5 DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

This summary is for information only

and is not approved for modification of the aircraf

ATA SYSTEM : 57

TITLE : WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION I

KEEL BEAM FITTING AT FR.40

MODIFICATION No. : 56467S18944

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During a structural A330 aircraft fatigue test, cracks appeared in 

fitting at FR40, initiating at the first fastener hole aft of FR4

test bench was in post Mod. No. 41652S12091 (WINGS - SECTION 15/21 

FITTING BEAM/FORWARD LOWER FUSELAGE JOINT) production solution co

The intention of the production solution was also proposed by Serv

A340-57-4036 for retrofit.

The structural analysis has led to the issue of the Inspection Se

A340-57-4089 (WINGS - CENTER WING BOX - INSPECTION OF KEEL BEAM FA

AT FRAME 40 (UNREPAIRED AIRCRAFT)).

The Inspection Service Bulletin requires a detailed inspection on 

pre Mod. No. 49202S16307 (FUSELAGE - CENTER FUSELAGE - REINFORCE 

including mandatory and recommended thresholds and repetitive ins

intervals.

This Service Bulletin recommends to modify the fasteners installa

junction of the keel beam fitting at FR40.

Accomplishment of this Service Bulletin cancels the inspection re

Service Bulletin A340-57-4089 for aircraft on which Mod. No. 44360

CENTER WING - MODIFY FR40 and FRONT SPAR) in not embodied.

This fix for the existing mandatory Inspection Service Bulletin at 

beam.

EVALUATION TABLE

COMPLIANCE Recommended CANCELS INSPECTION S

POTENTIAL AD No A/C OPERATION AFFECT

RELIABILITY AFFECTED No PAX COMFORT AFFECTED 
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

As per EASA IR 21, a minor change is one that has no appreciable 

mass, balance, structural strength, reliability, operational char

affecting the airworthiness of the product. All other changes are 

EFFECTIVITY

This Service Bulletin is applicable to these operators :

AAW ACA AFR AUA CES CPA DLH ETD GFA IBE MAU MSR PAL SWR THY UAE V

NOTE : This Service Bulletin is only applicable to aircraft on wh

modification No. 41652S11819 (FUSELAGE - STRUCTURE - INTRO

COMMONALITY ITEMS) is embodied and modification No. 49202S1

- CENTER FUSELAGE - REINFORCE SECTION 15/21) and modificat

44360S13013 (WING - CENTER WING - MODIFY FR40 AND FRONT SPA

embodied.

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : 57.11.00.005

OEB : None

AOT : None

SIL : None

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

OTHERS : None

NATURE OF THE WORK

AIRCRAFT : YES

EQUIPMENT : NO

MODIFICATION CLASSIFICATION

MAJOR 56467S18944

MINOR

None

2
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

MATERIAL INFORMATION

AIRCRAFT DATA

Config. 01

Kit 574106A01R00

Bolts, nuts and washer

APPENDICES

Appendix 1 - REPORT

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

3
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

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4
5 DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

ATA SYSTEM : 57

TITLE : WINGS - CENTER WING BOX - MODIFY FASTENERS INSTALLATION I

KEEL BEAM FITTING AT FR.40

MODIFICATION No. : 56467S18944

This document contains AIRBUS PROPRIETARY INFORMATION and shall a

remain the property of AIRBUS; no intellectual property right or 

granted by AIRBUS in connection with any information contained in 

delivered on the express condition that said document and the inf

contained in it shall be treated as confidential, shall not be us

purpose other than that for which it is hereby delivered. It shal

disclosed in whole or in part to third parties and shall not be d

any manner (except for the purposes of performing the tasks descr

and provided that any recipient of such document shall comply wit

conditions herein), without AIRBUS' prior written consent.

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Models

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

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft 

0114 0115 0117 0123 0125 0126 0128 0129 0131 01

0141 0142 0145-0147 0149-0152 0154 0156-0161 01

0166-0170 0173-0175

NOTE : This Service Bulletin is only applicable 

which modification No. 41652S11819 (FUSE

STRUCTURE - INTRODUCE A340 COMMONALITY IT

embodied and modification No. 49202S1630

CENTER FUSELAGE - REINFORCE SECTION 15/21

modification No. 44360S13013 (WING - CENT

MODIFY FR40 AND FRONT SPAR) are not embod
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(c) Effectivity by MSN and Kit/Configuration

The kits and configurations applicable to these 

at the end of this list:

0114-0115 0117 0123 0125-0126 0128-0129 0131 01

0141-0142 0145-0147 0149-0152 0154 0156-0161 01

0166-0170 0173-0175

NOTE : Config. 01 is valid for all the aircraft 

effectivity of this Service Bulletin as a 

configuration.

OPERATOR MSN

AAW 0151

ACA 0154 0167 0170 0175

AFR 0168 0174

AUA 0169

CES 0129 0131 0141 0161

CPA 0123 0126 0128 0136 0137 0142 0147 0

DLH 0135 0158

ETD 0117

GFA 0133

IBE 0125 0134 0145 0146

MAU 0152

MSR 0156 0159

PAL 0173

SWR 0150

THY 0115

UAE 0139 0149 0163 0166

VIR 0114 0164

KIT No. QTY PER A/C CONFIGURATION

574106A01R00 2 01

2
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

C. REASON

(1) History

During a structural A330 aircraft fatigue test, crac

the keel beam fitting at FR40, initiating at the fir

hole aft of FR40 datum. The test bench was in post Mo

41652S12091 (WINGS - SECTION 15/21 - MODIFY KEEL FITT

BEAM/FORWARD LOWER FUSELAGE JOINT) production solutio

configuration.

The intention of the production solution was also pro

Service Bulletin A340-57-4036 for retrofit.

The structural analysis has led to the issue of the 

Service Bulletin A340-57-4089 (WINGS - CENTER WING BO

OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED A

The Inspection Service Bulletin requires a detailed 

A340 aircraft pre Mod. No. 49202S16307 (FUSELAGE - C

- REINFORCE SECTION 15/21) including mandatory and r

thresholds and repetitive inspection intervals.

(2) Objective/Action

This Service Bulletin recommends to modify the faste

installation in the junction of the keel beam fitting 

(3) Advantages

Accomplishment of this Service Bulletin cancels the 

requirements of Service Bulletin A340-57-4089 for air

Mod. No. 44360S13013 (WING - CENTER WING - MODIFY FR4

SPAR) in not embodied.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

(1) Config. 01

(a) On the LH and RH sides, remove (only if necessa

between FR39.1 and FR40, for access.

3
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(d) On the LH and RH sides, install (if removed) the 

FR39.1 and FR40.

E. COMPLIANCE

(1) Classification

Recommended

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is recommend

earliest opportunity where manpower and facilities a

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA

If an aircraft listed in the effectivity has a modificatio

embodied that is not of AIRBUS origin, and which affects 

this Service Bulletin, the operator is responsible for ob

approval by its airworthiness authority for any adaptatio

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are 

direct labor cost to do the work. These estimates assume 

will be done by experienced personnel, and may need to be 

upwards to suit operator's circumstances. The estimates do 

the time to prepare, plan or inspect the work. Manufactur

procurement of parts and tools, drying times for paints, 

and general administration work are also not included.

Config. 01

Get access 

Removal of the ducts 

Removal of fastener hole 5 

Rotating probe inspection

hole 5

Installation of the

fastener hole 5

Removal of fastener holes

6 and 7

4
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

H. WEIGHT AND BALANCE

Not changed

I. ELECTRICAL LOAD DATA

Not changed

J. REFERENCES

PMS 01-05-05

Service Bulletin No. A340-57-4036

Service Bulletin No. A340-57-4089

Appendix 1

K. PUBLICATIONS AFFECTED

Not changed

L. INTERCHANGEABILITY/MIXABILITY

Not applicable

Test 

Close-up 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

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

21-20-00 21-53-18 

28-25-00 32-12-00 

53-35-13 57-17-11

Consumable Material List (CML)

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

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

Service Information Letter (SIL) : 51-012

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

51-48-00 51-76-12

5
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

This Page Intentionally Left Blank

6
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

of this Service Bulletin. The address is :

AIRBUS

SPARES SUPPORT AND SERVICES

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet: http://spa

For ordering by fax: +49 40 50 76 25 

(2) Price and Availability

Kit 574106A01R00

Cost : 180.00 US Dollars

Availability : 120 calendar days from receipt of orde

The Kit availability given above is the standard lead 

date of your purchase order. If you require the Kit(

time, please include a retrofit planning schedule wit

so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimat

to economic conditions at the issue date of the Serv

B. INDUSTRY SUPPORT INFORMATION

This Service bulletin is subject to the Fatigue Test Inte

Program. Refer to the FTIP policy.

C. LIST OF COMPONENTS

Kit 574106A01R00

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

25 EN6115-6Y-20 1 Bolt

26 NSA5368-616D 1 Washer

27 ASNA2531-6 1 Nut

31 ASNA2531-5 1 Nut

32 EN6115-5-12 1 Bolt

33 ASNA2529-6 1 Nut

34 EN6115V6Y-16 1 Bolt

7
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

y 

Bulletin. The SM will give you the correct part num

number relationship.

D. LIST OF MATERIALS — OPERATOR SUPPLIED

(1) Consumable Materials

(2) Components

None

E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR

None

F. TOOLING — PRICE AND AVAILABILITY

(1) To accomplish this Service Bulletin, it is necessary 

following tools and equipment.

(a) Equipment and materials for the check of the ho

51-10-01 Part 6.

(b) Equipment and materials for the check of the ho

51-10-18 Part 6.

(2) Fatigue Technology Incorporated (FTI) has allocated t

tool kit numbers for cold working :

NOTE : For definition of capital, durable and expenda

refer to SIL 51-012.

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

This tool reference include all capital, durable a

tooling kits regardless of effectivity but capital 

DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C 

Fuel Tank Sealant

Polysulfide

09-002B As required

Corrosion Inhibiting Brush

Consistency

09-013B As required

Solvent General Purpose 11-026 As required

8
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Bulletin on more than one aircraft, operato

the quantity of durable tool to be ordered b

SIL 51-012.

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

NOTE : In this expendable tool, there is the minim

necessary to accomplish this Service Bulleti

aircraft. One expendable tool has to be orde

aircraft where this Service Bulletin is acco

Operators interested in obtaining the FTI tool kit s

Fatigue Technology Inc.

401 Andover Park West

SEATTLE, WA 98188-7605

USA

E.Mail : sales@fatiguetech.com

E.Mail : aog@fatiguetech.com

Phone : (1) 206 2462010

Fax : (1) 206 2449886

G. SPECIAL TOOLS

None

9
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REVISION No. : 00 — Page :

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This Page Intentionally Left Blank

10
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

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WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY 

MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENAN

REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICA

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIB

:

— PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOT

NECESSARY ON WIRING AND COMPONENTS.

— REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATER

CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONT

DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

(1) Preparation

(a) Config. 01

1 Make sure that the aircraft is grounded (Refe

12-34-24 Page block 201).

2 Put the access platform(s) in position.

3 Open the Main Landing Gear (MLG) doors (Refe

32-12-00 Page block 201).

4 Do the preparation procedure as specified in

removal/installation of the air-conditioning 

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

5 Do the preparation procedure as specified in

removal/installation of the pack discharge

temperature-sensor (541HH and 542HH) (Refer t

Page block 401).

6 Do the preparation procedure as specified in

removal/installation of the APU bleed-air duc

AMM 36-12-41 Page block 401).

7 Remove the access panels 191FB for the LH sid

for the RH side (Refer to AMM 53-35-13 Page 

AMM 06-41-53).

11
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

11 Get access to the work area.

(2) Standard Practices

(a) For the specification of the material numbers (M

to the CML.

(b) Clean the surfaces to be sealed with Solvent Ge

(Mat No. 11-026) .

(c) Use a non-metallic spatula to remove the sealant 

areas with Solvent General Purpose (Mat No. 11-0

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

(e) Remove and install the fasteners (Refer to SRM 

(f) Apply Corrosion Inhibiting Brush Consistency (Mat 

on all the fasteners to be installed (wet assem

(g) For the oversize and alternative fasteners (Refe

51-43-00).

(h) Torque the standard threaded fasteners (Refer to 

Page block 201).

(i) Do the cold expansion of the holes (Refer to SRM 

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

(k) Install the plug with liquid nitrogen (Refer to 

).

B. MODIFICATION

(1) Config. 01

(a) On the LH and RH sides, remove (only if necessa

between FR39.1 and FR40, for access.

Refer to Figures 1 and 2

1 On RH side, remove the air conditioning duct

Refer to Figure 1

12
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE (01) Disconnect and move the rod Item

(19) without removal.

NOTE (02) Remove the Insulation Item (9) w

clamp Item (17) from the duct It

necessary.

NOTE (03) For the removal of the sensor 54

AMM 21-53-18 Page block 401).

2 On RH side, remove the air ventilation duct.

Refer to Figure 2

a Remove :

3 On LH side, remove the necessary APU bleed ai

between FR39.1 and FR40 (Refer to AMM 36-12-4

401).

4 Put the blanking plugs on the disconnected l

(b) On the LH and RH sides of aircraft between FR40 

replace the keel beam fasteners for aircraft wit

installed on hole 5.

Refer to Kit 574106A01R00

Refer to Figure 3

NOTE : Description below is given for one side o

aircraft, two Kit 574106A01R00 are neces

one aircraft.

1 Inspect the hole 5.

(

2 Washer Item (1

2 Nut Item (1

1 Clamp Item (1

1 Clamp Item (1

1 Duct Item (2

8 Clamp Item (2

4 Clamp Item (2

2 Sleeve Item (2

1 Sleeve Item (2

13
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

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c Do a rotating probe inspection (Refer to N

through all the layers.

— If no crack is detected, do the operatio

paragraph (1)(b)2.

— If crack is detected do the operations g

paragraph (1)(b)3.

2 No crack, oversize the hole 5 in the keel bea

Refer to Figure 3 , Sheets 1 , 3 and 4

a Ream the hole at the level of the keel bea

diameter comprised between 17mm (0.669in.) 

(0.677in.) with a radius of 2mm (0.079in.)

reaming depth in the CWB lower panel is co

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

b Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02i

hole dia. 17mm (0.669in.).

c Oversize the hole 5 through all the layers 

comprised between 10.177mm (0.401in.) and 

(0.402in.).

d Clean the drilled area.

e Install :

NOTE (01) Before installation of the faste

Corrosion Inhibiting Brush Consi

No. 09-013B) (wet assembly).

NOTE (02) Coat the nut and washer with Fue

Polysulfide (Mat No. 09-002B) .

3 Crack detected, oversize the hole 5 in the ke

Refer to Figure 3 , Sheets 1 , 3 and 4

1 Bolt EN6115V6Y-16 Item 34

1 Washer F5332433420000 Item 35

1 Nut ASNA2529-6 Item 33

1 Washer NSA5368PD616D Item 42

14
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

— Crack finding, contact AIRBUS.

— No crack finding, oversize the hole in t

only to a diameter comprised between 17m

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

Admissible reaming depth in the CWB lowe

comprised between 1mm (0.039in.) and 1.2

— Do a chamfer of 0.5mm*0.5mm (0.02in.*0.0

hole dia. 17mm (0.669in.).

— Oversize the hole 5 through all the laye

diameter comprised between 10.177mm (0.4

10.219mm (0.402in.)

— Install :

NOTE (01) Before installation of the fas

Corrosion Inhibiting Brush Con

No. 09-013B) (wet assembly).

NOTE (02) Coat the nut and washer with 

Sealant Polysulfide (Mat No. 0

4 Inspect holes 6 and 7

Refer to Figure 3 , Sheets 1 and 2

a Remove :

b Remove the sealant and clean the holes.

c Do a rotating probe inspection through all 

holes 6 and 7 (Refer to NTM 51-10-01).

— If a crack is detected, contact AIRBUS.

1 Bolt EN6115V6Y-16 Item 34

1 Washer F5332433420000 Item 35

1 Nut ASNA2529-6 Item 33

1 Washer NSA5368PD616D Item 42

1 Nut Item (2

1 Nut Item (4

1 Bolt Item (1

1 Bolt Item (3

15
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

working comprised between 9.53mm (0.375in

(0.378in.).

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

b Clean the drilled area.

c Do the cold working of the hole (Refer to 

Use FTI tool list kit No. FTI-A340-57-4106

EK-A340-57-4106-1.

d Ream the hole to the final hole diameter c

between 10.177mm (0.401in.) and 10.219mm 

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

e Clean the drilled area.

f Install :

NOTE (01) Before installation of the faste

Corrosion Inhibiting Brush Consi

No. 09-013B) (wet assembly).

NOTE (02) Coat the nut with Fuel Tank Seal

Polysulfide (Mat No. 09-002B) .

6 Install the fastener in hole 7.

Refer to Figure 3 , Sheets 1 , 3 and 4

a Oversize the hole to a diameter comprised 

7.809mm (0.307in.) and 7.849mm (0.309in.)

b Install :

NOTE (01) Before installation of the faste

Corrosion Inhibiting Brush Consi

No. 09-013B) (wet assembly).

1 Bolt EN6115-6Y-20 Item 25

1 Nut ASNA2531-6 Item 27

1 Washer NSA5368-616D Item 26

1 Bolt EN6115-5-12 Item 32

1 Nut ASNA2531-5 Item 31

16
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(c) On the LH and RH sides of aircraft between FR40 

replace the keel beam fasteners, for aircraft w

installed on hole 5.

Refer to Figure 4

NOTE (01) Description below is given for one sid

aircraft, two Kit 574106A01R00 are ne

modify one aircraft.

NOTE (02) If the diameter of the bush is >13mm 

if the bush is installed in other laye

beam fitting only, contact AIRBUS.

1 Inspect the hole 5.

Refer to Figure 4 , Sheets 1 and 2

a Remove :

b Remove the sealant and clean the hole.

c Do a rotating probe inspection (Refer to N

through all the layers.

— If crack is detected, contact AIRBUS.

— If no crack is detected, do the operatio

paragraph (1)(c)2.

2 No crack finding, oversize the hole in the ke

Refer to Figure 4 , Sheets 1 , 3 and 4

a Ream the hole at the level of the keel bea

diameter comprised between 17mm (0.669in.) 

(0.677in.) with a radius of 2mm (0.079in.)

reaming depth in the CWB lower panel is co

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

b Do a chamfer of 0.5mm*0.5mm (0.02in.*0.02i

hole dia. 17mm (0.669in.).

1 Bolt Item (3

1 Nut Item (4

1 Bush Item (5

17
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

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NOTE (01) Before installation of the faste

Corrosion Inhibiting Brush Consi

No. 09-013B) (wet assembly).

NOTE (02) Coat the nut and washer with Fue

Polysulfide (Mat No. 09-002B) .

3 Inspect holes 6 and 7.

Refer to Figure 4 , Sheets 1 and 2

a Remove :

b Remove the sealant and clean the holes.

c Do a rotating probe inspection through all 

holes 6 and 7 (Refer to NTM 51-10-01).

— If a crack is detected, contact AIRBUS.

— If no crack is detected, do the operatio

the paragraphes (1)(c)4 and 5.

4 Do the cold working of the hole 6.

Refer to Figure 4 , Sheets 1 , 3 and 4

a Ream the hole to the starting hole diamete

working comprised between 9.53mm (0.375in

(0.378in.).

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

Clean the drilled area.

b Do the cold working of the hole (Refer to 

Use FTI tool list kit No. FTI-A340-57-4106

EK-A340-57-4106-1.

1 Nut ASNA2529-6 Item 33

1 Washer NSA5368PD616D Item 42

1 Nut Item (2

1 Nut Item (4

1 Bolt Item (1

1 Bolt Item (4

18
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE (01) Before installation of the faste

Corrosion Inhibiting Brush Consi

No. 09-013B) (wet assembly).

NOTE (02) Coat the nut with Fuel Tank Seal

Polysulfide (Mat No. 09-002B) .

5 Install the fastener in hole 7.

Refer to Figure 4 , Sheets 1 , 3 and 4

a Oversize the hole to a diameter comprised 

7.809mm (0.307in.) and 7.849mm (0.309in.)

b Install :

NOTE (01) Before installation of the faste

Corrosion Inhibiting Brush Consi

No. 09-013B) (wet assembly).

NOTE (02) Coat the nut with Fuel Tank Seal

Polysulfide (Mat No. 09-002B) .

NOTE (03) If necessary, contact AIRBUS fo

washer solution.

6 For the report after modification, refer to A

(d) On the LH and RH sides, install (if removed) the 

FR39.1 and FR40.

Refer to Figures 1 and 2

1 Remove the blanking plugs on the disconnected 

2 On LH side, install (if removed) the APU blee

ducts between FR39.1 and FR40 (Refer to AMM 

block 401).

1 Bolt EN6115-6Y-20 Item 25

1 Nut ASNA2531-6 Item 27

1 Washer NSA5368-616D Item 26

1 Bolt EN6115-5-12 Item 32

1 Nut ASNA2531-5 Item 31

19
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Items (20) thru (24) were retained 

4 On RH side, install (if removed) the air cond

Refer to Figure 1

a Install :

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

NOTE (02) For the installation of the sens

(Refer to AMM 21-53-18 Page bloc

NOTE (03) Items (8) thru (17) were retaine

C. TEST

(1) Config. 01

(a) Preparation

1 Install the access covers 147AZ and 148AZ (Re

57-17-11 Page block 401).

2 Refuel the center tank (Refer to AMM 28-25-00 

301).

3 Install the torque shaft assies 5010CW and 50

AMM 27-84-45 Page block 201).

4 Clamp Item (2

2 Sleeve Item (2

1 Sleeve Item (2

1 Duct Item (8

1 Insulation Item (9

1 Nut Item (1

1 Bolt Item (1

1 Washer Item (1

2 Screw Item (1

2 Washer Item (1

2 Nut Item (1

1 Clamp Item (1

1 Clamp Item (1

20
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

2 Do the test after the removal/installation of 

air ducts (Refer to AMM 36-12-41 Page block 4

3 Do the test after the removal/installation of 

(147AZ and 148AZ) (Refer to AMM 57-17-11 Page 

4 Do the test after the removal/installation of 

shaft assy (5010CW and 5070CW)(Refer to AMM 2

block 401).

5 Do the test after the removal/installation of 

conditioning distribution ducts (Refer to AMM 

block 201).

D. CLOSE UP

(1) Config. 01

(a) Do the close-up procedure as specified in remova

of the pack discharge temperature-sensor (541HH 

(Refer to AMM 21-53-18 Page block 401).

(b) Do the close-up procedure as specified in remova

of the APU bleed-air ducts (Refer to AMM 36-12-4

401).

(c) Install the access panels 191FB for the LH side 

the RH side (Refer to AMM 53-35-13 Page block 40

06-41-53).

(d) Close the Main Landing Gear (MLG) doors (Refer t

Page block 201).

(e) Make sure that the work areas are clean and clea

other items of equipment.

(f) Remove the access platform(s).

(g) Restore the systems and the aircraft to normal o

condition.

E. DOCUMENTATION

Write in the applicable aircraft records that you have don

given in the Service Bulletin.

21
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 1 Sheet 1

Config. 01 : Removal/Installation of the Air Conditioning Ducts 

and FR40, for Access.

22
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 2 Sheet 1

Config. 01 : Removal/Installation of the Ventilation ducts betwe

FR40, for Access.

23
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 3 Sheet 1

Config. 01 : Replacement of the fasteners of the Keel Beam (hole 

24
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 3 Sheet 2

Config. 01 : Replacement of the fasteners of the Keel Beam (hole 

25
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 3 Sheet 3

Config. 01 : Replacement of the fasteners of the Keel Beam (hole 

26
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 3 Sheet 4

Config. 01 : Replacement of the fasteners of the Keel Beam (hole 

27
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 4 Sheet 1

Config. 01 : Replacement of the fasteners of the Keel Beam (hol

dia. <or= 13mm (0.512 in.))

28
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 4 Sheet 2

Config. 01 : Replacement of the fasteners of the Keel Beam (hol

dia. <or= 13mm (0.512 in.))

29
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 4 Sheet 3

Config. 01 : Replacement of the fasteners of the Keel Beam (hol

dia. <or= 13mm (0.512 in.))

30
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 4 Sheet 4

Config. 01 : Replacement of the fasteners of the Keel Beam (hol

dia. <or= 13mm (0.512 in.))

31
5 DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved
DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 1 Sheet 1

Inspection Report

2
5 DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

A - SB WILL BE embodied............. YES/NO (if NO p

If YES, aircraft concerned (as per SB effectivity by default) and 

(month/year) of embodiment:...................

.................................

.................................

B - SB HAS BEEN embodied on aircraft:..............

.................................

.................................

Operator comments:.......................

................................

................................

From Airline:..........................

Name/Title:...........................

Signature:.............. Date:......

If operational documentation is affected (see Paragraph 1.K of th

information is needed prior to next normal revision or prior to S

please indicate required service:

Either: Modification Operational Impact (MOI), if available. . YE

Or : Intermediate revision. ................ YE

Important Information: This SB will only be incorporated in your m

operational documentation if this sheet is returned to Airbus and 

duly authorised representative. With the next feasible revision, 

result in

- updating of maintenance documentation to show pre and post S

- updating of maintenance and operational documentation to show 

after embodiment.

If this SB requires previous or simultaneous accomplishment of ot

Airbus shall automatically include them in the manual revisions. 

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.
5 DATE : Aug 30/07 SERVICE BULLETIN No. : A340

REVISION No. : 00 — Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(Please rate on a scale of 1 to 4, with 4 being the 

- Quality rating of this SB 

- Quality rating of the Accomplishment Instructions 

- Quality rating of the Illustrations 

- Is this SB easy to understand ? 

If you have had difficulties in the accomplishment of this SB plea

the area(s) and give a short description of the issue.

Planning Material Instruct

X Effectivity X Kit content X Preparat

X Reason X List of Materials X Mod/Insp

X Manpower Operator Supplied X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustra

Comments :

Operator : Date:

Name/Title :

Please return this form to :

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.