10 for all fastener holes.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

c Drill the marked fastener holes for cold working with the correct start drill, as

given in Figure 4, Sheet 7 thru 10.

d Ream the marked fastener holes for cold working with the correct start

reamer, as given in Figure 4, Sheet 7 thru 10.

e Expand the marked fastener holes in accordance with the SRM 51-48-00,

Page block 001.

f Ream the marked fastener holes with the correct gage finish reamer, as

given in Figure 4, Sheet 7 thru 10.

g Deburr the fastener holes.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

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SERVICE BULLETIN

h Clean the repair area with cleaning agent (Mat. No. 11-026) and lint-free

cloth (Mat. No. 19-003).

i Install the fastener with sealant (Mat. No. 09-005), as given in Figure 3,

Sheet 15 and Figure 4, Sheet 7 :

NOTE : If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables in Figure 4 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 534172D02R01.

2 bolt EN6115K4Y7 Item 38

2 bolt EN6115K4Y10 Item 40

2 bolt EN6115K4Y11 Item 41

6 nut ASNA2528-4 Item 51

j Clean the repair area with cleaning agent (Mat. No. 11-026) and lint-free

cloth (Mat. No. 19-003).

2 Install the fasteners with cold working at FR85 between STGR2B R/H and

STGR5A R/H.

a Clean the working area with cleaning agent (Mat. No. 11-026).

b Measure the size of the fastener holes and define the next stage of drill hole

diameter in accordance with the SRM 51-48-00, Page block 001 for cold

working and Figure 4, Sheet 1 thru 10 for all fastener holes.

CAUTION : MAKE SURE THAT YOU DRILL AT A 90 DEG ANGLE TO THE

FUSELAGE SKIN TO AVOID A MISROUTING OF THE DRILL

HOLE.

c Drill the marked fastener holes for cold working with the correct start drill, as

given in Figure 4, Sheet 7 thru 10.

d Ream the marked fastener holes for cold working with the correct start

reamer, as given in Figure 4, Sheet 7 thru 10.

e Expand the marked fastener holes in accordance with the SRM 51-48-00,

Page block 001.

f Ream the marked fastener holes with the correct gage finish reamer, as

given in Figure 4, Sheet 7 thru 10.

g Deburr the fastener holes.

h Clean the repair area with cleaning agent (Mat. No. 11-026) and lint-free

cloth (Mat. No. 19-003).

i Install the fastener with sealant (Mat. No. 09-005), as given in Figure 3,

Sheet 15 and Figure 4, Sheet 7 :

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 45

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A340

SERVICE BULLETIN

NOTE : If the following fasteners do not fit and oversize fasteners are

necessary, refer to the fastener tables in Figure 4 to find the

correct bolt or pin with the associated nut or collar which is

part of Kit 534172D02R01.

2 bolt EN6115K4Y7 Item 38

2 bolt EN6115K4Y10 Item 40

2 bolt EN6115K4Y11 Item 41

6 nut ASNA2528-4 Item 51

j Clean the repair area with cleaning agent (Mat. No. 11-026) and lint-free

cloth (Mat. No. 19-003)lint-free cloth (Mat. No. 19-003).

(i) Apply surface protection to the modification area.

1 Apply sealant (Mat. No. 09-013) or sealant (Mat. No. 09-016) to form a bead

around the new doubler and reinstalled angles.

2 Apply wash primer (Mat. No. 16-020) to all reworked edges and heads of

fasteners.

3 Apply polyurethane primer (Mat. No. 16-001) to all reworked edges and

heads of fasteners.

4 Apply polyurethane top coat (Mat. No. 16-018) to all reworked edges and

heads of fasteners.

5 Apply corrosion preventive (Mat. No. 15-005) to the modification area inside the

fuselage.

C. TEST

None

D. CLOSE UP

(1) Config. 01

(a) Install the vertical stabilizer as given in AMM 55-31-11, Page block 401.

(b) Reinstall the Bleed Air pipe between FR85 and FR87, refer to AMM 36-12-41,

Page block 401.

(c) Reinstall the Bleed Air pipe sense line between FR85 and FR87, refer to AMM

36-22-17, Page block 401.

(d) If removed, install the AFT galley, refer to AMM 25-33-52, Page block 401and

AMM 25-33-53, Page block 401.

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

equipment.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 46

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A340

SERVICE BULLETIN

(f) Install the AFT galley ceiling refer to AMM 25-33-54, Page block 401 or the AFT

galley pelmet refer to AMM 25-33-48.

(g) Close the access door 312AR in the REAR fuselage area.

(h) Remove the access platform(s) from the aircraft REAR section.

(i) Pressurize the Green, the Blue and the Yellow hydraulic reservoirs, refer to AMM

29-14-00, Page block 201.

(j) Fill the Green hydraulic tank, refer to AMM 12-12-29, Page block 301.

(k) Pressurize the Green, the Blue and the Yellow hydraulic systems, refer to AMM

29-00-00, Page block 201.

(l) Remove the warning notices :

- in the cockpit from the hydraulic section 40VU of the overhead panel,

- on the ground service panel from each hydraulic system.

(m) Close the FWD passenger/crew doors (1L/1R), refer to AMM 52-10-00, Page

block 201).

(n) Remove the access platform from the passenger/crew doors.

E. DOCUMENTATION

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

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 47

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 1, Sheet 1

Config. 01: Flow Chart of Fastener Installation Process and Example of Fastener Hole Reworking

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 48

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 1, Sheet 2

Config. 01: Flow Chart of Fastener Installation Process and Example of Fastener Hole Reworking

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 49/50

Printed in France © AIRBUS 2007 All rights reserved

A340

SERVICE BULLETIN

Figure 2, Sheet 1

Config. 01: Removal of Fasteners from the upper fuselage shell between FR80 and FR86

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 51

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 2, Sheet 2

Config. 01: Removal of Fasteners from the upper fuselage shell between FR80 and FR86

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 52/53

Printed in France © AIRBUS 2007 All rights reserved

A340

SERVICE BULLETIN

Figure 2, Sheet 3

Config. 01: Removal of Fasteners from the upper fuselage shell between FR80 and FR86

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 54

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 2, Sheet 4

Config. 01: Removal of Fasteners from the upper fuselage shell between FR80 and FR86

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 55

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 1

Config. 01: Installation of Reinforcement Brackets and new Fasteners with Cold Working.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 56

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 2

Config. 01: Installation of Reinforcement Brackets and new Fasteners with Cold Working.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 57

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 3

Config. 01: Installation of Reinforcement Brackets and new Fasteners with Cold Working.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 58

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 4

Config. 01: Installation of Reinforcement Brackets and new Fasteners with Cold Working.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 59

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 5

Config. 01: Installation of Reinforcement Brackets and new Fasteners with Cold Working.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 60

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 6

Config. 01: Installation of Reinforcement Brackets and new Fasteners with Cold Working.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 61

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 7

Config. 01: Installation of Reinforcement Brackets and new Fasteners with Cold Working.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 62

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 8

Config. 01: Installation of Reinforcement Brackets and new Fasteners with Cold Working.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 63

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 9

Config. 01: Installation of Reinforcement Brackets and new Fasteners with Cold Working.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 64

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 10

Config. 01: Installation of Reinforcement Brackets and new Fasteners with Cold Working.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 65

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 11

Config. 01: Installation of Reinforcement Brackets and new Fasteners with Cold Working.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 66

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 12

Config. 01: Installation of Reinforcement Brackets and new Fasteners with Cold Working.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 67

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 13

Config. 01: Installation of Reinforcement Brackets and new Fasteners with Cold Working.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 68

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 14

Config. 01: Installation of Reinforcement Brackets and new Fasteners with Cold Working.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 69

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 3, Sheet 15

Config. 01: Installation of Reinforcement Brackets and new Fasteners with Cold Working.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 70

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 4, Sheet 1

Config. 01: Fastener Table

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 71

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 4, Sheet 2

Config. 01: Fastener Table

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 72

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 4, Sheet 3

Config. 01: Fastener Table

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 73

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 4, Sheet 4

Config. 01: Fastener Table

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 74

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 4, Sheet 5

Config. 01: Fastener Table

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 75

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 4, Sheet 6

Config. 01: Fastener Table

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 76

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 4, Sheet 7

Config. 01: Fastener Table

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 77/78

Printed in France © AIRBUS 2007 All rights reserved

A340

SERVICE BULLETIN

Figure 4, Sheet 8

Config. 01: Fastener Table

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 79/80

Printed in France © AIRBUS 2007 All rights reserved

A340

SERVICE BULLETIN

Figure 4, Sheet 9

Config. 01: Fastener Table

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 81/82

Printed in France © AIRBUS 2007 All rights reserved

A340

SERVICE BULLETIN

Figure 4, Sheet 10

Config. 01: Fastener Table

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 83/84

Printed in France © AIRBUS 2007 All rights reserved

A340

SERVICE BULLETIN

Figure 5, Sheet 1

Config. 01: Inspection Areas of Fastener Hole Rototest

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 85

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 5, Sheet 2

Config. 01: Inspection Areas of Fastener Hole Rototest

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 86

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 5, Sheet 3

Config. 01: Inspection Areas of Fastener Hole Rototest

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 87

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 5, Sheet 4

Config. 01: Inspection Areas of Fastener Hole Rototest

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 88

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

Figure 5, Sheet 5

Config. 01: Inspection Areas of Fastener Hole Rototest

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 89

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 90

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SERVICE BULLETIN

REPORTING SHEET

TITLE : FUSELAGE - REAR FUSELAGE - INTRODUCE STRUCTURAL CHANGES DUE TO EF3 TEST

RESULTS IN SECTION 19 (RETRO SOLUTION) - INSTALLATION OF REINFORCEMENT

DOUBLERS AND COLD WORKING ON FASTENER HOLES AT FR80 BETWEEN STGR 2A AND

5A AND BETWEEN FR84 - FR87 AT STGR 2 AND STGR 5 LH/RH.

MODIFICATION No. : 53222D44560

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: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

Or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 1 of 1

Printed in France © AIRBUS 2007 All rights reserved
A340

SERVICE BULLETIN

REPORTING QUALITY

TITLE : FUSELAGE - REAR FUSELAGE - INTRODUCE STRUCTURAL CHANGES DUE TO EF3 TEST

RESULTS IN SECTION 19 (RETRO SOLUTION) - INSTALLATION OF REINFORCEMENT

DOUBLERS AND COLD WORKING ON FASTENER HOLES AT FR80 BETWEEN STGR 2A AND

5A AND BETWEEN FR84 - FR87 AT STGR 2 AND STGR 5 LH/RH.

MODIFICATION No. : 53222D44560

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: SEM4 Service Bulletins Management

FAX: (+33) 5 61 93 42 51

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 1 of 1

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SERVICE BULLETIN

REPORTING QUALITY

Or via your Resident Customer Support Office.

DATE : Jul 10/07 SERVICE BULLETIN No. : A340-53-4172

REVISION No. : 01 - Jul 08/09 Page : 1 of 1

Printed in France © AIRBUS 2007 All rights reserved