@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 FASTENER HOLES AT

FRAME 40 VERTICAL WEB BELOW INTRADOS

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During ALI 57.11.04 inspections tasks on the rear fitting of the Frame 40 between stringer 38 and 39

LH/RH side, cracks have been found on the fasteners next to the one to be inspected (for the

configuration PRE MOD 44360). After reaming at second oversize of the subjected hole, the crack is

still present.

This Service Bulletin mandates the Inspection of the fasteners holes at Frame 40 Vertical Web between

stringer 38 and 39 below Intrados, left and right sides for all A340 aircraft pre-modification 49202 and

post-modification 44360 embodiments. The aim of this Inspection Service Bulletin is to implement the

corrective inspection necessary to the in-service aircraft.

For aircraft previously inspected as per Technical Disposition Ref. LR57D11023270 or

LR57D11029173, next inspection is due based on interval value given in this ISB or dedicated RDAS

instructions requirements in case of deviations to the TD instructions.

Accomplishment of this ISB will permit early detection of cracks on the Frame 40 Vertical Web between

stringer 38 and 39 below Intrados, left and right sides and will ensure that the structural integrity of the

area is maintained.

The Task ALI 57.11.04 applicable to aircraft post-mod 44360 will be superseded by accomplishment of

ISB 57-4125.

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

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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SERVICE BULLETIN

SUMMARY

EVALUATION TABLE

COST SAVING NO LROPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 574125A01R02 2 41,900.00 Screws, Nuts

EFFECTIVITY

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

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

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

UAE VIR XAX

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU 57.11.00.007

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER OIT Ref. 999.0082/12

OTHER OIT Ref. 999.0086/11

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 574125-832-801-001: Inspection

TOTAL MANHOURS 38.75

ELAPSED TIME (HOURS) 38.75

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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@A340

SERVICE BULLETIN

SUMMARY

Task 574125-833-801-001: Repair

TOTAL MANHOURS 53.75

ELAPSED TIME (HOURS) 53.75

APPENDICES

Appendix 01: Inspection Report

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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SERVICE BULLETIN

SUMMARY

**CONF ALL

FR40

RH SIDE SHOWN

LH SIDE SYMMETRICAL

NOTES:

HOLES OF AREA A TO BE INSPECTED

HOLES OF AREA B TO BE INSPECTED

HOLE OF AREA C TO BE INSPECTED VIEW LOOKING AFT

FR47

FR40

B

B A

B

A Z141 Z142 − 

F_SB_574125_5_SAAA_01_01

Figure A-FSAAA - Sheet 01

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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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 FASTENER HOLES AT

FRAME 40 VERTICAL WEB BELOW INTRADOS

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

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

No. 44360S13013 and 44360S13482 are embodied and modification

49202S16307 is not embodied.

(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 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

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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SERVICE BULLETIN

(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.

OPERATOR MSN

83V 0235 0280 0292

ABD 0210

ABQ 0216 0257

AFR 0186 0207 0237 0245 0246 0260 0307 0310 0377 0399

AIB 0182 0302 0318 0332

ALK 0367 0374 0381

ARG 0373

CAL 0402 0406 0411 0415 0433

CCA 0192 0199 0201 0242 0243 0264

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

HFY 0190

IBE 0193 0217 0221 0329 0387 0414 0459 0474 0483

LAN 0359 0363 0429 0442

MAU 0194 0268

MDG 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 0202 0236

VIR 0214 0225

XAX 0273 0278

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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SERVICE BULLETIN

(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 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

(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

Kit 574125A01R02 2

Consumable CMLA01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During ALI 57.11.04 inspections tasks on the rear fitting of the Frame 40 between

stringer 38 and 39 LH/RH side, cracks have been found on the fasteners next to the

one to be inspected (for the configuration PRE MOD 44360). After reaming at second

oversize of the subjected hole, the crack is still present.

(2) Objective/Action

This Service Bulletin mandates the Inspection of the fasteners holes at Frame 40

Vertical Web between stringer 38 and 39 below Intrados, left and right sides for all A340

aircraft pre-modification 49202 and post-modification 44360 embodiments. The aim of

this Inspection Service Bulletin is to implement the corrective inspection necessary to the

in-service aircraft.

For aircraft previously inspected as per Technical Disposition Ref. LR57D11023270 or

LR57D11029173, next inspection is due based on interval value given in this ISB or

dedicated RDAS instructions requirements in case of deviations to the TD instructions.

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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SERVICE BULLETIN

(3) Advantages

Accomplishment of this ISB will permit early detection of cracks on the Frame 40 Vertical

Web between stringer 38 and 39 below Intrados, left and right sides and will ensure that

the structural integrity of the area is maintained.

(4) Operational/Maintenance Consequences

The Task ALI 57.11.04 applicable to aircraft post-mod 44360 will be superseded by

accomplishment of ISB 57-4125.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 574125-832-801-001: Inspection

(1) Do a Special Detailed Inspection of the Fastener Holes of the Areas A and C at

FR40, LH Side

(2) Do a Special Detailed Inspection of the Fastener Holes of the Areas A and C at

FR40, RH Side

(3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR40, LH

Side

(4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR40, RH

Side

(5) Do a rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Holes of the

Areas A and C of the Frame 40, LH Side

(6) Do a rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Holes of the

Areas A and C of the Frame 40, RH Side

(7) Do a Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Holes of the

Areas A and C of the Frame 40, LH Side

(8) Do a Rototest Inspection Post Service Bulletin No. A340-57-4090 of the Holes of the

Areas A and C of the Frame 40, RH Side

(9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side

(10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side

Task 574125-833-801-001: Repair

(1) Install new same Fasteners Pre Service Bulletin No. A340-57-4090 of the Areas A

and C in transition fit, LH Side

(2) Install new same Fasteners Pre Service Bulletin No. A340-57-4090 of the Areas A

and C in transition fit, RH Side

(3) Install new same Fasteners Post Service Bulletin No. A340-57-4090 of the Areas A

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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SERVICE BULLETIN

and C in transition fit, LH Side

(4) Install new same Fasteners Post Service Bulletin No. A340-57-4090 of the Areas A

and C in transition fit, RH Side

(5) Install new same Fasteners of the Area B in transition fit, LH Side

(6) Install new same Fasteners of the Area B in transition fit, RH Side

(7) Oversize the Holes to the First Oversize in comparison with the current Hole

diameter of the Areas A and C Pre Service Bulletin No. A340-57-4090, LH Side

(8) Oversize the Holes to the First Oversize in comparison with the current Hole

diameter of the Areas A and C Pre Service Bulletin No. A340-57-4090, RH Side

(9) Oversize the Holes to the First Oversize in comparison with the current Hole

diameter of the Areas A and C Post Service Bulletin No. A340-57-4090, LH Side

(10) Oversize the Holes to the First Oversize in comparison with the current Hole

diameter of the Areas A and C Post Service Bulletin No. A340-57-4090, RH Side

(11) Oversize the Holes to the First Oversize in comparison with the current Hole

diameter of the Area B, LH Side

(12) Oversize the Holes to the First Oversize in comparison with the current Hole

diameter of the Area B, RH Side

(13) Install new Fasteners Pre Service Bulletin No. A340-57-4090 of the Areas A and C

in transition fit, LH Side

(14) Install new Fasteners Pre Service Bulletin No. A340-57-4090 of the Areas A and C

in transition fit, RH Side

(15) Install new Fasteners Post Service Bulletin No. A340-57-4090 of the Areas A and C

in transition fit, LH Side

(16) Install new Fasteners Post Service Bulletin No. A340-57-4090 of the Areas A and C

in transition fit, RH Side

(17) Install new Fasteners of the Area B in transition fit, LH Side

(18) Install new Fasteners of the Area B in transition fit, RH Side

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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SERVICE BULLETIN

(2) Accomplishment Timescale

Table 1: Special Detailed Inspection of the Fasteners Holes of the Areas A and C of the frame 40, LH

and RH sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Do a Rototest

Inspection Pre SB

No. A340-57-4090

on LH and RH

Sides, refer to

SUBTASK

574125-832-005

001 for LH Side

and to SUBTASK

574125-832-006

001 for RH Side

Refer to table 3

OR

Apply Service

Bulletin No.

A340-57-4090

and

Before next flight

Config. 001 Pre

Service Bulletin

No. A340-57-4090

Do a Rototest

Inspection Post SB

No. A340-57-4090

on LH and RH

Sides, refer to

SUBTASK

574125-832-007

001 for LH Side

and to SUBTASK

574125-832-008

001 for RH Side

Refer to table 4

Perform this rototest at the Threshold from SB No.

A340-57-4090 embodiment

Config. 001 Post

Service Bulletin

No. A340-57-4090

Do a Rototest

Inspection Post SB

No. A340-57-4090

on LH and RH

Sides, refer to

SUBTASK

574125-832-007

001 for LH Side

and to SUBTASK

574125-832-008

001 for RH Side

Refer to table 4

Perform this rototest at the Threshold from SB No.

A340-57-4090 embodiment

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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SERVICE BULLETIN

Table 2: Special Detailed Inspection of the Fasteners Holes of the Area B of the frame 40, LH and RH

sides

Condition Action Compliance Time

Threshold

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

Config. 001 Do a Rototest

Inspection on LH

and RH Sides,

refer to SUBTASK

574125-832-009

001 for LH Side

and to SUBTASK

574125-832-010

001 for RH Side

Refer to table 5

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fasteners Holes of the

Areas A and C of the frame 40, LH and RH sides

Condition Action Compliance Time

Threshold from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

A340-200

WV002

FC optimized

set: 19,300 FC

/77,300 FH

or

FH optimized

set: 16,400 FC

/111,200 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

A340-200

WV021

FC optimized

set: 15,900 FC

/63,600 FH

or

FH optimized

set: 13,500 FC

/91,500 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

Config. 001 Pre

Service Bulletin

No.

A340-57-4090

A340-300

WV020 Serie

Do a Rototest

Inspection Pre

SB No.

A340-57-4090

on LH and RH

Sides, refer to

SUBTASK

574125-832-005

001 for LH Side

and to

SUBTASK

574125-832-006

001 for RH

Side

FC optimized

set: 15,900 FC

/63,600 FH

or

FH optimized

set: 13,500 FC

/91,500 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 7

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SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fasteners Holes of the

Areas A and C of the frame 40, LH and RH sides

Condition Action Compliance Time

Threshold from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A340WV Install New

same fasteners

in transition fit

Pre SB No.

A340-57-4090

on LH and/or

RH Sides, refer

to SUBTASK

574125-833-001

001 for LH Side

and/or to

SUBTASK

574125-833-002

001 for RH

Side

and

Before next

flight

None None

A340-200

WV002

None None FC optimized

set: 9,200 FC

/36,900 FH

or

FH optimized

set: 7,650 FC

/51,800 FH

See NOTE (*)

A340-200

WV021

None None FC optimized

set: 6,650 FC

/26,700 FH

or

FH optimized

set: 5,550 FC

/37,600 FH

See NOTE (*)

No Crack found

A340-300

WV020 Serie

Repeat the

Rototest

Inspection of

the holes Pre

SB No.

A340-57-4090

on LH and/or

RH Sides, refer

to SUBTASK

574125-832-005

001 for LH Side

and/or to

SUBTASK

574125-832-006

001 for RH

Side

None None FC optimized

set: 6,650 FC

/26,700 FH

or

FH optimized

set: 5,550 FC

/37,600 FH

See NOTE (*)

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fasteners Holes of the

Areas A and C of the frame 40, LH and RH sides

Condition Action Compliance Time

Threshold from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

OR

Apply Service

Bulletin No.

A340-57-4090

and

Before next

flight

None None

No crack found

All A340WV

Do a Rototest

Inspection Post

SB No.

A340-57-4090

on LH and RH

Sides, refer to

SUBTASK

574125-832-007

001 for LH Side

and to

SUBTASK

574125-832-008

001 for RH

Side

Refer to table 4

Perform this rototest at the Threshold from SB No.

A340-57-4090 embodiment

Crack found All A340WV Oversize the

holes to first

oversize in

comparison

with the current

hole diameter

Pre SB No.

A340-57-4090

on LH and/or

RH Sides, refer

to SUBTASK

574125-833-007

001 for LH Side

and/or to

SUBTASK

574125-833-008

001 for RH

Side and Do a

Rototest

Inspection

Before next

flight

None None

Crack found

after Rototest

Inspection

All A340WV Contact Airbus Before next

flight

None None

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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SERVICE BULLETIN

Table 3: Rototest Inspection Pre Service Bulletin No. A340-57-4090 of the Fasteners Holes of the

Areas A and C of the frame 40, LH and RH sides

Condition Action Compliance Time

Threshold from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A340WV Install new

fasteners in

transition fit Pre

SB No.

A340-57-4090

on LH and/or

RH Sides, refer

to SUBTASK

574125-833-013

001 for LH Side

and/or to

SUBTASK

574125-833-014

001 for RH

Side

and

Before next

flight

None None

A340-200

WV002

None None FC optimized

set: 9,200 FC

/36,900 FH

or

FH optimized

set: 7,650 FC

/51,800 FH

See NOTE (*)

A340-200

WV021

None None FC optimized

set: 6,650 FC

/26,700 FH

or

FH optimized

set: 5,550 FC

/37,600 FH

See NOTE (*)

No Crack found

after Rototest

Inspection

A340-300

WV020 Serie

Repeat the

Rototest

Inspection of

the holes Pre

SB No.

A340-57-4090

on LH and/or

RH Sides, refer

to SUBTASK

574125-832-005

001 for LH Side

and/or to

SUBTASK

574125-832-006

001 for RH

Side

None None FC optimized

set: 6,650 FC

/26,700 FH

or

FH optimized

set: 5,550 FC

/37,600 FH

See NOTE (*)

NOTE: NOTE (*): For FH and FC optimization on A330/A340 aircraft, operators shall select

the set that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the fasteners holes of the

Areas A and C of the frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold from

SB 57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

A340-200

WV002

FC optimized

set: 48,900

FC/195,800 FH

or

FH optimized

set: 36,800 FC

/248,500 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

A340-200

WV021

FC optimized

set: 32,000 FC

/128,200 FH

or

FH optimized

set: 24,100 FC

/162,700 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

Config. 001

Post Service

Bulletin No.

A340-57-4090

A340-300

WV020 Serie

Do a Rototest

Inspection Post

SB No.

A340-57-4090

on LH and RH

Sides, refer to

SUBTASK

574125-832-007

001 for LH Side

and to

SUBTASK

574125-832-008

001 for RH

Side

FC optimized

set: 32,000 FC

/128,200 FH

or

FH optimized

set: 24,100 FC

/162,700 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 11

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SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the fasteners holes of the

Areas A and C of the frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold from

SB 57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A340WV Install new

same fasteners

in transition fit

Post SB No.

A340-57-4090

on LH and/or

RH Sides, refer

to SUBTASK

574125-833-003

001 for LH Side

and/or to

SUBTASK

574125-833-004

001 for RH

Side

and

Before next

flight

None None

A340-200

WV002

None None FC optimized

set: 9,200 FC

/36,900 FH

or

FH optimized

set: 7,650 FC

/51,800 FH

See NOTE (*)

A340-200

WV021

None None FC optimized

set: 6,650 FC

/26,700 FH

or

FH optimized

set: 5,550 FC

/37,600 FH

See NOTE (*)

No crack found

A340-300

WV020 Serie

Repeat the

Rototest

Inspection of

the holes Post

SB No.

A340-57-4090

on LH and/or

RH Sides, refer

to SUBTASK

574125-832-007

001 for LH Side

and/or to

SUBTASK

574125-832-008

001 for RH

Side

None None FC optimized

set: 6,650 FC

/26,700 FH

or

FH optimized

set: 5,550 FC

/37,600 FH

See NOTE (*)

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 12

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@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the fasteners holes of the

Areas A and C of the frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold from

SB 57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

Crack found All A340WV Oversize the

holes to first

oversize in

comparison

with the current

hole diameter

on LH and/or

RH Sides, refer

to SUBTASK

574125-833-009

001 for LH Side

and/or to

SUBTASK

574125-833-010

001 for RH

Side and do a

Rototest

Inspection

Before next

flight

None None

Crack found

after Rototest

Inspection

All A340WV Contact Airbus Before next

flight

None None

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 13

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@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the fasteners holes of the

Areas A and C of the frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold from

SB 57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A340WV Install new

fasteners in

transition fit

Post SB No.

A340-57-4090

on LH and/or

RH Sides, refer

to SUBTASK

574125-833-015

001 for LH Side

and/or to

SUBTASK

574125-833-016

001 for RH

Side

and

Before next

flight

None None

A340-200

WV002

None None FC optimized

set: 9,200 FC

/36,900 FH

or

FH optimized

set: 7,650 FC

/51,800 FH

See NOTE (*)

A340-200

WV021

None None FC optimized

set: 6,650 FC

/26,700 FH

or

FH optimized

set: 5,550 FC

/37,600 FH

See NOTE (*)

No Crack found

after Rototest

Inspection

A340-300

WV020 Serie

Repeat the

Rototest

Inspection of

the holes Post

SB No.

A340-57-4090

on LH and/or

RH Sides, refer

to SUBTASK

574125-832-007

001 for LH Side

and/or to

SUBTASK

574125-832-008

001 for RH

Side

None None FC optimized

set: 6,650 FC

/26,700 FH

or

FH optimized

set: 5,550 FC

/37,600 FH

See NOTE (*)

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 14

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@A340

SERVICE BULLETIN

Table 4: Rototest Inspection Post Service Bulletin No. A340-57-4090 of the fasteners holes of the

Areas A and C of the frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold from

SB 57-4090

embodiment

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

NOTE: NOTE (*): For FH and FC optimization on A330/A340 aircraft, operators shall select

the set that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

Table 5: Rototest Inspection of the fasteners holes of the Area B of the frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

A340-200

WV002

FC optimized

set: 19,300 FC

/77,300 FH

or

FH optimized

set: 16,400 FC

/111,200 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

A340-200

WV021

FC optimized

set: 15,900 FC

/63,600 FH

or

FH optimized

set: 13,500 FC

/91,500 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

Config. 001

A340-300

WV020 Serie

Do a Rototest

Inspection on

LH and RH

Sides, refer to

SUBTASK

574125-832-009

001 for LH Side

and to

SUBTASK

574125-832-010

001 for RH

Side

FC optimized

set: 15,900 FC

/63,600 FH

or

FH optimized

set: 13,500 FC

/91,500 FH

See NOTE (*)

1,300 FC or 24

months from

SB issuance

date

None

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 15

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SERVICE BULLETIN

Table 5: Rototest Inspection of the fasteners holes of the Area B of the frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A340WV Install new

same fasteners

in transition fit

on LH and/or

RH Sides, refer

to SUBTASK

574125-833-005

001 for LH Side

and/or to

SUBTASK

574125-833-006

001 for RH

Side

and

Before next

flight

None None

A340-200

WV002

None None FC optimized

set: 9,200 FC

/36,900 FH

or

FH optimized

set: 7,650 FC

/51,800 FH

See NOTE (*)

A340-200

WV021

None None FC optimized

set: 6,650 FC

/26,700 FH

or

FH optimized

set: 5,550 FC

/37,600 FH

See NOTE (*)

No Crack found

A340-300

WV020 Serie

Repeat the

Rototest

Inspection on

LH and/or RH

Sides, refer to

SUBTASK

574125-832-009

001 for LH Side

and/or to

SUBTASK

574125-832-010

001 for RH

Side

None None FC optimized

set: 6,650 FC

/26,700 FH

or

FH optimized

set: 5,550 FC

/37,600 FH

See NOTE (*)

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 16

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@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the fasteners holes of the Area B of the frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

Crack found All A340WV Oversize the

holes to first

oversize in

comparison

with the current

hole diameter

on LH and/or

RH Sides, refer

to SUBTASK

574125-833-011

001 for LH Side

and/or to

SUBTASK

574125-833-012

001 for RH

Side and do a

Rototest

Inspection

Before next

flight

None None

Crack found

after Rototest

Inspection

All A340WV Contact Airbus Before next

flight

None None

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 17

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@A340

SERVICE BULLETIN

Table 5: Rototest Inspection of the fasteners holes of the Area B of the frame 40, LH and RH Sides

Condition Action Compliance Time

Threshold from

first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

All A340WV Install new

fasteners in

transition fit on

LH and/or RH

Sides, refer to

SUBTASK

574125-833-017

001 for LH Side

and/or to

SUBTASK

574125-833-018

001 for RH

Side

and

Before next

flight

None None

A340-200

WV002

None None FC optimized

set: 9,200 FC

/36,900 FH

or

FH optimized

set: 7,650 FC

/51,800 FH

See NOTE (*)

A340-200

WV021

None None FC optimized

set: 6,650 FC

/26,700 FH

or

FH optimized

set: 5,550 FC

/37,600 FH

See NOTE (*)

No Crack found

after Rototest

Inspection

A340-300

WV020 Serie

Repeat the

Rototest

Inspection of

the holes on LH

and/or RH

Sides, refer to

SUBTASK

574125-832-009

001 for LH Side

and/or to

SUBTASK

574125-832-010

001 for RH

Side

None None FC optimized

set: 6,650 FC

/26,700 FH

or

FH optimized

set: 5,550 FC

/37,600 FH

See NOTE (*)

NOTE: NOTE (*): For FH and FC optimization on A330/A340 aircraft, operators shall select

the set that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 18

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SERVICE BULLETIN

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

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

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

Organisation Approval No. EASA.21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

Task 574125-832-801-001: Inspection

Get Access 13.00

On Aircraft

Do a Special Detailed Inspection of the Fastener Holes

of the Areas A and C at FR40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Areas A and C at FR40, RH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR40, LH Side

0.25

Do a Special Detailed Inspection of the Fastener Holes

of the Area B at FR40, RH Side

0.25

Do a rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Holes of the Areas A and C of the

Frame 40, LH Side

2.25

Do a rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Holes of the Areas A and C of the

Frame 40, RH Side

2.25

Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Holes of the Areas A and C of the

Frame 40, LH Side

2.25

Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Holes of the Areas A and C of the

Frame 40, RH Side

2.25

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, LH Side

1.00

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 19

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SERVICE BULLETIN

Task 574125-832-801-001: Inspection

Do a Rototest Inspection of the Holes of the Area B of

the Frame 40, RH Side

1.00

Tests 0.75

Close-Up 13.00

TOTAL MANHOURS 38.75

ELAPSED TIME (HOURS) 38.75

NOTE: For Areas A and C, if Service Bulletin No. A340-57-4090 is accomplished,

only the manhours stating post Service Bulletin No. A340-57-4090 apply.

For Areas A and C, if Service Bulletin No. A340-57-4090 is not accomplished,

only the manhours stating pre Service Bulletin No. A340-57-4090 apply.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 574125-833-801-001: Repair

Get Access 13.00

On Aircraft

Install new same Fasteners Pre Service Bulletin No.

A340-57-4090 of the Areas A and C in transition fit, LH

Side

1.75

Install new same Fasteners Pre Service Bulletin No.

A340-57-4090 of the Areas A and C in transition fit, RH

Side

1.75

Install new same Fasteners Post Service Bulletin No.

A340-57-4090 of the Areas A and C in transition fit, LH

Side

1.75

Install new same Fasteners Post Service Bulletin No.

A340-57-4090 of the Areas A and C in transition fit, RH

Side

1.75

Install new same Fasteners of the Area B in transition

fit, LH Side

1.00

Install new same Fasteners of the Area B in transition

fit, RH Side

1.00

Oversize the Holes to the First Oversize in comparison

with the current Hole diameter of the Areas A and C

Pre Service Bulletin No. A340-57-4090, LH Side

1.75

Oversize the Holes to the First Oversize in comparison

with the current Hole diameter of the Areas A and C

Pre Service Bulletin No. A340-57-4090, RH Side

1.75

Oversize the Holes to the First Oversize in comparison

with the current Hole diameter of the Areas A and C

Post Service Bulletin No. A340-57-4090, LH Side

1.75

Oversize the Holes to the First Oversize in comparison

with the current Hole diameter of the Areas A and C

Post Service Bulletin No. A340-57-4090, RH Side

1.75

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 20

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SERVICE BULLETIN

Task 574125-833-801-001: Repair

Oversize the Holes to the First Oversize in comparison

with the current Hole diameter of the Area B, LH Side

1.00

Oversize the Holes to the First Oversize in comparison

with the current Hole diameter of the Area B, RH Side

1.00

Install new Fasteners Pre Service Bulletin No.

A340-57-4090 of the Areas A and C in transition fit, LH

Side

1.75

Install new Fasteners Pre Service Bulletin No.

A340-57-4090 of the Areas A and C in transition fit, RH

Side

1.75

Install new Fasteners Post Service Bulletin No.

A340-57-4090 of the Areas A and C in transition fit, LH

Side

1.75

Install new Fasteners Post Service Bulletin No.

A340-57-4090 of the Areas A and C in transition fit, RH

Side

1.75

Install new Fasteners of the Area B in transition fit, LH

Side

1.00

Install new Fasteners of the Area B in transition fit, RH

Side

1.00

Tests 0.75

Close-Up 13.00

TOTAL MANHOURS 53.75

ELAPSED TIME (HOURS) 53.75

NOTE: For Areas A and C, if Service Bulletin No. A340-57-4090 is accomplished,

only the manhours stating post Service Bulletin No. A340-57-4090 apply.

For Areas A and C, if Service Bulletin No. A340-57-4090 is not accomplished,

only the manhours stating pre Service Bulletin No. A340-57-4090 apply.

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

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

20-21-11 21-20-00 21-52-41

25-52-00 25-80-00 36-22-19

52-30-00 53-35-13

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Standards Manual (SM)

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 21

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@A340

SERVICE BULLETIN

Structural Repair Manual (SRM) 51-11-00 51-22-00 51-24-00

51-40-00 51-42-00 51-43-00

51-44-00

K. PUBLICATION AFFECTED

Airworthiness Limitation Section (ALS) Airworthiness Limitation Section

(ALS) Part 2

Maintenance Planning Document (MPD) Impact on Scheduled Maintenance:

Refer to MPD

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 22

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

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:

Kit 574125A01R02 AIRBUS

Material Logistics and Suppliers

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 2590

For ordering by E-mail: airbus.kit@airbus.com

(2) Price and Availability

Kit 574125A01R02

Cost 20,950.00 USD

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 Kits 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. The latest valid price and lead time for ordering

purposes shall be obtained through the AirbusSpares portal or through a request for

quotation to airbus.kit@airbus.com.

B. INDUSTRY SUPPORT INFORMATION

This Service Bulletin is subject to a specific support provided by AIRBUS. For more details

regarding the applicable commercial policy, please contact your Customer Support Director.

C. LIST OF COMPONENTS

Kit 574125A01R02

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

NOTES

1 EN6115V5-12 1 SCREW

2 ASNA2529-5 7 NUT

3 EN6115T7-19 1 SCREW

4 ASNA2531-7 3 NUT

5 EN6115V4-10 4 SCREW

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 23

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@A340

SERVICE BULLETIN

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

NOTES

6 EN6115V5-14 2 SCREW

7 ASNA2529-4 4 NUT

10 EN6115V5X12 1 SCREW

11 EN6115T7X19 1 SCREW

12 EN6115V4X10 4 SCREW

13 EN6115V5X14 2 SCREW

14 EN6115T7-22 2 SCREW

15 EN6115T7X22 2 SCREW

16 EN6115V6-12 1 SCREW

17 ASNA2529-6 3 NUT

18 EN6115V5-10 4 SCREW

19 EN6115V6-14 2 SCREW

21 EN6115V6X12 1 SCREW

22 EN6115V5X10 4 SCREW

23 EN6115V6X14 2 SCREW

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.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency

(obsolete)

09-013 As required

Adhesion Promoter For Polysulfide

Sealant

09-028 As required

Polysulphide Fuel Tank Sealant 09-046 As required

Trichloroethane 11-004 As required

Lint-Free Cotton Cloth 19-003 As required

(2) Components

NOTE: To accomplish this Service Bulletin it is necessary to use the expendable

parts listed in the AMM Task 21-52-41-400-801 mentioned in paragraph

close-up.

(3) Equipment

None

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 24

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SERVICE BULLETIN

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

NOTE: To accomplish this Service Bulletin it is necessary to use the tools listed

in the AMM Task 21-52-41-000-801 mentioned in paragraph job set-up

and in the AMM Task 21-52-41-400-801 mentioned in paragraph closeup.

(3) Special Tools

None

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 25

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SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 26

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 574125-832-801-001 - Inspection

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.

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

INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED

MOVEMENT OF THE LANDING GEAR.

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

Zone

137 138

Manpower

TOTAL MANHOURS 38.75

ELAPSED TIME (HOURS) 38.75

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 27

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SERVICE BULLETIN

A. GENERAL

CAUTION: To accomplish this Service Bulletin it is not necessary to put the aircraft

under zero stress jacking. No zero stress jacking is required also in case of

concurrent accomplishment of maintenance tasks or SBs in frame 40 area.

However this is applicable only for the accomplishment of these tasks/SBs

without deviation. Indeed, in case of heavy repair, a temporary re-installation

of fasteners and/or zero stress jacking procedure could be anticipated.

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

NOTE: The purpose of flow charts are for information only to show the various

Inspection/Repair phases described in this Service Bulletin.

(1) Subtask 574125-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

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

(b) For the identification of Access Panels (Refer to AMM 06-41-53, Page Block 001).

(c) For the specification of the material numbers (Mat. No.) refer to Consumable

Material List (CML).

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

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(g) Remove and install the fasteners (Refer to SRM 51-42-00).

(2) Subtask 574125-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 28

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SERVICE BULLETIN

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

Service Bulletin.

B. PREPARATION

(1) Subtask 574125-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

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

12-34-24-860-802).

(b) Put the access platform(s) in position at door 821.

(2) Subtask 574125-941-002-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbotton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(3) Subtask 574125-941-003-001 - Remove/Open for Access in the Belly Fairing Areas

RH side

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 21-52-41-000-801

Task 36-22-19-000-801

Task 53-35-13-000-802

Fig. A-FBAAA

Remove/Install of the Heat Shield

Sheet 01

Sheet 02

Fig. A-FDBAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 29

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SERVICE BULLETIN

References

Fig. A-FDCAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

(a) Remove the Belly Fairing Access-Panels 193DB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FDBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FDCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) Remove, if necessary, the Wing Bleed-Air Duct Sensing Elements (Refer to AMM

Task 36-22-19-000-801).

(e) Remove the Heat Shield of the RH Conditioning Pack (Refer to Fig. A-FBAAA

Sheet 01 and Fig. A-FBAAA Sheet 02):

1 Heat Shield Item (8) Retain

12 Screw Item (9) Retain

(4) Subtask 574125-941-004-001 - Remove/Open for Access in the Belly Fairing Area

LH side

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 53-35-13-000-802

(a) Remove the Belly Fairing Access-Panels 192PB (Refer to AMM Task

53-35-13-000-802).

(5) Subtask 574125-941-005-001 - Remove/Open for Access in the FWD CargoCompartment

Manpower Resources

Skills NON SPECIFIC

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 30

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@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FDAAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (FWD

Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove, if necessary, the air conditioning ducts between

Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. AFDAAA Sheet 01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 574125-110-001-001 - Cleaning of the structure

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Trichloroethane 11-004 As required

Lint-Free Cotton Cloth 19-003 As required

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 31

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@A340

SERVICE BULLETIN

WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN

IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS.

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection area with:

Trichloroethane 11-004 As required

and (if necessary)

Lint-Free Cotton

Cloth

19-003 As required

(7) Subtask 574125-210-001-001 - Preparation of the inspection Areas

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00, Page Block 001

51-22-00, Page Block 001

(a) Use a FLASHLIGHT to do this inspection if necessary.

(b) Make sure that the surface of the inspection area is clean and smooth.

(c) Do a visual check of the inspection area for damages or discontinuities.

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 32

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SERVICE BULLETIN

(d) Make sure that there is no:

1 Corrosion damage:

- If you find corrosion damage, refer to the Structural Repair Manual

for Types, inspection, removal and corrosion protection (Refer to SRM

51-22-00, Page Block 001).

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...):

- If you find this type of damage, refer to the Structural Repair Manual for

damage classification and corrective action (Refer to SRM 51-11-00, Page

Block 001).

C. PROCEDURE

(1) Subtask 574125-832-001-001 - Do a Special Detailed Inspection of the Fastener

Holes of the Areas A and C at FR40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A340-57-4090

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA

(a) If Service Bulletin No.A340-57-4090 is accomplished:

1 Do SUBTASK 574125-832-007 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Holes of the Areas A and C of the Frame 40,

LH Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

(b) If Service Bulletin No. A340-57-4090 is not accomplished:

1 Do SUBTASK 574125-832-005 001 Do a rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Holes of the Areas A and C of the Frame 40,

LH Side at the threshold given in the table 3 of the Planning Information

Paragraph E.(2).

or

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 33

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@A340

SERVICE BULLETIN

Apply Service Bulletin No. A340-57-4090 before next flight

And do the SUBTASK 574125-832-007 001 Do a Rototest Inspection Post

Service Bulletin No. A340-57-4090 of the Holes of the Areas A and C of the

Frame 40, LH Side at the threshold given in the table 4 of the Planning

Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

(2) Subtask 574125-832-002-001 - Do a Special Detailed Inspection of the Fastener

Holes of the Areas A and C at FR40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Service Bulletin (SB) A340-57-4090

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA

(a) If Service Bulletin No.A340-57-4090 is accomplished:

1 Do SUBTASK 574125-832-008 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Holes of the Areas A and C of the Frame 40,

RH Side at the threshold given in the table 4 of the Planning Information

Paragraph E.(2).

(b) If Service Bulletin No. A340-57-4090 is not accomplished:

1 Do SUBTASK 574125-832-006 001 Do a rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Holes of the Areas A and C of the Frame 40,

RH Side at the threshold given in the table 3 of the Planning Information

Paragraph E.(2).

or

Apply Service Bulletin No. A340-57-4090 before next flight

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 34

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@A340

SERVICE BULLETIN

And do the SUBTASK 574125-832-008 001 Do a Rototest Inspection Post

Service Bulletin No. A340-57-4090 of the Holes of the Areas A and C of the

Frame 40, RH Side at the threshold given in the table 4 of the Planning

Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

(3) Subtask 574125-832-003-001 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA

(a) Do SUBTASK 574125-832-009 001 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, LH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(4) Subtask 574125-832-004-001 - Do a Special Detailed Inspection of the Fastener

Holes of the Area B at FR40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills AIRFRAME

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-FFAAA

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 35

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@A340

SERVICE BULLETIN

(a) Do SUBTASK 574125-832-010 001 Do a Rototest Inspection of the Holes of the

Area B of the Frame 40, RH Side at the threshold given in the table 5 of the

Planning Information Paragraph E.(2).

(5) Subtask 574125-832-005-001 - Do a rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Holes of the Areas A and C of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.25

Minimum number of person 1

Subtask elapsed time 2.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Fig. A-FCBAA

Inspection Area

Sheet 01

Sheet 02

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection pre Service Bulletin No. A340-57-4090 of the areas A and

C of the frame 40, LH side.

- In the area A, remove the fasteners from holes H41, H42, H44, and H46, LH

side:

Refer to Fig. A-FCAAA

4 Screw Item (5) Discard

4 Nut Item (7) Discard

- In the area A, remove the fasteners from holes H45 and H259, LH side:

Refer to Fig. A-FCAAA

2 Screw Item (6) Discard

2 Nut Item (2) Discard

- In the area C, remove the fastener from hole H25, LH side:

Refer to Fig. A-FCAAA

1 Screw Item (1) Discard

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 36

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@A340

SERVICE BULLETIN

1 Nut Item (2) Discard

- Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and

H259, LH side.

Refer to Fig. A-FCBAA

Refer to NTM 51-10-01

1 If no crack is found:

a Do SUBTASK 574125-833-001 001 Install new same Fasteners Pre

Service Bulletin No. A340-57-4090 of the Areas A and C in transition fit,

LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574125-832-005 001 Do a rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Holes of the Areas A and C of the Frame 40, LH

Side at the interval given in the table 3 of the Planning Information

Paragraph E.(2).

or

b Apply Service Bulletin No. A340-57-4090 before next flight

And do the SUBTASK 574125-832-007 001 Do a Rototest Inspection

Post Service Bulletin No. A340-57-4090 of the Holes of the Areas A and

C of the Frame 40, LH Side at the threshold given in the table 4 of the

Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

2 If crack is found:

a Do SUBTASK 574125-833-007 001 Oversize the Holes to the First

Oversize in comparison with the current Hole diameter of the Areas A

and C Pre Service Bulletin No. A340-57-4090, LH Side and check if

crack is found with a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Do SUBTASK 574125-833-013 001 Install new Fasteners Pre

Service Bulletin No. A340-57-4090 of the Areas A and C in

transition fit, LH Side before next flight

and

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 37

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@A340

SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

574125-832-005 001 Do a rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Holes of the Areas A and C

of the Frame 40, LH Side at the interval given in the table 3 of

the Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(6) Subtask 574125-832-006-001 - Do a rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Holes of the Areas A and C of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.25

Minimum number of person 1

Subtask elapsed time 2.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Fig. A-FCBAA

Inspection Area

Sheet 01

Sheet 02

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection pre Service Bulletin No. A340-57-4090 of the areas A and

C of the frame 40, RH side.

- In the area A, remove the fasteners from holes H41, H42, H44, and H46, RH

side:

Refer to Fig. A-FCAAA

4 Screw Item (5) Discard

4 Nut Item (7) Discard

- In the area A, remove the fasteners from holes H45 and H259, RH side:

Refer to Fig. A-FCAAA

2 Screw Item (6) Discard

2 Nut Item (2) Discard

- In the area C, remove the fastener from hole H25, RH side:

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 38

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@A340

SERVICE BULLETIN

Refer to Fig. A-FCAAA

1 Screw Item (1) Discard

1 Nut Item (2) Discard

- Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and

H259, RH side.

Refer to Fig. A-FCBAA

Refer to NTM 51-10-01

1 If no crack is found:

a Do SUBTASK 574125-833-002 001 Install new same Fasteners Pre

Service Bulletin No. A340-57-4090 of the Areas A and C in transition fit,

RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574125-832-006 001 Do a rototest Inspection Pre Service Bulletin No.

A340-57-4090 of the Holes of the Areas A and C of the Frame 40, RH

Side at the interval given in the table 3 of the Planning Information

Paragraph E.(2).

or

b Apply Service Bulletin No. A340-57-4090 before next flight

And do the SUBTASK 574125-832-008 001 Do a Rototest Inspection

Post Service Bulletin No. A340-57-4090 of the Holes of the Areas A and

C of the Frame 40, RH Side at the threshold given in the table 4 of the

Planning Information Paragraph E.(2).

NOTE: The threshold is to be counted from Service Bulletin No.

A340-57-4090 embodiment.

2 If crack is found:

a Do SUBTASK 574125-833-008 001 Oversize the Holes to the First

Oversize in comparison with the current Hole diameter of the Areas A

and C Pre Service Bulletin No. A340-57-4090, RH Side and check if

crack is found with a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 39

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@A340

SERVICE BULLETIN

<2> If no crack is found after the rototest inspection:

<a> Do SUBTASK 574125-833-014 001 Install new Fasteners Pre

Service Bulletin No. A340-57-4090 of the Areas A and C in

transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574125-832-006 001 Do a rototest Inspection Pre Service

Bulletin No. A340-57-4090 of the Holes of the Areas A and C

of the Frame 40, RH Side at the interval given in the table 3 of

the Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(7) Subtask 574125-832-007-001 - Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Holes of the Areas A and C of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 2.25

Minimum number of person 1

Subtask elapsed time 2.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Fig. A-FCBAA

Inspection Area

Sheet 01

Sheet 02

Fig. A-FCCAA

Remove/Install of the fasteners post

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection post Service Bulletin No. A340-57-4090 of the areas A and

C of the frame 40, LH side.

- In the area A, remove the fasteners from holes H41, H42, H44, and H46, LH

side:

Refer to Fig. A-FCCAA

4 Screw Item (18) Discard

4 Nut Item (2) Discard

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 40

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@A340

SERVICE BULLETIN

- In the area A, remove the fasteners from holes H45 and H259, LH side:

Refer to Fig. A-FCCAA

2 Screw Item (19) Discard

2 Nut Item (17) Discard

- In the area C, remove the fastener from hole H25, LH side:

Refer to Fig. A-FCCAA

1 Screw Item (16) Discard

1 Nut Item (17) Discard

- Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and

H259, LH side.

Refer to Fig. A-FCBAA

Refer to NTM 51-10-01

1 If no crack is found:

a Do SUBTASK 574125-833-003 001 Install new same Fasteners Post

Service Bulletin No. A340-57-4090 of the Areas A and C in transition fit,

LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574125-832-007 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Holes of the Areas A and C of the Frame 40, LH

Side at the interval given in the table 4 of the Planning Information

Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Do SUBTASK 574125-833-009 001 Oversize the Holes to the First

Oversize in comparison with the current Hole diameter of the Areas A

and C Post Service Bulletin No. A340-57-4090, LH Side and check if

crack is found with a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Do SUBTASK 574125-833-015 001 Install new Fasteners Post

Service Bulletin No. A340-57-4090 of the Areas A and C in

transition fit, LH Side before next flight

and

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 41

5

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

SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

574125-832-007 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Holes of the Areas A and C

of the Frame 40, LH Side at the interval given in the table 4 of

the Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

(8) Subtask 574125-832-008-001 - Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Holes of the Areas A and C of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 2.25

Minimum number of person 1

Subtask elapsed time 2.25

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Service Bulletin (SB) A340-57-4090

Fig. A-FCBAA

Inspection Area

Sheet 01

Sheet 02

Fig. A-FCCAA

Remove/Install of the fasteners post

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection post Service Bulletin No. A340-57-4090 of the areas A and

C of the frame 40, RH side.

- In the area A, remove the fasteners from holes H41, H42, H44, and H46, RH

side:

Refer to Fig. A-FCCAA

4 Screw Item (18) Discard

4 Nut Item (2) Discard

- In the area A, remove the fasteners from holes H45 and H259, RH side:

Refer to Fig. A-FCCAA

2 Screw Item (19) Discard

2 Nut Item (17) Discard

- In the area C, remove the fastener from hole H25, RH side:

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 42

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@A340

SERVICE BULLETIN

Refer to Fig. A-FCCAA

1 Screw Item (16) Discard

1 Nut Item (17) Discard

- Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and

H259, RH side.

Refer to Fig. A-FCBAA

Refer to NTM 51-10-01

1 If no crack is found:

a Do SUBTASK 574125-833-004 001 Install new same Fasteners Post

Service Bulletin No. A340-57-4090 of the Areas A and C in transition fit,

RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574125-832-008 001 Do a Rototest Inspection Post Service Bulletin No.

A340-57-4090 of the Holes of the Areas A and C of the Frame 40, RH

Side at the interval given in the table 4 of the Planning Information

Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Do SUBTASK 574125-833-010 001 Oversize the Holes to the First

Oversize in comparison with the current Hole diameter of the Areas A

and C Post Service Bulletin No. A340-57-4090, RH Side and check if

crack is found with a rototest inspection before next flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Do SUBTASK 574125-833-016 001 Install new Fasteners Post

Service Bulletin No. A340-57-4090 of the Areas A and C in

transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574125-832-008 001 Do a Rototest Inspection Post Service

Bulletin No. A340-57-4090 of the Holes of the Areas A and C

of the Frame 40, RH Side at the interval given in the table 4 of

the Planning Information Paragraph E.(2).

(b) For the inspection report, refer to Appendix 01.

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SERVICE BULLETIN

(9) Subtask 574125-832-009-001 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Fig. A-FCBAA

Inspection Area

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the area B of the frame 40, LH side.

- Remove the fasteners from holes H38 and H43, LH side.

Refer to Fig. A-FCAAA:

2 Screw Item (14) Discard

2 Nut Item (4) Discard

- Remove the fastener from hole H39, LH side.

Refer to Fig. A-FCAAA Sheet 02:

1 Screw Item (3) Discard

1 Nut Item (4) Discard

- Do a rototest inspection at the holes H38, H39 and H43, LH side.

Refer to Fig. A-FCBAA

Refer to NTM 51-10-01

1 If no crack is found:

a Do SUBTASK 574125-833-005 001 Install new same Fasteners of the

Area B in transition fit, LH Side before next flight

and

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SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

574125-832-009 001 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, LH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Do SUBTASK 574125-833-011 001 Oversize the Holes to the First

Oversize in comparison with the current Hole diameter of the Area B, LH

Side and check if crack is found with a rototest inspection before next

flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Do SUBTASK 574125-833-017 001 Install new Fasteners of

the Area B in transition fit, LH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574125-832-009 001 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, LH Side at the interval given in the

table 5 of the Planning Information Paragraph E.(2).

(10) Subtask 574125-832-010-001 - Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Fig. A-FCBAA

Inspection Area

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA

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SERVICE BULLETIN

At the threshold given in the Planning Information Paragraph E.(2):

(a) Do a rototest inspection of the area B of the frame 40, RH side.

- Remove the fasteners from holes H38 and H43, RH side.

Refer to Fig. A-FCAAA:

2 Screw Item (14) Discard

2 Nut Item (4) Discard

- Remove the fastener from hole H39, RH side.

Refer to Fig. A-FCAAA Sheet 02:

1 Screw Item (3) Discard

1 Nut Item (4) Discard

- Do a rototest inspection at the holes H38, H39 and H43, RH side.

Refer to Fig. A-FCBAA

Refer to NTM 51-10-01

1 If no crack is found:

a Do SUBTASK 574125-833-006 001 Install new same Fasteners of the

Area B in transition fit, RH Side before next flight

and

Repeat the rototest inspection as described in SUBTASK

574125-832-010 001 Do a Rototest Inspection of the Holes of the Area B

of the Frame 40, RH Side at the interval given in the table 5 of the

Planning Information Paragraph E.(2).

b For the inspection report, refer to Appendix 01.

2 If crack is found:

a Do SUBTASK 574125-833-012 001 Oversize the Holes to the First

Oversize in comparison with the current Hole diameter of the Area B, RH

Side and check if crack is found with a rototest inspection before next

flight.

<1> If crack is found after the rototest inspection:

<a> Contact Airbus before next flight.

<2> If no crack is found after the rototest inspection:

<a> Do SUBTASK 574125-833-018 001 Install new Fasteners of

the Area B in transition fit, RH Side before next flight

and

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SERVICE BULLETIN

Repeat the rototest inspection as described in SUBTASK

574125-832-010 001 Do a Rototest Inspection of the Holes of

the Area B of the Frame 40, RH Side at the interval given in

the table 5 of the Planning Information Paragraph E.(2).

D. TEST

(1) Subtask 574125-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

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

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation of

the parts removed for the access refer to SUBTASK 574125-942-001

001 Install/Close Items Removed/Opened for access in the Belly

Fairing Area RH side , SUBTASK 574125-942-002 001 Install/Close

Item Removed/Opened for access in the Belly Fairing Area LH

side , SUBTASK 574125-942-004 001 Close-up and SUBTASK

574125-942-003 001 Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

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(b) Procedure:

1 Do test procedure as specified after the Installation of the Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of the Installation of the Air

Conditioning Pack (Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

E. CLOSE-UP

(1) Subtask 574125-942-001-001 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area RH side

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesion Promoter For

Polysulfide Sealant

09-028 As required

Polysulphide Fuel Tank

Sealant

09-046 As required

References

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

Task 25-80-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

Consumable Material List (CML)

Fig. A-FBAAA

Remove/Install of the Heat Shield

Sheet 01

Sheet 02

Fig. A-FDCAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

Fig. A-FDBAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

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CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574125-700-001 001 Testing .

(a) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(b) Install the Heat Shield of the RH Conditioning Pack (Refer to Fig. A-FBAAA Sheet

01 and Fig. A-FBAAA Sheet 02):

1 Heat shield Item (8) Retained at

removal

12 Screw Item (9) Retained at

removal

- Install screws Item (9) with:

Adhesion Promoter

For Polysulfide

Sealant

09-028 As required

Polysulphide Fuel

Tank Sealant

09-046 As required

on and around the screws.

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FDCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FDBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the Wing Bleed-Air Duct Sensing Elements (Refer to AMM Task

36-22-19-400-801).

(f) Install the Belly Fairing Access-Panels 193DB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 574125-942-002-001 - Install/Close Item Removed/Opened for access in

the Belly Fairing Area LH side

Manpower Resources

Skills NON SPECIFIC

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SERVICE BULLETIN

References

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

NOTE: The parts removed for the access must be installed before the

SUBTASK 574125-700-001 001 Testing .

(a) Install the Belly Fairing Access-Panels 192PB (Refer to AMM Task

53-35-13-400-802).

(3) Subtask 574125-942-003-001 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FDAAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (FWD

Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574125-700-001 001 Testing .

(a) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FDAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(b) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(c) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801).

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(d) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(4) Subtask 574125-942-004-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

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

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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This Page Intentionally Left Blank

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SERVICE BULLETIN

Task 574125-833-801-001 - Repair

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.

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

INSTALLED ON THE LANDING GEAR.

THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR.

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

Zone

137 138

Manpower

TOTAL MANHOURS 53.75

ELAPSED TIME (HOURS) 53.75

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SERVICE BULLETIN

A. GENERAL

(1) Subtask 574125-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-41-53, Page Block 001

Task 20-21-11-911-801

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-42-00

51-43-00

51-44-00

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

(b) For the identification of Access Panels (Refer to AMM 06-41-53, Page Block 001).

(c) For the specification of the material numbers (Mat. No.) refer to Consumable

Material List (CML).

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

(e) In case alternative and substitute fasteners are to be used, you must check that the

associated nut/collar are compatible in accordance with SRM 51-40-00.

(f) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(g) Remove and install the fasteners (Refer to SRM 51-42-00).

(h) Drill and deburr the holes (Refer to SRM 51-44-00).

(i) Torque the standard threaded fasteners (Refer to AMM Task 20-21-11-911-801).

(j) Apply the sealant (Refer to SRM 51-24-00).

(k) For alternative and substitute fasteners (Refer to SRM 51-43-00).

(2) Subtask 574125-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

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SERVICE BULLETIN

B. PREPARATION

NOTE: This PREPARATION procedure is already done in the INSPECTION task.

(1) Subtask 574125-941-006-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

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

12-34-24-860-802).

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

(2) Subtask 574125-941-007-001 - Safety Precautions

Manpower Resources

Skills NON SPECIFIC

(a) On the AIR control panel 225VU:

1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)

pushbutton switches are released.

2 Put a WARNING NOTICE in position to tell persons not to operate these

pushbotton switches.

(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons

not to supply the ground air source.

(3) Subtask 574125-941-008-001 - Remove/Open for Access in the Belly Fairing Areas

RH side

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 21-52-41-000-801

Task 36-22-19-000-801

Task 53-35-13-000-802

Fig. A-FBAAA

Remove/Install of the Heat Shield

Sheet 01

Sheet 02

Fig. A-FDBAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

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References

Fig. A-FDCAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

(a) Remove the Belly Fairing Access-Panels 193DB (Refer to AMM Task

53-35-13-000-802).

(b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows

(Refer to AMM Task 21-20-00-010-801 and Fig. A-FDBAA Sheet 01).

1 Remove:

1 Duct Item (26) Retain

(c) On the RH side, remove and retain the air ventilation duct as follows (Refer to

AMM Task 21-20-00-010-801 and Fig. A-FDCAA Sheet 01).

1 Remove:

1 Duct Item (41) Retain

(d) Remove, if necessary, the Wing Bleed-Air Duct Sensing Elements (Refer to AMM

Task 36-22-19-000-801).

(e) Remove the Heat Shield of the RH Conditioning Pack (Refer to Fig. A-FBAAA

Sheet 01 and Fig. A-FBAAA Sheet 02):

1 Heat Shield Item (8) Retain

12 Screw Item (9) Retain

(4) Subtask 574125-941-009-001 - Remove/Open for Access in the Belly Fairing Area

LH side

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 53-35-13-000-802

(a) Remove the Belly Fairing Access-Panels 192PB (Refer to AMM Task

53-35-13-000-802).

(5) Subtask 574125-941-010-001 - Remove/Open for Access in the FWD CargoCompartment

Manpower Resources

Skills NON SPECIFIC

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801

Task 25-52-00-000-801

Task 25-80-00-000-801

Task 52-30-00-010-801

Fig. A-FDAAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (FWD

Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

(a) Open the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-010-801).

(b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM

Task 25-52-00-000-801).

(c) On the LH and RH sides, remove, if necessary, the air conditioning ducts between

Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. AFDAAA Sheet 01).

1 Remove:

2 Duct Item (11) Retain

2 Duct Item (12) Retain

2 Recirculation filterhousingItem (13) Retain

2 Recirculation fan Item (14) Retain

(d) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(6) Subtask 574125-110-002-001 - Cleaning of the structure

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Trichloroethane 11-004

Lint-Free Cotton Cloth 19-003 As required

References

Aircraft Maintenance Manual (AMM) Task 25-80-00-000-801

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WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER

SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH

THE WORK AREA.

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN

IRRITANTS.

OBEY THE MANUFACTURERS INSTRUCTIONS.

PUT ON PROTECTIVE CLOTHING.

DO NOT GET THEM IN YOUR MOUTH.

DO NOT SMOKE.

DO NOT BREATHE THE GAS.

GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE

THIS/THESE MATERIAL/S.

USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A

MASK.

(a) Clean the inspection area with:

Trichloroethane 11-004 As required

and (if necessary)

Lint-Free Cotton

Cloth

19-003 As required

(b) Remove the insulation blankets if necessary (Refer to AMM Task

25-80-00-000-801).

(7) Subtask 574125-210-002-001 - Preparation of the repair Areas

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-11-00, Page Block 001

51-22-00, Page Block 001

(a) Use a FLASHLIGHT to do this repair if necessary.

(b) Make sure that the surface of the repair area is clean and smooth.

(c) Do a visual check of the repair area for damages or discontinuities.

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(d) Make sure that there is no:

1 Corrosion damage:

- If you find corrosion damage, refer to the Structural Repair Manual

for Types, inspection, removal and corrosion protection (Refer to SRM

51-22-00, Page Block 001).

2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...):

- If you find this type of damage, refer to the Structural Repair Manual for

damage classification and corrective action (Refer to SRM 51-11-00, Page

Block 001).

C. PROCEDURE

(1) Subtask 574125-833-001-001 - Install new same Fasteners Pre Service Bulletin No.

A340-57-4090 of the Areas A and C in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

Material necessary to do the job

Kit 574125A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V5-12 1 SCREW

2 ASNA2529-5 3 NUT

5 EN6115V4-10 4 SCREW

6 EN6115V5-14 2 SCREW

7 ASNA2529-4 4 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 59

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@A340

SERVICE BULLETIN

References

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

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

In accordance with SRM 51-43-00

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

In accordance with SRM 51-42-00

(a) Depending on inspection results of the areas A and C, if no crack is found, install

the fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V4-10 Item 5

4 Nut ASNA2529-4 Item 7

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fasteners at holes H45 and H259:

2 Screw EN6115V5-14 Item 6

2 Nut ASNA2529-5 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 In the area C:

a Install the fastener at hole H25:

1 Screw EN6115V5-12 Item 1

1 Nut ASNA2529-5 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 60

5

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@A340

SERVICE BULLETIN

(2) Subtask 574125-833-002-001 - Install new same Fasteners Pre Service Bulletin No.

A340-57-4090 of the Areas A and C in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

Material necessary to do the job

Kit 574125A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V5-12 1 SCREW

2 ASNA2529-5 3 NUT

5 EN6115V4-10 4 SCREW

6 EN6115V5-14 2 SCREW

7 ASNA2529-4 4 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Remove/Install of the fasteners post

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

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

In accordance with SRM 51-43-00

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

In accordance with SRM 51-42-00

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 61

5

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@A340

SERVICE BULLETIN

(a) Depending on inspection results of the areas A and C, if no crack is found, install

the fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V4-10 Item 5

4 Nut ASNA2529-4 Item 7

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fasteners at holes H45 and H259:

2 Screw EN6115V5-14 Item 6

2 Nut ASNA2529-5 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 In the area C:

a Install the fastener at hole H25:

1 Screw EN6115V5-12 Item 1

1 Nut ASNA2529-5 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(3) Subtask 574125-833-003-001 - Install new same Fasteners Post Service Bulletin

No. A340-57-4090 of the Areas A and C in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 62

5

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@A340

SERVICE BULLETIN

Material necessary to do the job

Kit 574125A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2529-5 4 NUT

16 EN6115V6-12 1 SCREW

17 ASNA2529-6 3 NUT

18 EN6115V5-10 4 SCREW

19 EN6115V6-14 2 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Remove/Install of the fasteners post

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

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

In accordance with SRM 51-42-00

In accordance with SRM 51-43-00

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

(a) Depending on inspection results of the areas A and C, if no crack is found, install

the fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V5-10 Item 18

4 Nut ASNA2529-5 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fasteners at holes H45 and H259:

2 Screw EN6115V6-14 Item 19

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 63

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@A340

SERVICE BULLETIN

2 Nut ASNA2529-6 Item 17

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 In the area C:

a Install the fastener at hole H25:

1 Screw EN6115V6-12 Item 16

1 Nut ASNA2529-6 Item 17

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(4) Subtask 574125-833-004-001 - Install new same Fasteners Post Service Bulletin

No. A340-57-4090 of the Areas A and C in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

Material necessary to do the job

Kit 574125A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2529-5 4 NUT

16 EN6115V6-12 1 SCREW

17 ASNA2529-6 3 NUT

18 EN6115V5-10 4 SCREW

19 EN6115V6-14 2 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 64

5

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

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Remove/Install of the fasteners post

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

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

In accordance with SRM 51-42-00

In accordance with SRM 51-43-00

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

(a) Depending on inspection results of the areas A and C, if no crack is found, install

the fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V5-10 Item 18

4 Nut ASNA2529-5 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fasteners at holes H45 and H259:

2 Screw EN6115V6-14 Item 19

2 Nut ASNA2529-6 Item 17

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 In the area C:

a Install the fastener at hole H25:

1 Screw EN6115V6-12 Item 16

1 Nut ASNA2529-6 Item 17

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 65

5

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@A340

SERVICE BULLETIN

(5) Subtask 574125-833-005-001 - Install new same Fasteners of the Area B in

transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 574125A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6115T7-19 1 SCREW

4 ASNA2531-7 3 NUT

14 EN6115T7-22 2 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

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

In accordance with SRM 51-43-00

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

In accordance with SRM 51-42-00

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 66

5

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@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 In the area B:

a Install the fasteners at holes H38 and H43:

2 Screw EN6115T7-22 Item 14

2 Nut ASNA2531-7 Item 4

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fastener at hole H39:

1 Screw EN6115T7-19 Item 3

1 Nut ASNA2531-7 Item 4

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(6) Subtask 574125-833-006-001 - Install new same Fasteners of the Area B in

transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 574125A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6115T7-19 1 SCREW

4 ASNA2531-7 3 NUT

14 EN6115T7-22 2 SCREW

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 67

5

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@A340

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

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

In accordance with SRM 51-43-00

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

In accordance with SRM 51-42-00

(a) Depending on inspection results of the area B, if no crack is found, install the

fasteners.

1 In the area B:

a Install the fasteners at holes H38 and H43:

2 Screw EN6115T7-22 Item 14

2 Nut ASNA2531-7 Item 4

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fastener at hole H39:

1 Screw EN6115T7-19 Item 3

1 Nut ASNA2531-7 Item 4

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 68

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SERVICE BULLETIN

(7) Subtask 574125-833-007-001 - Oversize the Holes to the First Oversize in

comparison with the current Hole diameter of the Areas A and C Pre Service

Bulletin No. A340-57-4090, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the Areas A and C, if crack is found, oversize

the holes.

1 In the area A:

a Drill to the first oversize diameter the holes H41, H42, H44, H45, H46

and H259 to the dimension given in Fig. A-FCAAA Sheet 02.

b Do a rototest inspection, refer to NTM 51-10-01, on the drilled holes to

check if the crack is still present.

2 In the area C:

a Drill to the first oversize diameter the hole H25 to the dimension given in

Fig. A-FCAAA Sheet 02.

b Do a rototest inspection, refer to NTM 51-10-01, on the drilled hole to

check if the crack is still present.

(8) Subtask 574125-833-008-001 - Oversize the Holes to the First Oversize in

comparison with the current Hole diameter of the Areas A and C Pre Service

Bulletin No. A340-57-4090, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 69

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas A and C, if crack is found, oversize

the holes.

1 In the area A:

a Drill to the first oversize diameter the holes H41, H42, H44, H45, H46

and H259 to the dimension given in Fig. A-FCAAA Sheet 02.

b Do a rototest inspection, refer to NTM 51-10-01, on the drilled holes to

check if the crack is still present.

2 In the area C:

a Drill to the first oversize diameter the hole H25 to the dimension given in

Fig. A-FCAAA Sheet 02.

b Do a rototest inspection, refer to NTM 51-10-01, on the drilled hole to

check if the crack is still present.

(9) Subtask 574125-833-009-001 - Oversize the Holes to the First Oversize in

comparison with the current Hole diameter of the Areas A and C Post Service

Bulletin No. A340-57-4090, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 70

5

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@A340

SERVICE BULLETIN

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Remove/Install of the fasteners post

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Refer to Fig. A-FCCAA Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas A and C, if crack is found, oversize

the holes.

1 In the area A:

a Drill to the first oversize diameter the holes H41, H42, H44, H45, H46

and H259 to the dimension given in Fig. A-FCCAA Sheet 02.

b Do a rototest inspection, refer to NTM 51-10-01, on the drilled holes to

check if the crack is still present.

2 In the area C:

a Drill to the first oversize diameter the hole H25 to the dimension given in

Fig. A-FCCAA Sheet 02.

b Do a rototest inspection, refer to NTM 51-10-01, on the drilled hole to

check if the crack is still present.

(10) Subtask 574125-833-010-001 - Oversize the Holes to the First Oversize in

comparison with the current Hole diameter of the Areas A and C Post Service

Bulletin No. A340-57-4090, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCCAA

Remove/Install of the fasteners post

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 71

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@A340

SERVICE BULLETIN

Refer to Fig. A-FCCAA Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the areas A and C, if crack is found, oversize

the holes.

1 In the area A:

a Drill to the first oversize diameter the holes H41, H42, H44, H45, H46

and H259 to the dimension given in Fig. A-FCCAA Sheet 02.

b Do a rototest inspection, refer to NTM 51-10-01, on the drilled holes to

check if the crack is still present.

2 In the area C:

a Drill to the first oversize diameter the hole H25 to the dimension given in

Fig. A-FCCAA Sheet 02.

b Do a rototest inspection, refer to NTM 51-10-01, on the drilled hole to

check if the crack is still present.

(11) Subtask 574125-833-011-001 - Oversize the Holes to the First Oversize in

comparison with the current Hole diameter of the Area B, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02

In accordance with SRM 51-44-00

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 72

5

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@A340

SERVICE BULLETIN

(a) Depending on inspection results of the area B, if crack is found, oversize the holes.

1 In the area B:

a Drill to the first oversize diameter the holes H38, H39 and H43 to the

dimension given in Fig. A-FCAAA Sheet 02.

b Do a rototest inspection, refer to NTM 51-10-01, on the drilled holes to

check if the crack is still present.

(12) Subtask 574125-833-012-001 - Oversize the Holes to the First Oversize in

comparison with the current Hole diameter of the Area B, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Non Destructive Test Manual (NTM) 51-10-01

Structural Repair Manual (SRM) 51-44-00

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02

In accordance with SRM 51-44-00

(a) Depending on inspection results of the area B, if crack is found, oversize the holes.

1 In the area B:

a Drill to the first oversize diameter the holes H38, H39 and H43 to the

dimension given in Fig. A-FCAAA Sheet 02.

b Do a rototest inspection, refer to NTM 51-10-01, on the drilled holes to

check if the crack is still present.

(13) Subtask 574125-833-013-001 - Install new Fasteners Pre Service Bulletin No.

A340-57-4090 of the Areas A and C in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 73

5

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

Material necessary to do the job

Kit 574125A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2529-5 3 NUT

7 ASNA2529-4 4 NUT

10 EN6115V5X12 1 SCREW

12 EN6115V4X10 4 SCREW

13 EN6115V5X14 2 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02

In accordance with SRM 51-43-00

In accordance with SRM 51-42-00

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

(a) Depending on inspection results of the areas A and C, if no crack is found, install

the new fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V4X10 Item 12

4 Nut ASNA2529-4 Item 7

Wet install the fasteners with:

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 74

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@A340

SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

b Install the fasteners at holes H45 and H259:

2 Screw EN6115V5X14 Item 13

2 Nut ASNA2529-5 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 In the area C:

a Install the fastener at hole H25:

1 Screw EN6115V5X12 Item 10

1 Nut ASNA2529-5 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(14) Subtask 574125-833-014-001 - Install new Fasteners Pre Service Bulletin No.

A340-57-4090 of the Areas A and C in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

Material necessary to do the job

Kit 574125A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2529-5 3 NUT

7 ASNA2529-4 4 NUT

10 EN6115V5X12 1 SCREW

12 EN6115V4X10 4 SCREW

13 EN6115V5X14 2 SCREW

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 75

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SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02

In accordance with SRM 51-43-00

In accordance with SRM 51-42-00

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

(a) Depending on inspection results of the areas A and C, if no crack is found, install

the new fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V4X10 Item 12

4 Nut ASNA2529-4 Item 7

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fasteners at holes H45 and H259:

2 Screw EN6115V5X14 Item 13

2 Nut ASNA2529-5 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 In the area C:

a Install the fastener at hole H25:

1 Screw EN6115V5X12 Item 10

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 76

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SERVICE BULLETIN

1 Nut ASNA2529-5 Item 2

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(15) Subtask 574125-833-015-001 - Install new Fasteners Post Service Bulletin No.

A340-57-4090 of the Areas A and C in transition fit, LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

Material necessary to do the job

Kit 574125A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2529-5 4 NUT

17 ASNA2529-6 3 NUT

21 EN6115V6X12 1 SCREW

22 EN6115V5X10 4 SCREW

23 EN6115V6X14 2 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Remove/Install of the fasteners post

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Refer to Fig. A-FCCAA Sheet 02

In accordance with SRM 51-43-00

In accordance with SRM 51-42-00

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 77

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SERVICE BULLETIN

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

(a) Depending on inspection of results of the areas A and C, if no crack is found, install

the new fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V5X10 Item 22

4 Nut ASNA2529-5 Item 2

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fasteners at holes H45 and H259:

2 Screw EN6115V6X14 Item 23

2 Nut ASNA2529-6 Item 17

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 In the area C:

a Install the fastener at hole H25:

1 Screw EN6115V6X12 Item 21

1 Nut ASNA2529-6 Item 17

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(16) Subtask 574125-833-016-001 - Install new Fasteners Post Service Bulletin No.

A340-57-4090 of the Areas A and C in transition fit, RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 78

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SERVICE BULLETIN

Manpower Resources

Manhours 1.75

Minimum number of person 1

Subtask elapsed time 1.75

Skills AIRFRAME

Material necessary to do the job

Kit 574125A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2529-5 4 NUT

17 ASNA2529-6 3 NUT

21 EN6115V6X12 1 SCREW

22 EN6115V5X10 4 SCREW

23 EN6115V6X14 2 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCCAA

Remove/Install of the fasteners post

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Refer to Fig. A-FCCAA Sheet 02

In accordance with SRM 51-43-00

In accordance with SRM 51-42-00

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

(a) Depending on inspection of results of the areas A and C, if no crack is found, install

the new fasteners.

1 In the area A:

a Install the fasteners at holes H41, H42, H44 and H46:

4 Screw EN6115V5X10 Item 22

4 Nut ASNA2529-5 Item 2

Wet install the fasteners with:

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 79

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SERVICE BULLETIN

Sealant-Brush

Consistency

09-013 As required

b Install the fasteners at holes H45 and H259:

2 Screw EN6115V6X14 Item 23

2 Nut ASNA2529-6 Item 17

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

2 In the area C:

a Install the fastener at hole H25:

1 Screw EN6115V6X12 Item 21

1 Nut ASNA2529-6 Item 17

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

(17) Subtask 574125-833-017-001 - Install new Fasteners of the Area B in transition fit,

LH Side

Work Zones and Access Panels

Zone Access/Work location

137 Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 574125A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 ASNA2531-7 3 NUT

11 EN6115T7X19 1 SCREW

15 EN6115T7X22 2 SCREW

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 80

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SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02

In accordance with SRM 51-43-00

In accordance with SRM 51-42-00

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

(a) Depending on inspection results of the area B, if no crack is found, install the new

fasteners.

1 In the area B:

a Install the fasteners at holes H38 and H43:

2 Screw EN6115T7X22 Item 15

2 Nut ASNA2531-7 Item 4

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fastener at hole H39:

1 Screw EN6115T7X19 Item 11

1 Nut ASNA2531-7 Item 4

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 81

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SERVICE BULLETIN

(18) Subtask 574125-833-018-001 - Install new Fasteners of the Area B in transition fit,

RH Side

Work Zones and Access Panels

Zone Access/Work location

138 Work location Frame 40

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 574125A01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 ASNA2531-7 3 NUT

11 EN6115T7X19 1 SCREW

15 EN6115T7X22 2 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

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

Structural Repair Manual (SRM) 51-42-00

51-43-00

Fig. A-FCAAA

Remove/Install of the fasteners pre

Service Bulletin No. A340-57-4090

Sheet 01

Sheet 02

Refer to Fig. A-FCAAA Sheet 02

In accordance with SRM 51-43-00

In accordance with SRM 51-42-00

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

(a) Depending on inspection results of the area B, if no crack is found, install the new

fasteners.

1 In the area B:

a Install the fasteners at holes H38 and H43:

2 Screw EN6115T7X22 Item 15

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 82

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SERVICE BULLETIN

2 Nut ASNA2531-7 Item 4

Wet install the fasteners with:

Sealant-Brush

Consistency

09-013 As required

b Install the fastener at hole H39:

1 Screw EN6115T7X19 Item 11

1 Nut ASNA2531-7 Item 4

Wet install the fastener with:

Sealant-Brush

Consistency

09-013 As required

D. TEST

(1) Subtask 574125-700-002-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

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

Task 21-52-41-400-801

Task 25-52-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

NOTE: This test procedure is to be accomplished after the installation of

the parts removed for the access refer to SUBTASK 574125-942-005

001 Install/Close Items Removed/Opened for access in the Belly

Fairing Area RH side , SUBTASK 574125-942-006 001 Install/Close

Item Removed/Opened for access in the Belly Fairing Area LH

side , SUBTASK 574125-942-008 001 Close-up and SUBTASK

574125-942-007 001 Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment .

(a) Job Set-up:

1 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task

53-35-13-400-802).

2 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to

AMM Task 36-22-19-400-801).

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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SERVICE BULLETIN

3 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air Conditioning Pack (Refer to AMM Task

21-52-41-400-801).

4 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Ceiling Panels, the Partition Panels and the

Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task

25-52-00-400-801).

5 Remove the Safety clips and tags and close the circuit breakers as specified

after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM

Task 21-20-00-410-801).

(b) Procedure:

1 Do test procedure as specified after the Installation of the Wing Bleed-air Duct

Sensing Elements (Refer to AMM Task 36-22-19-400-801).

2 Do test procedure as specified after the Installation of the Installation of the Air

Conditioning Pack (Refer to AMM Task 21-52-41-400-801).

3 Do test procedure as specified after the Installation of the Air-Conditioning

Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

E. CLOSE-UP

(1) Subtask 574125-942-005-001 - Install/Close Items Removed/Opened for access in

the Belly Fairing Area RH side

Manpower Resources

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Adhesion Promoter For

Polysulfide Sealant

09-028 As required

Polysulphide Fuel Tank

Sealant

09-046 As required

References

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

Task 21-52-41-400-801

Task 25-80-00-400-801

Task 36-22-19-400-801

Task 53-35-13-400-802

Structural Repair Manual (SRM) 51-24-00

Fig. A-FBAAA

Remove/Install of the Heat Shield

Sheet 01

Sheet 02

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 84

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SERVICE BULLETIN

References

Fig. A-FDCAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

Fig. A-FDBAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (Belly

Fairing Area)

Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR

CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A

GROUND SOURCE.

HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574125-700-002 001 Testing .

(a) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

(b) Install the Heat Shield of the RH Conditioning Pack refer to Fig. A-FBAAA Sheet 01

and Fig. A-FBAAA Sheet 02:

1 Heat shield Item (8) Retained at

removal

12 Screw Item (9) Retained at

removal

- Install screws Item (9) with:

Adhesion Promoter

For Polysulfide

Sealant

09-028 As required

Apply the sealant, refer to SRM 51-24-00.

Polysulphide Fuel

Tank Sealant

09-046 As required

on and around the screws.

(c) On the RH side, install the air ventilation duct (Refer to AMM Task

21-20-00-410-801 and Fig. A-FDCAA Sheet 01).

1 Install:

1 Duct Item (41) Retained at

removal

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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SERVICE BULLETIN

(d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to

AMM Task 21-20-00-410-801 and Fig. A-FDBAA Sheet 01).

1 Install:

1 Duct Item (26) Retained at

removal

(e) Install the Wing Bleed-Air Duct Sensing Elements (Refer to AMM Task

36-22-19-400-801).

(f) Install the Belly Fairing Access-Panels 193DB (Refer to AMM Task

53-35-13-400-802).

(2) Subtask 574125-942-006-001 - Install/Close Item Removed/Opened for access in

the Belly Fairing Area LH side

Manpower Resources

Skills NON SPECIFIC

References

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

NOTE: The parts removed for the access must be installed before the

SUBTASK 574125-700-002 001 Testing .

(a) Install the Belly Fairing Access-Panels 192PB (Refer to AMM Task

53-35-13-400-802).

(3) Subtask 574125-942-007-001 - Install/Close Items Removed/Opened for Access in

the FWD Cargo-Compartment

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-52-00-400-801

Task 25-80-00-400-801

Task 52-30-00-410-801

Fig. A-FDAAA

Remove/Install the Air Conditioning

Ducts between FR39.1 and FR40 (FWD

Cargo-Compartment)

Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.

NOTE: The parts removed for the access must be installed before the

SUBTASK 574125-700-002 001 Testing .

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 86

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SERVICE BULLETIN

(a) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and

Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FDAAA Sheet 01).

1 Install:

2 Duct Item (11) Retained at

removal

2 Duct Item (12) Retained at

removal

2 Recirculation filterhousingItem (13) Retained at

removal

2 Recirculation fan Item (14) Retained at

removal

(b) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task

25-52-00-400-801).

(c) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801).

(d) Close the FWD cargo-compartment door 821 (Refer to AMM Task

52-30-00-410-801).

(4) Subtask 574125-942-008-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

(a) Remove all the fixtures, tools, test and support equipment used during this

procedure.

(b) Remove the access platform(s).

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

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

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SERVICE BULLETIN

**CONF ALL

FR47

FR40

A

C

(8)

FR40.3

FR41

FR40.2

B

Z192 Z196 − 

B

A

(12 POS) (9)

F_SB_574125_5_BAAA_01_02

Figure A-FBAAA - Sheet 01

Remove/Install of the Heat Shield

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 88

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SERVICE BULLETIN

**CONF ALL

NOTES:

01 INSTALL SCREW ITEM (9) WITH MAT. No. 09−046 (WET ASSEMBLY).

APPLY A TORQUE VALUE OF 1.65 N.m ± 0.15 (14.60 lbf.in).

02 APPLY MAT. No. 09−028 and 09−046 ON AND AROUND THE SCREW.

FWD C

FR41

A

A

A A

(9)

01

02

RECEPTACLE

HEAT SHIELD

(8)

TYPICAL SECTION

F_SB_574125_5_BAAA_02_02

Figure A-FBAAA - Sheet 02

Remove/Install of the Heat Shield

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 89

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SERVICE BULLETIN

**CONF ALL

FR40

RH SIDE SHOWN

LH SIDE SYMMETRICAL

VIEW LOOKING AFT

FR47

FR40

B

B A

B

H25

H39

H41

H42

H44

H46

H259

H45

H43

H38

A Z141 Z142 − 

C

NOTE:

AREA HOLE NUMBER

A 41, 42, 44, 45, 46, 259

B 38, 39, 43

C 25 F_SB_574125_5_CAAA_01_02

Figure A-FCAAA - Sheet 01

Remove/Install of the fasteners pre Service Bulletin No. A340-57-4090

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 90

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@A340

SERVICE BULLETIN

**CONF ALL

FR40

C

RH SIDE SHOWN

LH SIDE SYMMETRICAL

HOLE

SYMBOL ITEM DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

EN6115V4−10 SCREW

ASNA2529−4 NUT

EN6115V4X10 SCREW

NUT

NOTE:

02 INSTALL THE FASTENERS WITH MAT. No 09−013 (WET ASSEMBLY)

01 DEPENDING ON INSPECTION RESULT

N

ASNA2529−4

5

7

12

7

N

HEAD ON THE VISIBLE SIDE

EXISTING HOLE DIAMETER

MIN MAX

6.227 mm

(0.245 in)

6.262 mm

(0.246 in)

11.476 mm

(0.452 in)

11.515 mm

(0.453 in)

10.972 mm

(0.432 in)

11.007 mm

(0.433 in)

6.310 mm

(0.248 in)

6.350 mm

(0.250 in)

EN6115V5−14 SCREW

ASNA2529−5 NUT

EN6115V5X14 SCREW

NUT

F

ASNA2529−5

6

2

13

2

7.815 mm

(0.308 in)

7.849 mm

(0.309 in)

EN6115T7−19 SCREW

ASNA2531−7 NUT

EN6115T7X19 SCREW

NUT

F

ASNA2531−7

3

4

11

4

8.296 mm

(0.327 in)

8.835 mm

(0.328 in)

EN6115V5−12 SCREW

ASNA2529−5 NUT

EN6115V5X12 SCREW

NUT

N

ASNA2529−5

1

2

10

2

7.815 mm

(0.308 in)

7.849 mm

(0.309 in)

11.080 mm

(0.436 in)

11.120 mm

(0.438 in)

F

HEAD ON THE HIDDEN SIDE

8.296 mm

(0.327 in)

8.335 mm

(0.328 in)

EN6115T7−22 SCREW

ASNA2531−7 NUT

EN6115T7X22 SCREW

NUT

F

ASNA2531−7

14

4

15

4

11.476 mm

(0.452 in)

11.515 mm

(0.453 in)

10.972 mm

(0.432 in)

11.007 mm

(0.433 in)

7.900 mm

(0.311 in)

7.940 mm

(0.312 in)

VIEW LOOKING AFT

(5)

(7)

(5)

(7)

(6)

(2)

(6)

(2)

(3)

(4)

(3)

(4)

(1)

(2)

(1)

(2)

(14)

(4)

(14)

(4)

01

01

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FASTENER

PN

FIRST OVERSIZE

01

01

02

02

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FASTENER

FIRST OVERSIZE

01

01

02

02

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FASTENER

FIRST OVERSIZE

01

01

02

02

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FASTENER

FIRST OVERSIZE

01

01

02

02

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FASTENER

FIRST OVERSIZE

7.900 mm

(0.311 in)

7.940 mm

(0.312 in)

11.080 mm

(0.436 in)

11.120 mm

(0.438 in)

STGR38

STGR39

STGR40

H25

H39

H44

H41 H42

H45 H46

H259

H43

H38

CENTER WING BOX LOWER PANEL REFERENCE

F_SB_574125_5_CAAA_02_03

Figure A-FCAAA - Sheet 02

Remove/Install of the fasteners pre Service Bulletin No. A340-57-4090

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 91

5

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@A340

SERVICE BULLETIN

**CONF ALL

FR47

FR40

B

B

A

A Z141 Z142 − 

F_SB_574125_5_CBAA_01_00

Figure A-FCBAA - Sheet 01

Inspection Area

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 92

5

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@A340

SERVICE BULLETIN

**CONF ALL

FR40

RH SIDE SHOWN

LH SIDE SYMMETRICAL

H25

H39

H41 H42

H44

H46

H259

H45

B

H43

H38

VIEW LOOKING AFT

NOTE:

AREA HOLE NUMBER

A 41, 42, 44, 45, 46, 259

B 38, 39, 43

C 25

F_SB_574125_5_CBAA_02_01

Figure A-FCBAA - Sheet 02

Inspection Area

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 93

5

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@A340

SERVICE BULLETIN

**CONF ALL

FR40

RH SIDE SHOWN

LH SIDE SYMMETRICAL

VIEW LOOKING AFT

FR47

FR40

B

B A

B

H25 H41

H42

H44

H46

H259

H45

A Z141 Z142 − 

C

NOTE:

AREA HOLE NUMBER

A 41, 42, 44, 45, 46, 259

C 25

F_SB_574125_5_CCAA_01_02

Figure A-FCCAA - Sheet 01

Remove/Install of the fasteners post Service Bulletin No. A340-57-4090

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 94

5

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

SERVICE BULLETIN

**CONF ALL

C

HOLE

SYMBOL PN DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

EN6115V5−10 SCREW

ASNA2529−5 NUT

EN6115V5X10 SCREW

NUT

N

ASNA2529−5

18

2

22

2

EXISTING HOLE DIAMETER

MIN MAX

EN6115V6−14 SCREW

ASNA2529−6 NUT

EN6115V6X14 SCREW

NUT

F

ASNA2529−6

19

17

23

17

9.387 mm

(0.370 in)

9.427 mm

(0.371 in)

EN6115V6−12 SCREW

ASNA2529−6 NUT

EN6115V6X12 SCREW

NUT

N

ASNA2529−6

16

17

21

17

9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

7.815 mm

(0.308 in)

7.849 mm

(0.309 in) 8.296 mm

(0.327 in)

8.335 mm

(0.328 in)

7.900 mm

(0.311 in)

7.940 mm

(0.312 in)

9.490 mm

(0.373 in)

9.530 mm

(0.375 in)

9.387 mm

(0.370 in)

9.427 mm

(0.371 in) 9.886 mm

(0.389 in)

9.925 mm

(0.390 in)

NOTE:

02 INSTALL THE FASTENERS WITH MAT. No 09−013 (WET ASSEMBLY)

01 DEPENDING ON INSPECTION RESULT

N

HEAD ON THE VISIBLE SIDE

F

HEAD ON THE HIDDEN SIDE

FR40

RH SIDE SHOWN

LH SIDE SYMMETRICAL

VIEW LOOKING AFT

(18)

(2)

(18)

(2)

(19)

(17)

(19)

(17)

(16)

(17)

(21)

(17)

ITEM

01

01

02

02

REMARKS

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FASTENER

FIRST OVERSIZE

01

01

02

02

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FASTENER

FIRST OVERSIZE

01

01

02

02

STANDARD FASTENER

IN TRANSITION FIT

IN TRANSITION FIT

FASTENER

FIRST OVERSIZE

9.490 mm

(0.373 in)

9.530 mm

(0.375 in)

STGR38

STGR39

STGR40

H25

H44

H41 H42

H45 H46

H259

CENTER WING BOX LOWER PANEL REFERENCE

F_SB_574125_5_CCAA_02_03

Figure A-FCCAA - Sheet 02

Remove/Install of the fasteners post Service Bulletin No. A340-57-4090

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 95

5

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@A340

SERVICE BULLETIN

**CONF ALL

Z130

FR39.1

FR40

B

B

A

A

RH SIDE SHOWN

LH SIDE SYMMETRICAL

(11) (12)

(14)

(13)

B

F_SB_574125_5_DAAA_01_00

Figure A-FDAAA - Sheet 01

Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment)

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 96

5

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@A340

SERVICE BULLETIN

**CONF ALL

B

FR39.2

FR40.2

A

B

(26)

A Z192

F_SB_574125_5_DBAA_01_00

Figure A-FDBAA - Sheet 01

Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area)

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 97

5

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@A340

SERVICE BULLETIN

**CONF ALL

FR39.2

FR40.2

B

(41)

A

B

A Z192

F_SB_574125_5_DCAA_01_00

Figure A-FDCAA - Sheet 01

Remove/Install the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area)

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 98

5

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@A340

SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

AT THE THRESHOLD GIVEN IN THE TABLES 1 AND 2

OF THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 574125−832−001 AND 574125−832−003) AND

RH SIDE (REFER TO SUBTASK 574125−832−002 AND 574125−832−004)

CRACKS YES NO

INSTALL NEW SAME FASTENER OF THE

(REFER TO SUBTASK 574125−832−009) AND

DO A ROTOTEST INSPECTION OF THE FASTENER

HOLES OF THE AREA B OF THE FRAME 40, LH AND RH SIDES

FOUND

(REFER TO SUBTASK 574125−832−009)

OF THE FASTENER HOLES OF THE

AREA B OF THE FRAME 40,

SEE FIG. A−FFAAA

SHEET 03

SEE FIG. A−FFAAA

SHEET 03

AREA B IN TRANSITION FIT, LH AND

(REFER TO SUBTASK 574125−833−005) AND

DO A SPECIAL DETAILED INSPECTION OF THE FASTENER HOLES

OF THE AREAS A, B AND C OF THE FRAME 40, LH SIDE

REPEAT THE ROTOTEST INSPECTION

SEE FIG. A−FFAAA

SHEET 02

LH AND RH SIDES

(REFER TO SUBTASK 574125−833−006)

RH SIDES, BEFORE NEXT FLIGHT

AND

AT THE INTERVAL GIVEN IN THE

INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 574125−832−010)

(REFER TO SUBTASK 574125−832−010)

AT THE THRESHOLD GIVEN IN THE TABLE 5 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

AREA B AREA A AND C

HOLES 38, 39 AND 43 HOLES 25, 41, 42,

44, 45, 46 AND 259

TABLE 5 OF THE PLANNING

F_SB_574125_5_FAAA_01_03

Figure A-FFAAA - Sheet 01

Flow Chart

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 99

5

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@A340

SERVICE BULLETIN

**CONF ALL

NOTE:

01 THRESHOLD TO BE COUNTED FROM MSB 57−4090 EMBODIMENT

QUESTION

ACTION

FINDING

CRACKS

OR

(REFER TO SUBTASK 574125−832−005) AND

SB No A340−57−4090 OF THE FASTENER HOLES OF

THE AREAS A AND C OF THE FRAME 40, LH AND RH SIDES

FOUND

A340−57−4090 NO YES ACCOMPLISHED

SEE FIG. A−FFAAA

SHEET 01

SB No

CRACKS YES NO

(REFER TO SUBTASK 574125−832−007) AND

FOUND

SEE FIG. A−FFAAA

SHEET 03

SEE FIG. A−FFAAA SHEET 03

OR

(REFER TO SUBTASK 574125−832−005) AND

SB No A340−57−4090 OF THE FASTENER HOLES OF

THE AREAS A AND C OF THE FRAME 40, LH AND RH SIDES

APPLY SB No A340−57−4090

YES NO

SEE FIG. A−FFAAA

SHEET 03

(SB No A340−57−4090

ACCOMPLISHED)

SEE FIG. A−FFAAA SHEET 03

(SB No A340−57−4090

NOT ACCOMPLISHED)

INSTALL NEW SAME FASTENERS PRE SB No A340−57−4090

OF THE AREAS A AND C IN TRANSITION FIT, LH AND RH SIDES,

THE AREAS A AND C OF THE FRAME 40, LH AND RH SIDES

DO A ROTOTEST INSPECTION PRE SB No A340−57−4090 OF THE FASTENER HOLES OF

DO A ROTOTEST INSPECTION POST

REPEAT THE ROTOTEST INSPECTION PRE (REFER TO SUBTASK 574125−832−007) AND

SB No A340−57−4090 OF THE FASTENER HOLES OF

THE AREAS A AND C OF THE FRAME 40, LH AND RH SIDES

INSTALL NEW SAME FASTENERS POST SB No A340−57−4090

(REFER TO SUBTASK 574125−833−003) AND

REPEAT THE ROTOTEST INSPECTION POST

01

BEFORE NEXT FLIGHT

(REFER TO SUBTASK 574125−832−006)

AT THE THRESHOLD GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 574125−832−008)

AT THE THRESHOLD GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 574125−832−006)

AT THE INTERVAL GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 574125−833−004)

(REFER TO SUBTASK 574125−832−008)

AT THE INTERVAL GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

BEFORE NEXT FLIGHT

(REFER TO SUBTASK 574125−833−001) AND

(REFER TO SUBTASK 574125−833−002)

OF THE AREAS A AND C IN TRANSITION FIT, LH AND RH SIDES,

BEFORE NEXT FLIGHT

F_SB_574125_5_FAAA_02_03

Figure A-FFAAA - Sheet 02

Flow Chart

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 100

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

SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

CRACKS YES NO FOUND

NO YES

SEE FIG. A−FFAAA

SHEET 01 AND SHEET 02

INSTALL NEW FASTENER PRE OR POST

(REFER TO SUBTASK 574125−833−007 AND 574125−833−008) OR

SEE FIG. A−FFAAA SHEET 02

(SB No A340−57−4090

NOT ACCOMPLISHED)

SEE FIG. A−FFAAA SHEET 02

(SB No A340−57−4090

ACCOMPLISHED)

SEE FIG. A−FFAAA SHEET 01

A340−57−4090

ACCOMPLISHED

SB No

SB No A340−57−4090 OF THE AREAS A AND C

(REFER TO SUBTASK 574125−833−009 AND 574125−833−010)

(REFER TO SUBTASK 574125−832−005) AND

SB No A340−57−4090 OF THE FASTENER HOLES OF

THE AREAS A AND C OF THE FRAME 40, LH AND RH SIDES,

REPEAT THE ROTOTEST INSPECTION PRE

(REFER TO SUBTASK 574125−832−007) AND

SB No A340−57−4090 OF THE FASTENER HOLES OF

REPEAT THE ROTOTEST INSPECTION POST

IN TRANSITION FIT, LH AND RH SIDES, BEFORE NEXT FLIGHT

CRACKS YES NO FOUND

INSTALL NEW FASTENER OF THE

HOLE DIAMETER AND DO A ROTOTEST INSPECTION,

OVERSIZE THE HOLES OF THE AREA B TO FIRST

OVERSIZE IN COMPARISON WITH THE CURRENT

(REFER TO SUBTASK 574125−833−011) AND

CONTACT AIRBUS

AREA B IN TRANSITION FIT, LH AND RH SIDES, 

(REFER TO SUBTASK 574125−833−017) AND

(REFER TO SUBTASK 574125−832−009) AND

OF THE FASTENER HOLES OF THE AREA B

OF THE FRAME 40, LH AND RH SIDES

REPEAT THE ROTOTEST INSPECTION

THE AREAS A AND C OF THE FRAME 40, LH AND RH SIDES,

LH AND RH SIDES, BEFORE NEXT FLIGHT

BEFORE NEXT FLIGHT

CONTACT AIRBUS

BEFORE NEXT FLIGHT

(REFER TO SUBTASK 574125−833−013 AND 574125−833−014)

OR

(REFER TO SUBTASK 574125−833−015 AND 574125−833−016)

(REFER TO SUBTASK 574125−833−018)

BEFORE NEXT FLIGHT

(REFER TO SUBTASK 574125−832−010)

AT THE INTERVAL GIVEN IN THE TABLE 5 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 574125−832−006)

AT THE INTERVAL GIVEN IN THE TABLE 3 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 574125−832−008)

AT THE INTERVAL GIVEN IN THE TABLE 4 OF

THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 574125−833−012)

AREAS A AND C

HOLES 25, 41, 42, 44, 45, 46 AND 259

AREA B

HOLES 38, 39 AND 43

THE CURRENT HOLE DIAMETER AND DO A ROTOTEST INSPECTION,

OVERSIZE THE HOLES OF THE AREAS A AND C PRE OR POST

SB No A340−57−4090 TO FIRST OVERSIZE IN COMPARISON WITH

LH AND RH SIDES, BEFORE NEXT FLIGHT

F_SB_574125_5_FAAA_03_04

Figure A-FFAAA - Sheet 03

Flow Chart

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 101

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@A340

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 102

5

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@A340

SERVICE BULLETIN

Appendix 01: Inspection Report

**CONF ALL

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: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 1

5

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

SERVICE BULLETIN

Appendix 01: Inspection Report

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A340−57−4125

DATE OF INSPECTION :

RETURN TO :

INSPECTION METHOD :

LH SIDE

ROTOTEST

CRACKS

YES

INSPECTION

CRACKS AFTER

OVERSIZE

H25 NO

CRACKS CRACKS AFTER

OVERSIZE

YES NO YES NO YES NO

RH SIDE

H38 YES NO YES NO YES NO YES NO

H39 YES NO YES NO YES NO YES NO

H41 YES NO YES NO YES NO YES NO

H42 YES NO YES NO YES NO YES NO

H43 YES NO YES NO YES NO YES NO

H44 YES NO YES NO YES NO YES NO

H45 YES NO YES NO YES NO YES NO

H46 YES NO YES NO YES NO YES NO

H259 YES NO YES NO YES NO YES NO

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − 

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

E−mail: Structure.sbinspectionresult@airbus.com

F_SB_574125_5_RAAA_01_01

Figure A-FRAAA - Sheet 01

Appendix 01: Inspection Report

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 2

5

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

SERVICE BULLETIN

Appendix 01: Inspection Report

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A340−57−4125

DATE OF INSPECTION :

RETURN TO :

INSPECTION METHOD : ROTOTEST

INSPECTION

H25

H38

H39

H41

H42

H43

H44

H45

H46

H259

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − 

CENTER WING BOX (WB/LR)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

E−mail: Structure.sbinspectionresult@airbus.com

LH SIDE

mm

FINAL

DIAMETER

in

RH SIDE

INITIAL

DIAMETER

FINAL

DIAMETER

INITIAL

DIAMETER

mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

F_SB_574125_5_RAAA_02_01

Figure A-FRAAA - Sheet 02

Appendix 01: Inspection Report

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 3

5

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

SERVICE BULLETIN

Appendix 01: Inspection Report

**CONF ALL

FR40

VIEW LOOKING AFT

STGR38

STGR39

STGR40

H25

H39

H44

H42 H41

H46 H45

H259

H43

H38

LH SIDE SHOWN

RH SIDE SYMMETRICAL

CENTER WING BOX LOWER PANEL REFERENCE

F_SB_574125_5_RAAA_03_00

Figure A-FRAAA - Sheet 03

Appendix 01: Inspection Report

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 4

5

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@A340

SERVICE BULLETIN

Appendix 01: Inspection Report

**CONF ALL

FR40 FRONT

FITTING

(8.5 mm)

(0.335 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

FR40 POST

Y1959

(6 mm)

(0.236 in)

FR40 FRONT

FITTING

(6 mm)

(0.236 in)

FR40 REAR

FITTING

(9.2 mm)

(0.362 in)

HOLE 25 HOLE 38

HOLE 43

FR40 POST

Y1959

(6 mm)

(0.236 in)

FITTING

Y1959

(12 mm)

(0.472 in)

FR40 FRONT

FITTING

(6 mm)

(0.236 in)

FR40 SPAR

WEB

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

FWD

FWD

FWD NOTE:

THESE THICKNESSES ARE THEORETICAL

AFT LOWER

FITTING

Y1959

(12 mm)

(0.472 in)

AFT LOWER

F_SB_574125_5_RAAA_04_01

Figure A-FRAAA - Sheet 04

Appendix 01: Inspection Report

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 5

5

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@A340

SERVICE BULLETIN

Appendix 01: Inspection Report

**CONF ALL

FR40 FRONT

FITTING

(6 mm)

(0.236 in)

HOLE 39

HOLE 41, 42, 44, 46 HOLE 45, 259

FR40 POST

Y1959

(6 mm)

(0.236 in)

AFT LOWER FITTING

Y1959

(8 mm)

(0.315 in)

FR40 FRONT

FITTING

(6 mm)

(0.236 in)

FR40 SPAR

WEB

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

FWD

FWD

FWD

NOTE:

THESE THICKNESSES ARE THEORETICAL

FR40 SPAR

WEB

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

FR40

ORBITAL TEE

(6 mm)

(0.236 in)

FR40 FRONT

FITTING

(6 mm)

(0.236 in)

FR40 SPAR

WEB

(4 mm)

(0.157 in)

FR40 REAR

FITTING

(5 mm)

(0.197 in)

F_SB_574125_5_RAAA_05_01

Figure A-FRAAA - Sheet 05

Appendix 01: Inspection Report

DATE: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 6

5

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@A340

SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - CENTER WING BOX - INSPECTION OF FASTENER HOLES AT

FRAME 40 VERTICAL WEB BELOW INTRADOS

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: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 1

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@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: Mar 12/13 SERVICE BULLETIN No.: A340-57-4125

REVISION No.: 00 - Mar 12/13 Page: 1

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