@A340

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - CENTER WING BOX - INSPECTION OF ONE FASTENER HOLE

IN THE JUNCTION KEEL BEAM FITTING AT FRAME 40

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

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

40 (FR40), initiating at the first hole aft of FR40 datum. The structural analysis led to the issue

of the Mandatory Inspection Service Bulletin No. A340-57-4089 (WINGS - CENTER WING BOX -

INSPECTION OF KEEL BEAM FASTENER HOLES AT FRAME 40 (UNREPAIRED AIRCRAFT))

and the issue of the Recommended modification Service Bulletin No. A340-57-4106, Modification

No. 56467S18944 (WINGS - CENTER WING BOX-MODIFY FASTENERS INSTALLATION IN THE

JUNCTION KEEL BEAM FITTING AT FR40).

Accomplishment of the Service Bulletin No. A340-57-4106 cancels the inspection requirements of the

Service Bulletin No. A340-57-4089.

The accomplishment Instructions in Service Bulletin No. A340-57-4106 must be completed for all

aircraft belonging to configuration 002 listed in the effectivity of this Service Bulletin Rev. 01 and Rev.

02.

A missing instruction has been detected in the following cases:

- Either with a crack indication at hole 5 at time of Service Bulletin No. A340-57-4106 Rev. 01 or

Rev. 02 accomplishment (Case 1),

- or with a bush installed before Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02

accomplishment at hole 5 and without a crack indication at hole 5 at time of Service Bulletin No.

A340-57-4106 Rev. 01 or Rev. 02 accomplishment (Case 2).

CASE 1:

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

REVISION No.: 00 - Jan 25/13 Page: 1

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SERVICE BULLETIN

SUMMARY

In case of crack indication during rototest inspection of fastener hole 5 as per Service Bulletin

instructions, adjacent hole 6 has to be cold worked. A rototest inspection has to be performed before

the cold working. However, this instruction is missing in the Service Bulletin.

CASE 2:

In case of bush installation before Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02

accomplishment at hole 5 and no crack indication at hole 5 reported by rototest per Service Bulletin

instructions, adjacent hole 6 has to be cold worked. A rototest inspection has to be performed before

the cold working. However, this instruction is missing in the Service Bulletin.

Doing a rototest inspection before the cold working is considered a standard practice. Nevertheless, two

Service Bulletin Information Transmission (SBIT) Ref. 11-0041 and 12-0032 have been issued to inform

operators about this occurrence.

Operators Information Transmission (OIT) Ref. 999.0082/12 can also be consulted about this

occurrence.

Eventually this Service Bulletin is issued to settle this matter.

This Service Bulletin requests a one time ultrasonic inspection of fastener hole 6 in the junction keel

beam fitting at FR40 LH/RH side to ensure that no crack was left unrepaired at time of fastener hole

cold working.

In case of no finding, affected aircraft are inspected as per Airworthiness Limitation Items (ALI) Task

ref. 57-11-63 based on interval value.

In case of finding, AIRBUS repair department will have to be contacted for further repair instructions.

For aircraft which have not accomplished Service Bulletin No. A340-57-4106 at Rev. 01 or Rev. 02,

perform repetitive inspection as per Inspection Service Bulletin No. A340-57-4089 or apply Service

Bulletin No. A340-57-4106 at Rev. 03 or next when recommended threshold is reached.

Accomplishment of this Service Bulletin will avoid extensive repair in the junction keel beam fitting at

FR40.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO LROPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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@A340

SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA01 1 See SB Nut

EFFECTIVITY

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

83V ABQ AFR AIB ALK ARG CAL CCA CES CPA DLH GAF GFA

IBE LAN MAU MDG MSR PAL S3R SAA SAS SWR THT THY UAE

VCV VIR XAX

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER Operator Information Telex (OIT) No.999.0082/12 and OIT No.

999.0086/11

OTHER SBIT 11-0041 and SBIT 12-0032

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 574126-832-801-001: Inspection

TOTAL MANHOURS 22.75

ELAPSED TIME (HOURS) 22.75

APPENDICES

Appendix 01: Inspection Report

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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@A340

SERVICE BULLETIN

SUMMARY

**CONF ALL

FR40

FR47

B

B

A

A

Z141 Z142 − 

HOLE 6 TO BE INSPECTED

LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

VIEW INSIDE CENTER TANK AT FR40

Y−1959

DATUM

Y1959

FR40

FR40 DATUM

STGR1

STGR1

F

W

D

B

C

C

F_SB_574126_5_SAAA_01_02

Figure A-FSAAA - Sheet 01

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

REVISION No.: 00 - Jan 25/13 Page: 4

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@A340

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - CENTER WING BOX - INSPECTION OF ONE FASTENER HOLE

IN THE JUNCTION KEEL BEAM FITTING AT FRAME 40

MODIFICATION No.: None

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

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

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

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

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

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

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

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

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

(2) Effectivity by MSN

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

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

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

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

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

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

0446-0447 0450 0459 0467 0470 0474 0483

(3) Effectivity by Operator

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

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

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

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

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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@A340

SERVICE BULLETIN

OPERATOR MSN

83V 0235 0239 0280 0292

ABQ 0216 0257

AFR 0186 0207 0237 0245 0246 0260 0307 0310 0377 0399

AIB 0332

ALK 0367 0374 0381

ARG 0373

CAL 0402 0406 0411 0415 0433

CCA 0192 0199 0201 0242 0243 0264

CES 0182

CPA 0208 0218 0220 0227 0228

DLH 0213 0233 0252 0297 0304 0321 0325 0327 0335 0347 0352 0354

0379 0390 0434 0447

GAF 0274 0355

GFA 0212 0215 0282

IBE 0193 0217 0221 0318 0329 0387 0414 0459 0474 0483

LAN 0359 0363 0429 0442

MAU 0194 0268

MDG 0210 0319

MSR 0178

PAL 0176 0187 0196

S3R 0204

SAA 0197 0378

SAS 0413 0424 0430 0435 0450 0467 0470

SWR 0179 0263

THT 0385 0395 0438 0446

THY 0180 0270 0331

UAE 0185 0190 0202 0236

VCV 0302

VIR 0214 0225

XAX 0273 0278

(4) Configuration by MSN

MSN CONFIGURATION

0176 0178 0179 0180 0182 0185 0186 0187 0190 0192 0193

0194 0196 0197 0199 0201 0202 0204 0207 0208 0210 0212

0213 0214 0215 0216 0217 0218 0220 0221 0225 0227 0228

0233 0235 0236 0237 0239 0242 0243 0245 0246 0252 0257

0260 0263 0264 0268 0270 0273 0274 0278 0280 0282 0292

0297 0302 0304 0307 0310 0318 0319 0321 0325 0327 0329

0331 0332 0335 0347 0352 0354 0355 0359 0363 0367 0373

0374 0377 0378 0379 0381 0385 0387 0390 0395 0399 0402

0406 0411 0413 0414 0415 0424 0429 0430 0433 0434 0435

0438 0442 0446 0447 0450 0459 0467 0470 0474 0483

001

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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@A340

SERVICE BULLETIN

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a

standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Component COMPA01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

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

Frame 40 (FR40), initiating at the first hole aft of FR40 datum. The structural analysis

led to the issue of the Mandatory Inspection Service Bulletin No. A340-57-4089

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

AT FRAME 40 (UNREPAIRED AIRCRAFT)) and the issue of the Recommended

modification Service Bulletin No. A340-57-4106, Modification No. 56467S18944 (WINGS

- CENTER WING BOX-MODIFY FASTENERS INSTALLATION IN THE JUNCTION

KEEL BEAM FITTING AT FR40).

Accomplishment of the Service Bulletin No. A340-57-4106 cancels the inspection

requirements of the Service Bulletin No. A340-57-4089.

The accomplishment Instructions in Service Bulletin No. A340-57-4106 must be

completed for all aircraft belonging to configuration 002 listed in the effectivity of this

Service Bulletin Rev. 01 and Rev. 02.

A missing instruction has been detected in the following cases:

- Either with a crack indication at hole 5 at time of Service Bulletin No. A340-57-4106

Rev. 01 or Rev. 02 accomplishment (Case 1),

- or with a bush installed before Service Bulletin No. A340-57-4106 Rev. 01 or Rev.

02 accomplishment at hole 5 and without a crack indication at hole 5 at time of

Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02 accomplishment (Case 2).

CASE 1:

In case of crack indication during rototest inspection of fastener hole 5 as per Service

Bulletin instructions, adjacent hole 6 has to be cold worked. A rototest inspection has to

be performed before the cold working. However, this instruction is missing in the Service

Bulletin.

CASE 2:

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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@A340

SERVICE BULLETIN

In case of bush installation before Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02

accomplishment at hole 5 and no crack indication at hole 5 reported by rototest per

Service Bulletin instructions, adjacent hole 6 has to be cold worked. A rototest inspection

has to be performed before the cold working. However, this instruction is missing in the

Service Bulletin.

Doing a rototest inspection before the cold working is considered a standard practice.

Nevertheless, two Service Bulletin Information Transmission (SBIT) Ref. 11-0041 and

12-0032 have been issued to inform operators about this occurrence.

Operators Information Transmission (OIT) Ref. 999.0082/12 can also be consulted about

this occurrence.

Eventually this Service Bulletin is issued to settle this matter.

(2) Objective/Action

This Service Bulletin requests a one time ultrasonic inspection of fastener hole 6 in

the junction keel beam fitting at FR40 LH/RH side to ensure that no crack was left

unrepaired at time of fastener hole cold working.

In case of no finding, affected aircraft are inspected as per Airworthiness Limitation

Items (ALI) Task ref. 57-11-63 based on interval value.

In case of finding, AIRBUS repair department will have to be contacted for further repair

instructions.

For aircraft which have not accomplished Service Bulletin No. A340-57-4106 at Rev.

01 or Rev. 02, perform repetitive inspection as per Inspection Service Bulletin No.

A340-57-4089 or apply Service Bulletin No. A340-57-4106 at Rev. 03 or next when

recommended threshold is reached.

(3) Advantages

Accomplishment of this Service Bulletin will avoid extensive repair in the junction keel

beam fitting at FR40.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 574126-832-801-001: Inspection

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

FR40, for access.

(2) Inspect one keel beam fastener hole between FR40 and STGR1.

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

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

REVISION No.: 00 - Jan 25/13 Page: 4

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SERVICE BULLETIN

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. It is anticipated that the AD will confirm the thresholds

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

accomplishment timescale.

Table 1, Config. 001 - Special Detailed inspection of hole 6

Condition Action Compliance Time (whichever occurs first)

Aircraft Model Threshold

FC/FH

(whichever

occurs first)

Grace Period

(whichever

occurs first)

Repetitive

Interval

Perform

repetitive

inspection as

per SB

A340-57-4089

A340-200

(WV002)

and

A340-200

(WV021)

and

A340-300

(WV020 serie)

Refer to A340-57-4089

OR

SB

A340-57-4106

at Rev. 01 or

Rev. 02 not

accomplished.

Apply SB

A340-57-4106

at Rev. 03 or

next.

A340-200

(WV002)

and

A340-200

(WV021)

and

A340-300

(WV020 serie)

Refer to A340-57-4106

SB

A340-57-4106

at Rev. 01 or

Rev. 02

accomplished,

hole 5 bushed

and rototest at

hole 6 made

before cold

working during

SB

A340-57-4106

accomplishment

No further

action in

accordance

with this SB.

Inspect as per

ALI Task

57-11-63.

A340-200

(WV002)

and

A340-200

(WV021)

and

A340-300

(WV020 serie)

At the threshold

given in ALI

Task ref.

57-11-63

None None

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

REVISION No.: 00 - Jan 25/13 Page: 5

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SERVICE BULLETIN

Table 1, Config. 001 - Special Detailed inspection of hole 6

Condition Action Compliance Time (whichever occurs first)

Aircraft Model Threshold

FC/FH

(whichever

occurs first)

Grace Period

(whichever

occurs first)

Repetitive

Interval

SB

A340-57-4106

at Rev. 01 or

Rev. 02

accomplished,

hole 5 bushed

and rototest at

hole 6 not

made before

cold working

during SB

A340-57-4106

accomplishment

Do the

preparation

procedure

(Refer to

SUBTASK

574126-941-001

001 Job Set-up

) and do the

one time

ultrasonic

inspection at

hole 6 (Refer to

SUBTASK

574126-832-002

001 Inspect

one keel beam

fastener hole

between FR40

and STGR1. )

A340-200

(WV002)

and

A340-200

(WV021)

and

A340-300

(WV020 serie)

- FC optimized

set:

4,700FC /

17,700FH

or

- FH optimized

set:

4,250FC /

27,900FH

- 24 months

from SB

issuance date

or

- 1,300FC from

SB issuance

date

None

Crack found on

hole 6

Contact

AIRBUS

A340-200

(WV002)

and

A340-200

(WV021)

and

A340-300

(WV020 serie)

Before next

flight

None None

No crack found

on hole 6

No further

action in

accordance

with this SB.

Inspect as per

ALI Task

57-11-63.

A340-200

(WV002)

and

A340-200

(WV021)

and

A340-300

(WV020 serie)

At the interval

given in ALI

Task ref.

57-11-63

None None

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

REVISION No.: 00 - Jan 25/13 Page: 6

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SERVICE BULLETIN

Table 1, Config. 001 - Special Detailed inspection of hole 6

Condition Action Compliance Time (whichever occurs first)

Aircraft Model Threshold

FC/FH

(whichever

occurs first)

Grace Period

(whichever

occurs first)

Repetitive

Interval

SB

A340-57-4106

at Rev. 01 or

Rev. 02

accomplished,

hole 5 not

bushed and no

crack found on

hole 5 during

SB

A340-57-4106

accomplishment

No further

action in

accordance

with this SB.

Inspect as per

ALI Task

57-11-63.

A340-200

(WV002)

and

A340-200

(WV021)

and

A340-300

(WV020 serie)

At the threshold

given in ALI

Task ref.

57-11-63

None None

SB

A340-57-4106

at Rev. 01 or

Rev. 02

accomplished,

hole 5 not

bushed, crack

found on hole 5

and rototest

made to hole 6

before cold

working during

SB

A340-57-4106

accomplishment

No further

action in

accordance

with this SB.

Inspect as per

ALI Task

57-11-63.

A340-200

(WV002)

and

A340-200

(WV021)

and

A340-300

(WV020 serie)

At the threshold

given in ALI

Task ref.

57-11-63

None None

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

REVISION No.: 00 - Jan 25/13 Page: 7

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SERVICE BULLETIN

Table 1, Config. 001 - Special Detailed inspection of hole 6

Condition Action Compliance Time (whichever occurs first)

Aircraft Model Threshold

FC/FH

(whichever

occurs first)

Grace Period

(whichever

occurs first)

Repetitive

Interval

SB

A340-57-4106

at Rev. 01 or

Rev. 02

accomplished,

hole 5 not

bushed, crack

found on hole 5

and rototest not

made to hole 6

before cold

working during

SB

A340-57-4106

accomplishment

Do the

preparation

procedure

(Refer to

SUBTASK

574126-941-001

001 Job Set-up

) and do the

one time

ultrasonic

inspection at

hole 6 (Refer to

SUBTASK

574126-832-002

001 Inspect

one keel beam

fastener hole

between FR40

and STGR1. )

A340-200

(WV002)

and

A340-200

(WV021)

and

A340-300

(WV020 serie)

- FC optimized

set:

4,700FC /

17,700FH

or

- FH optimized

set:

4,250FC /

27,900FH

- 24 months

from SB

issuance date

or

- 1,300FC from

SB issuance

date

None

Crack found on

hole 6

Contact

AIRBUS

A340-200

(WV002)

and

A340-200

(WV021)

and

A340-300

(WV020 serie)

Before next

flight

None None

No crack found

on hole 6

No further

action in

accordance

with this SB.

Inspect as per

ALI Task

57-11-63.

A340-200

(WV002)

and

A340-200

(WV021)

and

A340-300

(WV020 serie)

At the interval

given in ALI

Task ref.

57-11-63

None None

NOTE: Threshold to be counted from Service Bulletin No. A340-57-4106

accomplishment.

NOTE: For FH and FC optimization on A340 aircraft, operators shall select the

set that better suits aircraft operation and utilization, refer to OIT No.

999.086/11.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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SERVICE BULLETIN

F. APPROVAL

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

Organization Approval No. EASA.21J.031.

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

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

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

G. MANPOWER

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

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

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

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

included.

Task 574126-832-801-001: Inspection

Get Access 10.00

On Aircraft

On the LH and RH sides, remove (if necessary) the

ducts between FR39.1 and FR40, for access.

1.00

Inspect one keel beam fastener hole between FR40

and STGR1.

0.50

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

between FR39.1 and FR40.

1.00

Tests 0.25

Close-Up 10.00

TOTAL MANHOURS 22.75

ELAPSED TIME (HOURS) 22.75

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Airworthiness Limitation Item (ALI) Airworthiness Limitation Items (ALI)

57-11-63

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

21-20-00 21-53-18 36-12-41

53-35-13

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

Non Destructive Test Manual (NTM) 57-11-63

Service Bulletin (SB) A340-57-4089

A340-57-4106

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SERVICE BULLETIN

Standards Manual (SM)

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

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

AIRBUS Material, Logistics and Suppliers do not stock standard hardware as competitive

multiple suppliers ensure access to minimum prices. AIRBUS recommends Customers

with aircraft shown in the effectivity of this Service Bulletin to send a purchase order to

B/E Aerospace. The address is:

Component COMPA01 B/E AEROSPACE INC.

CONSUMABLES MANAGEMENT

10000 NW 15th Terrace Miami

FL 33172

USA

Tel EMEA: +49 (0) 40 822 285 31500

Tel US: +1 305 925 2600

Tel ASIA: +1 310 900 1300

Fax EMEA: +49 (0) 40 822 285 31010

Fax US: +1 305 507 7191

Fax ASIA: +1 310 819 1200

SITA: MIAMMCR

E-Mail: AOGdesk_CMG@beaerospace.com

internet: http://www.beconsumables.com

or, alternatively any other source on the open

market.

(2) Price and Availability

No AIRBUS kit will be provided.

Operator supplied standard hardware parts required to accomplish this Service Bulletin

are to be supplied from the Operator’s stock.

B. INDUSTRY SUPPORT INFORMATION

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

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

None

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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(2) Components

Component COMPA01

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

NOTES

10 MS21071-3 1 NUT

15 NSA5050-4 2 NUT

NOTE: If you find part numbers of hardware components in the related kit(s)

which you cannot identify in the LIST OF COMPONENTS of this Service

Bulletin, refer to Standards Manual (SM). The SM will give you the

correct part number to part number relationship.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 574126-832-801-001 - Inspection

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

Task Associated Data

Manpower

TOTAL MANHOURS 22.75

ELAPSED TIME (HOURS) 22.75

A. GENERAL

NOTE: The purpose of flow charts is to supplement the information given in the

Procedure and Compliance paragraphs and not to serve as the primary

source for tasks or compliance times given in this Service Bulletin.

(1) Subtask 574126-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(b) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-801.

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(c) Remove and install fasteners in accordance with SRM 51-42-00.

(d) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.

(2) Subtask 574126-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

(a) Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

B. PREPARATION

(1) Subtask 574126-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 21-20-00-010-801

Task 21-53-18-000-801

Task 36-12-41-000-801

Task 53-35-13-000-802

NOTE: Access to aircraft is only necessary to allow the ultrasonic inspection at

hole 6. Before this step you have to check your Service Bulletin reports

to see if this ultrasonic inspection is necessary.

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(b) Put access platform(s) in position.

(c) Do the Job Set-up as specified in the Removal of the air-conditioning distribution

ducts, refer to AMM Task 21-20-00-010-801.

(d) Do the Job Set-up procedure as specified in the Removal of the pack discharge

temperature-sensor (542HH), refer to AMM Task 21-53-18-000-801.

(e) Do the Job Set-up procedure as specified in the Removal of the APU bleed-air

ducts, refer to AMM Task 36-12-41-000-801.

(f) Remove the Belly Fairing Access-Panels 191FB for the LH side and 192GB for the

RH side, refer to AMM Task 53-35-13-000-802.

(g) Get access to the work area.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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C. PROCEDURE

(1) Subtask 574126-832-001-001 - On the LH and RH sides, remove (if necessary) the

ducts between FR39.1 and FR40, for access.

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-53-18-000-801

Task 36-12-41-000-801

Structural Repair Manual (SRM) 51-42-00

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 for access

Sheet 01

Fig. A-FBBAA

Removal/Installation of the Ventilation

ducts between FR39.1 and FR40 for

access

Sheet 01

(a) On RH side, remove the air conditioning duct.

Refer to Fig. A-FBAAA Sheet 01

Refer to SRM 51-42-00

1 Remove :

1 Duct Item (8) Retain

1 Insulation Item (9) Retain

1 Nut Item (10) Discard

1 Bolt Item (11) Retain

1 Washer Item (12) Retain

2 Screw Item (13) Retain

2 Washer Item (14) Retain

2 Nut Item (15) Discard

1 Clamp Item (16) Retain

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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1 Clamp Item (17) Retain

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

removal.

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

(17) from the duct Item (8) only if necessary.

NOTE (03): For the removal of the sensor 542HH, refer to AMM Task

21-53-18-000-801.

(b) On RH side, remove the air ventilation duct.

Refer to Fig. A-FBBAA Sheet 01

Refer to SRM 51-42-00

1 Remove :

1 Duct Item (20) Retain

4 Clamp Item (21) Retain

8 Clamp Item (22) Retain

1 Sleeve Item (23) Retain

2 Sleeve Item (24) Retain

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

and FR40, refer to AMM Task 36-12-41-000-801.

(d) Put the blanking plugs on the disconnected line ends.

(2) Subtask 574126-832-002-001 - Inspect one keel beam fastener hole between FR40

and STGR1.

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Airworthiness Limitation Item (ALI) Airworthiness Limitation Items (ALI)

57-11-63

Non Destructive Test Manual (NTM) 57-11-63

Service Bulletin (SB) A340-57-4089

A340-57-4106

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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References

Fig. A-FBCAA

Inspection of Hole 6 in the junction keel

beam

Sheet 01

Sheet 02

(a) At the threshold given in the PLANNING INFORMATION paragraph 1.E.(2):

Do a special detailed inspection of hole 6 in the junction keel beam fitting at FR40.

1 If Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02 is not accomplished:

a Perform repetitive inspection as per Inspection Service Bulletin No.

A340-57-4089

or

Apply Service Bulletin No. A340-57-4106 at Rev. 03 or next when

recommended threshold is reached.

2 If Service Bulletin No. A340-57-4106 Rev. 01 or Rev. 02 is accomplished:

a Do the inspection of the Hole 6.

Refer to Fig. A-FBCAA Sheet 01 and Fig. A-FBCAA Sheet 02

<1> Hole 5 has been already bushed before Service Bulletin No.

A340-57-4106 accomplishment:

<a> If Rototest at Hole 6 was made before cold working during

Service Bulletin No. A340-57-4106 accomplishment:

[1] No further action for Hole 6 in accordance with this

Service Bulletin (Hole 6 is covered by Airworthiness

Limitation Items (ALI) Task ref. 57-11-63).

[2] Inspect Hole 6 at the threshold of the Airworthiness

Limitation Items (ALI) Task ref. 57-11-63.

<b> If Rototest at Hole 6 was not made before cold working during

Service Bulletin No. A340-57-4106 accomplishment:

[1] Do the preparation procedure, refer to SUBTASK

574126-941-001 001 Job Set-up .

[2] Do the one time ultrasonic inspection of the Hole 6, refer

to NTM 57-11-63.

[3] If crack found on Hole 6:

[a] Contact AIRBUS before next flight.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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[4] If crack not found on Hole 6:

[a] Send inspection report to AIRBUS, refer to Appendix

01: Inspection Report .

[b] No further action on Hole 6 in accordance with this

Service Bulletin.

[c] Re-inspect the Hole 6 as per Airworthiness Limitation

Items (ALI) Task ref. 57-11-63, at the task interval,

refer to NTM 57-11-63.

<2> Hole 5 has not been already bushed before Service Bulletin No.

A340-57-4106 accomplishment:

<a> Crack not found on Hole 5 during Service Bulletin No.

A340-57-4106 accomplishment:

[1] No further action on Hole 6 in accordance with this

Service Bulletin (Hole 6 is covered by Airworthiness

Limitation Items (ALI) Task ref. 57-11-63).

[2] Inspect Hole 6 at the threshold of the Airworthiness

Limitation Items (ALI) Task ref. 57-11-63.

<b> Crack found on Hole 5 during Service Bulletin No.

A340-57-4106 accomplishment:

[1] If Rototest at Hole 6 was made before cold working during

Service Bulletin No. A340-57-4106 accomplishment:

[a] No further action on Hole 6 in accordance with this

Service Bulletin (Hole 6 is covered by Airworthiness

Limitation Items (ALI) Task ref. 57-11-63).

[b] Inspect Hole 6 at the threshold of the Airworthiness

Limitation Items (ALI) Task ref. 57-11-63.

[2] If Rototest at Hole 6 was not made before cold

working during Service Bulletin No. A340-57-4106

accomplishment:

[a] Do the preparation procedure, refer to SUBTASK

574126-941-001 001 Job Set-up .

[b] Do the one time ultrasonic inspection of the Hole 6,

refer to NTM 57-11-63.

[c] If crack found on Hole 6:

- Contact AIRBUS before next flight.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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[d] If crack not found on Hole 6:

- Send inspection report to AIRBUS, refer to

Appendix 01: Inspection Report .

- No further action on Hole 6 in accordance with

this Service Bulletin.

- Re-inspect the Hole 6 as per Airworthiness

Limitation Items (ALI) Task ref. 57-11-63, at the

task interval, refer to NTM 57-11-63.

(b) Send inspection report to AIRBUS, refer to Appendix 01: Inspection Report .

(3) Subtask 574126-832-003-001 - On the LH and RH sides, install (if removed) the

ducts between FR39.1 and FR40.

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 MS21071-3 1 NUT

15 NSA5050-4 2 NUT

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801

Task 21-53-18-400-801

Task 36-12-41-400-801

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FBAAA

Removal/Installation of the Air

Conditioning Ducts between FR39.1 and

FR40 for access

Sheet 01

Fig. A-FBBAA

Removal/Installation of the Ventilation

ducts between FR39.1 and FR40 for

access

Sheet 01

(a) Remove the blanking plugs on the disconnected line ends.

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

and FR40, refer to AMM Task 36-12-41-400-801.

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

Refer to Fig. A-FBAAA Sheet 01

Refer to AMM Task 20-21-11-911-801

Refer to SRM 51-42-00 and SRM 51-43-00

1 Install:

1 Duct Item (20) Retained at

removal

4 Clamp Item (21) Retained at

removal

8 Clamp Item (22) Retained at

removal

1 Sleeve Item (23) Retained at

removal

2 Sleeve Item (24) Retained at

removal

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

Refer to Fig. A-FBBAA Sheet 01

Refer to AMM Task 20-21-11-911-801

Refer to SRM 51-42-00 and SRM 51-43-00

1 Install:

1 Duct Item (8) Retained at

removal

1 Insulation Item (9) Retained at

removal

1 Nut MS21071-3 Item 10

1 Bolt Item (11) Retained at

removal

1 Washer Item (12) Retained at

removal

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2 Screw Item (13) Retained at

removal

2 Washer Item (14) Retained at

removal

2 Nut NSA5050-4 Item 15

1 Clamp Item (16) Retained at

removal

1 Clamp Item (17) Retained at

removal

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

NOTE (02): For the installation of the sensor 542HH, refer to AMM Task

21-53-18-400-801.

D. TEST

(1) Subtask 574126-700-001-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 53-35-13-400-802

(a) Remove the safety clip(s) and/or tag(s) and close/unlock the circuit breaker(s) as

specified in the Installation of the Belly Fairing Access-Panels, refer to AMM Task

53-35-13-400-802.

E. CLOSE-UP

(1) Subtask 574126-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801

Task 21-53-18-400-801

Task 36-12-41-400-801

Task 53-35-13-400-802

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

equipment.

(b) Install the Belly Fairing Access-Panels 191FB for the LH side and 192GB for the

RH side, refer to AMM Task 53-35-13-400-802.

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(c) Do the Close-up procedure as specified after the Installation of the Belly Fairing

Access-Panels, refer to AMM Task 53-35-13-400-802.

(d) Do the Close-up procedure as specified after the Installation of the APU bleed-air

ducts, refer to AMM Task 36-12-41-400-801.

(e) Do the Close-up procedure as specified after the Installation of the pack discharge

temperature-sensor (542HH), refer to AMM Task 21-53-18-400-801.

(f) Do the Close-up procedure as specified after the Installation of the air-conditioning

distribution ducts, refer to AMM Task 21-20-00-410-801.

(g) Remove access platform(s).

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

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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**CONF ALL

A

FR40.2

FR39.2

B

(9) (18)

(15) (17)

(8)

(16)

(10)

(11)

(12)

(13)

(14) (19)

(15)

(13)

(14)

542HH

A

B

Z190

15

15

10

F_SB_574126_5_BAAA_01_01

Figure A-FBAAA - Sheet 01

Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 for access

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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SERVICE BULLETIN

**CONF ALL

A

B

C D

C

D

D

B

FR40

FR47

(20)

(21)

(22)

(23)

(24)

(21)

(22)

C

D

C

D

C

D

A

Z190

F_SB_574126_5_BBAA_01_00

Figure A-FBBAA - Sheet 01

Removal/Installation of the Ventilation ducts between FR39.1 and FR40 for access

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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SERVICE BULLETIN

**CONF ALL

LH SIDE SHOWN

RH SIDE SYMMETRICAL

VIEW INSIDE CENTER TANK AT FR40

DATUM

Y1959

FR40

FR47

B

A

B

B

C

FR40

STGR1

A

Z141 Z142 − 

F_SB_574126_5_BCAA_01_00

Figure A-FBCAA - Sheet 01

Inspection of Hole 6 in the junction keel beam

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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SERVICE BULLETIN

**CONF ALL

Y1959

VIEW SIDE CENTRE TANK AT FR 40

FASTENER NOT AFFECTED

HOLE 6

CENTER WING BOX

LOWER PANEL

HOLE TO BE INSPECTED

AREA TO BE INSPECTED

FR40 DATUM

STGR1

F

W

D C

D D

KEEL BEAM

FITTING

STGR1

FR40

D

D

TYPICAL

F_SB_574126_5_BCAA_02_03

Figure A-FBCAA - Sheet 02

Inspection of Hole 6 in the junction keel beam

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

RE−INSPECT THE HOLE 6 AT THE

INTERVAL OF THE ALI 57.11.63

CRACK FOUND

ON HOLE 6

DO THE ONE TIME ULTRASONIC INSPECTION

AT HOLE 6, AT THE THRESHOLD GIVEN IN THE

PLANNING INFORMATION PARAGRAPH E.(2).

REFER TO SUBTASK 574126−832−002−001

INSPECT THE HOLE 6 AT THE

THRESHOLD OF THE ALI 57.11.63

CRACK FOUND

ON HOLE 5 DURING SB 57−4106

ACCOMPLISHMENT

HOLE 5 ALREADY

BUSHED BEFORE SB 57−4106

ACCOMPLISHMENT

SB 57−4106

REV. 01 OR REV. 02

EMBODIED

PERFORM REPETITIVE INSPECTION AS

REV.03 OR NEXT WHEN RECOMMENDED 

THRESHOLD IS REACHED

DO A SPECIAL DETAILED INSPECTION OF ONE FASTERNER HOLE IN THE

JUNCTION KEEL BEAM FITTING AT FR40 AT THE THRESHOLD GIVEN IN

THE PLANNING INFORMATION PARAGRAPH E.(2).

REFER TO SUBTASK 574126−832−002−001

YES

CHECK YOUR SERVICE BULLETIN REPORTS AND IF NECESSARY

NO YES

NO

PER ISB 57−4089 OR APPLY SB 57−4106 AT 

NO YES

YES NO

ROTOTEST AT

HOLE 6 MADE PRIOR TO

COLD WORKING DURING SB 57−4106

ACCOMPLISHMENT

NO FURTHER ACTION

HOLE 6

REFER TO SUBTASK 574126−941−001−001

DO THE PREPARATION PROCEDURE

NO YES

CONTACT AIRBUS

BEFORE NEXT FLIGHT

NO FURTHER ACTION

HOLE 6

F_SB_574126_5_FAAA_01_02

Figure A-FFAAA - Sheet 01

Flow Chart

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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This Page Intentionally Left Blank

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SERVICE BULLETIN

Appendix 01: Inspection Report

**CONF ALL

(1) The results of the inspection, including no findings, replacement or actions to be done, must be

forwarded to AIRBUS Department SEES1, on the attached inspection report sheet.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

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SERVICE BULLETIN

Appendix 01: Inspection Report

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A340−57−4126

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − 

INSPECTION METHOD : SPECIAL DETAILED

INSPECTION

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

E−mail: structure.sbinspectionresult@airbus.com

FAX +33 (0)5 61 93 36 14

YES NO

YES NO

YES NO

YES NO

SIDE

HOLE 6

HOLE 6

LH

RH

ULTRASONIC CRACK FOUND ? INSPECTION ?

F_SB_574126_5_RAAA_01_02

Figure A-FRAAA - Sheet 01

Inspection Report

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REPORTING SHEET

TITLE: WINGS - CENTER WING BOX - INSPECTION OF ONE FASTENER HOLE

IN THE JUNCTION KEEL BEAM FITTING AT FRAME 40

MODIFICATION No.: None

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

REVISION No.: 00 - Jan 25/13 Page: 1

5

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

SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

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

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Jan 25/13 SERVICE BULLETIN No.: A340-57-4126

REVISION No.: 00 - Jan 25/13 Page: 1

5

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