@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - CENTER FUSELAGE - INSPECTION OF RODS IN BELLY

FAIRING

MODIFICATION No.: None

This page transmits Revision No.01 of Service Bulletin No.A340-53-4185

ADDITIONAL WORK

**CONF ALL

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

REASON

Revision No. 01 issued to redefine item numbers of the rods at FR39.

CHANGES

SUMMARY

EFFECTIVITY OPERATOR LIST UPDATED R

Fig. A-FSAAA

Fig. A-FSAAA Sheet 01 SHEET UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Material Effectivity MATERIAL EFFECTIVITY UPDATED

MATERIAL SET QUANTITY UPDATED

R

ACCOMPLISHMENT INSTRUCTIONS

TASK 534185- 832-801-001-Inspection

Subtask 534185-020-001-001 SUBTASK SOLUTION ADDED N

Subtask 534185-020-002-001 SUBTASK SOLUTION ADDED N

Subtask 534185-420-001-001 SUBTASK SOLUTION ADDED N

Subtask 534185-420-002-001 SUBTASK SOLUTION ADDED N

TASK 534185- 832-802-001-Inspection

Subtask 534185-020-003-001 SUBTASK SOLUTION ADDED N

Subtask 534185-020-004-001 SUBTASK SOLUTION ADDED N

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 534185-833-001-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

MATERIAL LIST UPDATED

R

Subtask 534185-833-002-001 SUBTASK SOLUTION UPDATED

PART NUMBER UPDATED

ITEM NUMBER UPDATED

MATERIAL LIST UPDATED

R

Subtask 534185-420-003-001 SUBTASK SOLUTION ADDED N

Subtask 534185-420-004-001 SUBTASK SOLUTION ADDED N

Fig. A-FBAAA

Fig. A-FBAAA Sheet 01 SHEET UPDATED R

Fig. A-FBBAA

Fig. A-FBBAA Sheet 01 SHEET UPDATED R

Fig. A-FBCAA

Fig. A-FBCAA Sheet 01 SHEET UPDATED R

Fig. A-FBCAA Sheet 02 SHEET UPDATED R

Fig. A-FBDAA FIGURE SOLUTION ADDED N

Fig. A-FBDAA Sheet 01 SHEET ADDED N

Appendix 01

Fig. A-FAAAA

Fig. A-FAAAA Sheet 02 SHEET UPDATED R

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

No previous revision

REVISION SEQUENCE

ORIGINAL: Jan 17/11

REVISION No. : 01 - Apr 07/11

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 2

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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: 53

TITLE: FUSELAGE - CENTER FUSELAGE - INSPECTION OF RODS IN BELLY

FAIRING

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

A rod manufacturing process defect has been identified at TAC that could have led to deliver rods with

cracks (crimped end of the rod only).

This Inspection Service Bulletin (ISB) requires to inspect some rods in the belly fairing. Those rods can

be manufactured by either SARMA-SKF or by TAC.

- If they are manufactured by SARMA-SKF, no further action is required.

- If they are manufactured by TAC, it is mandatory within 6 years from the ISB issuance to perform a

Non Destructive Test (NDT) inspection at the crimped end of the rod body.

Cracked TAC rods must be replaced.

Accomplishment of this ISB will prevent any cracks on rods installed on the belly fairing.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO LROPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

SUMMARY

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA01 1 See SB Rod

Component COMPA02 1 See SB Pin

EFFECTIVITY

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

47W 56W 83V AAW AFR AIB ALK ARG B3R CAL CCA CES CPA

DGA DLH FIN GAF GFA HFY IBE KAC LAN LHT M3R MAU MSR

NMB OAL PAL QAF R3L RJA S3R SAA SAS SFW SLM SVW SWR

TAP THT THY UAE VCV VIR XAX

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 534185-832-801-001: Inspection

TOTAL MANHOURS 7.25

ELAPSED TIME (HOURS) 7.25

Task 534185-832-802-001: Inspection

TOTAL MANHOURS 13.00

ELAPSED TIME (HOURS) 13.00

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

SUMMARY

APPENDICES

Appendix 01

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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@A340

SERVICE BULLETIN

SUMMARY

**CONF ALL

FR37

FR39

FR48

FR53.2

FR53.9

B

B

B B

B

B

B B

B

A

MANUFACTURER AND PN TO BE IDENTIFIED

B TYPICAL

A Z190

C

C

F_SB_534185_5_SAAA_01_02

Figure A-FSAAA - Sheet 01

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SERVICE BULLETIN

SUMMARY

**CONF ALL

AREA TO BE

TYPICAL CRACK

INSPECTED

LOCATION

TYPICAL

C

F_SB_534185_5_SAAA_02_00

Figure A-FSAAA - Sheet 02

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 6

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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: 53

TITLE: FUSELAGE - CENTER FUSELAGE - INSPECTION OF RODS IN BELLY

FAIRING

MODIFICATION No.: None

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

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

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

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

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

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

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

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

340-211 340-212 340-213 340-311 340-312 340-313

(2) Effectivity by MSN

0002-0006 0008-0009 0011 0013-0015 0018-0029 0031-0035 0038-0041 0043-0044

0046-0049 0051-0053 0056-0058 0061 0063 0074-0076 0078-0081 0084-0085

0088-0091 0093-0094 0097 0101 0103-0104 0114-0115 0117 0123 0125-0126

0128-0129 0131 0133-0137 0139 0141-0142 0145-0147 0149-0152 0154 0156-0161

0163-0164 0166-0170 0173-0176 0178-0180 0182 0185-0187 0190 0192-0194

0196-0197 0199 0201-0202 0204 0207-0208 0210 0212-0218 0220-0221 0225

0227-0228 0233 0235-0237 0239 0242-0243 0245-0246 0252 0257 0260 0263-0264

0268 0270 0273-0274 0278 0280 0282 0292 0297 0302 0304 0307 0310 0318-0319

0321 0325 0327 0329 0331-0332 0335 0347 0352 0354-0355 0359 0363 0367

0373-0374 0377-0379 0381 0385 0387 0390 0395 0399 0402 0406 0411 0413-0415

0424 0429-0430 0433-0435 0438 0442 0446-0447 0450 0459 0467 0470 0474 0483

0528 0538 0541 0544-0546 0554 0556 0559 0561-0562 0582 0585 0590 0598 0643

0646 0651 0668 0793 0800 0835 0844 0921 0938 0955

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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

47W 0009

56W 0013

83V 0039 0040 0097 0103 0133

AAW 0151

AFR 0029 0078 0084 0186 0207 0210 0237 0245 0246 0260 0307 0310

0319 0373 0377 0399

AIB 0414

ALK 0032 0033 0034 0367 0374

ARG 0048 0063 0074 0080 0085 0093 0094

B3R 0046

CAL 0402 0406 0411 0415 0433 0541

CCA 0192 0199 0201 0242 0243 0264

CES 0129 0131 0141 0161 0182

CPA 0123 0126 0128 0136 0137 0142 0147 0157 0160 0208 0218 0220

0227 0228 0381

DGA 0075 0081

DLH 0020 0024 0027 0028 0035 0052 0053 0056 0135 0158 0213 0233

0252 0297 0304 0321 0325 0327 0335 0347 0352 0354 0379 0390

0434 0447

FIN 0058 0168 0174 0835 0844 0921 0938

GAF 0274

GFA 0212 0215 0282 0554

HFY 0117 0450

IBE 0005 0088 0125 0134 0145 0146 0170 0193 0217 0221 0302 0318

0329 0332 0387 0459 0474 0483

KAC 0089 0090 0101 0104

LAN 0167 0359 0363 0429 0442

LHT 0355

M3R 0061

MAU 0076 0152 0194 0268 0793 0800

MSR 0156 0159 0178

NMB 0047 0051

OAL 0235 0239 0280 0292

PAL 0173 0176 0187 0196

QAF 0026 0528

R3L 0004

RJA 0014 0022 0038 0043

S3R 0204

SAA 0006 0008 0011 0018 0019 0021 0197 0378 0544 0582 0590 0643

0646 0651

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SERVICE BULLETIN

OPERATOR MSN

SAS 0413 0424 0430 0435 0467 0470

SFW 0015

SLM 0049

SVW 0955

SWR 0150 0154 0169 0175 0179 0263 0538 0545 0546 0556 0559 0561

0562 0585 0598

TAP 0041 0044 0079 0091

THT 0385 0395 0438 0446 0668

THY 0023 0025 0057 0115 0180 0216 0257 0270 0331

UAE 0139 0149 0163 0166 0185 0190 0202 0236

VCV 0031

VIR 0002 0003 0114 0164 0214 0225

XAX 0273 0278

(4) Configuration by MSN

MSN CONFIGURATION

0002 0003 0004 0005 0006 0008 0009 0011 0013 0014 0015

0018 0019 0020 0021 0022 0023 0024 0025 0026 0027 0028

0029 0031 0032 0033 0034 0035 0038 0039 0040 0041 0043

0044 0046 0047 0048 0049 0051 0052 0053 0056 0057 0058

0061 0063 0074 0075 0076 0078 0079 0080 0081 0084 0085

0088 0089 0090 0091 0093 0094 0097 0101 0103 0104 0114

0115 0117 0123 0125 0126 0128 0129 0131 0133 0134 0135

0136 0137 0139 0141 0142 0145 0146 0147 0149 0150 0151

0152 0154 0156 0157 0158 0159 0160 0161 0163 0164 0166

0167 0168 0169 0170 0173 0174 0175 0176 0178 0179 0180

0182 0185 0186 0187 0190 0192 0193 0194 0196 0197 0199

0201 0202 0204 0207 0208 0210 0212 0213 0214 0215 0216

0217 0218 0220 0221 0225 0227 0228 0233 0235 0236 0237

0239 0242 0243 0245 0246 0252 0257 0260 0263 0264 0268

0270 0273 0274 0278 0280 0282 0292 0297 0302 0304 0307

0310 0318 0319 0321 0325 0327 0329 0331 0332 0335 0347

0352 0354 0355 0359 0363 0367 0373 0374 0377 0378 0379

0381 0385 0387 0390 0395 0399 0402 0406 0411 0413 0414

0415 0424 0429 0430 0433 0434 0435 0438 0442 0446 0447

0450 0459 0467 0470 0474 0483 0528 0538 0541 0544 0545

0546 0554 0556 0559 0561 0562 0582 0585 0590 0598 0643

0646 0651 0668 0793 0800 0835 0844 0921 0938 0955

001

(5) Configuration definition

**CONF 001

Configuration 001 is valid for all the aircraft given in the effectivity of this Service Bulletin

as a standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Component COMPA01 1

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

MATERIAL QTY PER A/C SEE NOTES

Component COMPA02 1

Consumable CMLA01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

A rod manufacturing process defect has been identified at TAC that could have led to

deliver rods with cracks (crimped end of the rod only).

(2) Objective/Action

This Inspection Service Bulletin (ISB) requires to inspect some rods in the belly fairing.

Those rods can be manufactured by either SARMA-SKF or by TAC.

- If they are manufactured by SARMA-SKF, no further action is required.

- If they are manufactured by TAC, it is mandatory within 6 years from the ISB

issuance to perform a Non Destructive Test (NDT) inspection at the crimped end of

the rod body.

Cracked TAC rods must be replaced.

(3) Advantages

Accomplishment of this ISB will prevent any cracks on rods installed on the belly fairing.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 534185-832-801-001: Inspection

(1) Do a One Time Detailed Inspection of the Rods

Task 534185-832-802-001: Inspection

(1) Do a HFEC Inspection of the TAC Rods

(2) Replace the Upper Rods of the Belly Fairing Structure at FR39

(3) Replace the Lateral Rods of the Belly Fairing Structure at FR39

(4) Replace the Lateral Rods of the Belly Fairing Structure at FR47

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

(5) Replace the Central Rod of the Belly Fairing Structure at FR47

(6) Replace the Upper Rods of the Belly Fairing Structure at FR53.2

(7) Replace the Lateral Rods of the Belly Fairing Structure at FR53.2

(8) Replace the Center Rods of the Belly Fairing Structure at FR53.2

(9) Replace the Upper Rods of the Belly Fairing Structure at FR53.4

(10) Replace the Lateral Rods of the Belly Fairing Structure at FR53.4

(11) Replace the Lateral Rods of the Belly Fairing Structure at FR53.9

(12) Replace the Rods of the Supports of the MLG Door Uplock at FR48

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

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

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

Agency (EASA). It is anticipated that the AD will confirm the thresholds given below but

reference should be made to the AD for confirmation of the mandated accomplishment

timescale.

COMPLIANCE TIME (whichever occurs

first)

CONDITION ACTION

THRESHOLD GRACE PERIOD

REPETITIVE

INTERVAL NOT

TO EXCEED

(whichever occurs

first)

CONF 001 Inspect in

accordance with

SUBTASK

534185-832-001

001 Do a One

Time Detailed

Inspection of the

Rods .

Not later than six

years from SB

issuance

- Not applicable

TAC rod found or

manufacturer

cannot be

identified

Do a HFEC

inspection of the

rod in accordance

with SUBTASK

534185-832-003

001 Do a HFEC

Inspection of the

TAC Rods

Not later than six

years from SB

issuance (See

NOTE)

- Not applicable

Other manufacturer

rod found.

No further action - - -

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

COMPLIANCE TIME (whichever occurs

first)

CONDITION ACTION

THRESHOLD GRACE PERIOD

REPETITIVE

INTERVAL NOT

TO EXCEED

(whichever occurs

first)

If the manufacturer

of the new rod to

be installed is not

TAC, replace the

rod in accordance

with SUBTASK

534185-833-001

001 Replace the

Upper Rods of the

Belly Fairing

Structure at FR39

thru SUBTASK

534185-833-011

001 Replace the

Rods of the

Supports of the

MLG Door Uplock

at FR48

Crack(s) found

If the manufacturer

of the new rod to

be installed is

TAC, do a HFEC

inspection of the

rod.

- In case of

finding, discard

the rod and do

the same with

another rod.

- If no findings,

replace the rod

in accordance

with SUBTASK

534185-833-001

001 Replace

the Upper Rods

of the Belly

Fairing Structure

at FR39

thru SUBTASK

534185-833-011

001 Replace

the Rods of

the Supports of

the MLG Door

Uplock at FR48

Before next flight - Not applicable

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SERVICE BULLETIN

COMPLIANCE TIME (whichever occurs

first)

CONDITION ACTION

THRESHOLD GRACE PERIOD

REPETITIVE

INTERVAL NOT

TO EXCEED

(whichever occurs

first)

No crack found. No further action - - -

NOTE: It is not necessary to perform the HFEC inspection on TAC rods

immediately after identification of the rod manufacturer.

Aircraft can go back into service and the HFEC inspection can be

performed later.

However, HFEC inspection must be performed within six years from the

ISB revision 00 issuance.

NOTE: We recommend to perform the preliminary detailed inspection at the

first C Check from SB issuance date, in order to have time to contact

AIRBUS Material, Logistics and suppliers (SMM) and to ensure all rods

(and B/E Aerospace for associated hardware) availability during the

month where the HFEC inspection will be performed on the aircraft.

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA 21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

Task 534185-832-801-001: Inspection

Get Access 3.00

On Aircraft

Do a One Time Detailed Inspection of the Rods 0.25

Close-Up 4.00

TOTAL MANHOURS 7.25

ELAPSED TIME (HOURS) 7.25

NOTE: The values given for the inspections are valid only for one rod.

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SERVICE BULLETIN

Task 534185-832-802-001: Inspection

Get Access 3.00

On Aircraft

Do a HFEC Inspection of the TAC Rods 0.50

Replace the Upper Rods of the Belly Fairing Structure

at FR39

0.50

Replace the Lateral Rods of the Belly Fairing Structure

at FR39

0.50

Replace the Lateral Rods of the Belly Fairing Structure

at FR47

0.50

Replace the Central Rod of the Belly Fairing Structure

at FR47

0.50

Replace the Upper Rods of the Belly Fairing Structure

at FR53.2

0.50

Replace the Lateral Rods of the Belly Fairing Structure

at FR53.2

0.50

Replace the Center Rods of the Belly Fairing Structure

at FR53.2

0.50

Replace the Upper Rods of the Belly Fairing Structure

at FR53.4

0.50

Replace the Lateral Rods of the Belly Fairing Structure

at FR53.4

0.50

Replace the Lateral Rods of the Belly Fairing Structure

at FR53.9

0.50

Replace the Rods of the Supports of the MLG Door

Uplock at FR48

0.50

Close-Up 4.00

TOTAL MANHOURS 13.00

ELAPSED TIME (HOURS) 13.00

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

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

20-21-11 32-12-00 53-35-11

53-35-13

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

Non Destructive Test Manual (NTM) 51-10-08

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12 51-42-00 51-43-00

51-49-00

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SERVICE BULLETIN

K. PUBLICATION AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

This Page Intentionally Left Blank

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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 :

Component COMPA01 AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 Hamburg

Germany

For ordering by internet:

http://spares.airbus.com

For ordering of single spares by fax: +49 40

50 76 40 13

E-Mail : ifd.spares@airbus.com

Component COMPA02 BAE Aerospoace

10000 NW 15th Terrace

Miami, FL 33172

USA

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

US : +1 305 925 2600

ASIA : +1 310 900 1300

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

US : +1 305 507 7191

ASIA : +1 310 819 1200

Sita : MIAMMCR

or contact your daily sales contact

E-Mail : AOGdesk_CMG@baeaerospace.com

(2) Price and Availability

No AIRBUS kit will be provided. Parts required to accomplish this Service Bulletin are to

be purchased by a Spares Purchase Order.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will provide the operator supplied AIRBUS parts at no charge for those aircraft with

findings further to inspection as per this Service Bulletin.

AIRBUS will reimburse the operator supplied standard hardware parts for those aircraft with

findings further to inspection as per this Service Bulletin.

AIRBUS will credit the manhours indicated in this Service Bulletin for inspections that are

performed on aircraft in warranty at the time of such inspection.

Claims for labor allowance should be received not later than 90 days after completion of the

last affected warranted aircraft.

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 11

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SERVICE BULLETIN

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013B As required

Corrosion Preventive Temporary

Protective Compound

15-005A As required

(2) Components

NOTE: We recommend to perform the preliminary detailed inspection at the

first C Check from SB issuance date, in order to have time to contact

AIRBUS Material, Logistics and suppliers (SMM) and to ensure all rods

(and B/E Aerospace for associated hardware) availability during the

month where the HFEC inspection will be performed on the aircraft.

Component COMPA01

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

NOTES

1 F0003010400100 2 ROD

2 F0003010400300 2 ROD

3 F0003010400400 2 ROD

4 F0003010400500 4 ROD

5 F0003010400700 2 ROD

6 F0003010400800 2 ROD

7 F0003010400900 1 ROD

8 F0003010401100 2 ROD

9 F0003010401200 2 ROD

10 F0003010401400 2 ROD

NOTE: The necessary quantity of rods depends on the inspection results.

Component COMPA02

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

NOTES

15 MS24665-153 36 PIN

18 MS24665-300 6 PIN

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

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

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

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

correct part number to part number relationship.

NOTE: The necessary quantity of pins depends on the inspection results.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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This Page Intentionally Left Blank

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 534185-832-801-001 - Inspection

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS :

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

Task Associated Data

Zone

190

Manpower

TOTAL MANHOURS 7.25

ELAPSED TIME (HOURS) 7.25

A. GENERAL

(1) Subtask 534185-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

B. PREPARATION

(1) Subtask 534185-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 15

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

Task 12-34-24-860-802

Task 32-12-00-010-801

Task 53-35-11-000-801

Task 53-35-13-000-801

Task 53-35-13-000-802

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

12-34-24-860-802).

(b) Open the MLG doors (Refer to AMM Task 32-12-00-010-801).

(c) Remove the following belly fairing access panels :

(Refer to AMM 06-41-53, Page Block 001, AMM Task 53-35-11-000-801, AMM

Task 53-35-13-000-801 and AMM Task 53-35-13-000-802).

191BB, 191CB, 191QB, 192BB, 192CB, 192QB, 195CB or 195AB, 196GB or

196AB, 197BB, 197EB, 197GB, 197HB, 198BB, 198EB, 198GB and 198HB

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

(2) Subtask 534185-020-001-001 - Remove the Aft Fillet Fairing from LH side for

Access

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-000-802

Fig. A-FBDAA

Remove/Install the Aft Fillet Fairing for

access

Sheet 01

(a) Remove :

Fig. A-FBDAA

(Refer to AMM Task 53-35-11-000-802)

1 Aft Fillet Fairing Item (30) Retain

(3) Subtask 534185-020-002-001 - Remove the Aft Fillet Fairing from RH side for

Access

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-000-802

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

References

Fig. A-FBDAA

Remove/Install the Aft Fillet Fairing for

access

Sheet 01

(a) Remove :

Fig. A-FBDAA

(Refer to AMM Task 53-35-11-000-802)

1 Aft Fillet Fairing Item (31) Retain

C. PROCEDURE

(1) Subtask 534185-832-001-001 - Do a One Time Detailed Inspection of the Rods

Work Zones and Access Panels

Zone Access/Work location

190

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

References

Fig. A-FBAAA

Area to be Inspected

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FBBAA

Flow Chart

Sheet 01

Sheet 02

(a) For the inspection area, refer to Fig. A-FBAAA.

(b) Do a one time detailed inspection of the rods.

Refer to Fig. A-FBBAA.

1 If the manufacturer of the rod is TAC or if the manufacturer cannot be

identified, go to SUBTASK 534185-832-003 001 Do a HFEC Inspection of the

TAC Rods or go to SUBTASK 534185-942-001 001 Close-up and release

your aircraft, if you intend to do the HFEC inspection later (SUBTASK

534185-832-003 001) but within 6 years from the ISB revision 00 issuance.

NOTE: We recommend to perform the preliminary detailed inspection

at the first C Check from SB issuance date, in order to

have time to contact AIRBUS Material, Logistics and suppliers

(SMM) and to ensure all rods (and B/E Aerospace for

associated hardware) availability during the month where the

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

HFEC inspection will be performed on the aircraft.

2 If the manufacturer of the rod is not TAC, no further action is required.

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

D. TEST

None

E. CLOSE-UP

(1) Subtask 534185-420-001-001 - Install the Aft Fillet Fairing at LH side

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-400-802

Fig. A-FBDAA

Remove/Install the Aft Fillet Fairing for

access

Sheet 01

(a) Install :

Fig. A-FBDAA

(Refer to AMM Task 53-35-11-400-802)

1 Aft Fillet Fairing Item (30) Retained at

removal

(2) Subtask 534185-420-002-001 - Install the Aft Fillet Fairing at RH side

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-400-802

Fig. A-FBDAA

Remove/Install the Aft Fillet Fairing for

access

Sheet 01

(a) Install :

Fig. A-FBDAA

(Refer to AMM Task 53-35-11-400-802)

1 Aft Fillet Fairing Item (31) Retained at

removal

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

(3) Subtask 534185-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

Task 32-12-00-410-801

Task 53-35-11-000-801

Task 53-35-13-000-801

Task 53-35-13-000-802

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

equipment.

(b) Remove the access platform(s).

(c) Install the following belly fairing access panels :

(Refer to AMM 06-41-53, Page Block 001, AMM Task 53-35-11-000-801, AMM

Task 53-35-13-000-801 and AMM Task 53-35-13-000-802).

191BB, 191CB, 191QB, 192BB, 192CB, 192QB, 195CB or 195AB, 196GB or

196AB, 197BB, 197EB, 197GB, 197HB, 198BB, 198EB, 198GB and 198HB

(d) Close the MLG doors (Refer to AMM Task 32-12-00-410-801).

(e) Restore the systems and the aircraft to normal operating conditions.

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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This Page Intentionally Left Blank

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

Task 534185-832-802-001 - Inspection

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS :

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

Task Associated Data

Zone

190

Manpower

TOTAL MANHOURS 13.00

ELAPSED TIME (HOURS) 13.00

A. GENERAL

(1) Subtask 534185-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

(2) Subtask 534185-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 21

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SERVICE BULLETIN

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Inhibiting Brush

Consistency

09-013B As required

Corrosion Preventive

Temporary Protective

Compound

15-005A As required

References

Aircraft Maintenance Manual (AMM) Task 20-11-11-911-803

Task 20-21-11-911-801

Structural Repair Manual (SRM) 51-23-12

51-42-00

51-43-00

51-49-00

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

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

(c) Torque the standard threaded fasteners (Refer to SRM 51-49-00 and AMM Task

20-21-11-911-801).

(d) Renew the protective finish with :

Corrosion

Preventive

Temporary

Protective

Compound

15-005A As required

(Refer to SRM 51-23-12)

(e) On the head of the fasteners apply :

Corrosion Inhibiting

Brush Consistency

09-013B As required

(f) Secure the rod ends with lock wire (Refer to AMM Task 20-11-11-911-803).

B. PREPARATION

(1) Subtask 534185-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 22

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

Task 12-34-24-860-802

Task 32-12-00-010-801

Task 53-35-11-000-801

Task 53-35-13-000-801

Task 53-35-13-000-802

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

12-34-24-860-802).

(b) Open the MLG doors (Refer to AMM Task 32-12-00-010-801).

(c) Remove the following belly fairing access panels :

(Refer to AMM 06-41-53, Page Block 001, AMM Task 53-35-11-000-801, AMM

Task 53-35-13-000-801 and AMM Task 53-35-13-000-802).

191BB, 191CB, 191QB, 192BB, 192CB, 192QB, 195CB or 195AB, 196GB or

196AB, 197BB, 197EB, 197GB, 197HB, 198BB, 198EB, 198GB and 198HB

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

(2) Subtask 534185-020-003-001 - Remove the Aft Fillet Fairing from LH side for

Access

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-000-802

Fig. A-FBDAA

Remove/Install the Aft Fillet Fairing for

access

Sheet 01

(a) Remove :

Fig. A-FBDAA

(Refer to AMM Task 53-35-11-000-802)

1 Aft Fillet Fairing Item (30) Retain

(3) Subtask 534185-020-004-001 - Remove the Aft Fillet Fairing from RH side for

Access

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-000-802

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

References

Fig. A-FBDAA

Remove/Install the Aft Fillet Fairing for

access

Sheet 01

(a) Remove :

Fig. A-FBDAA

(Refer to AMM Task 53-35-11-000-802)

1 Aft Fillet Fairing Item (31) Retain

C. PROCEDURE

(1) Subtask 534185-832-003-001 - Do a HFEC Inspection of the TAC Rods

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-10-08

Fig. A-FBAAA

Area to be Inspected

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FBBAA

Flow Chart

Sheet 01

Sheet 02

(a) For the inspection area, refer to Fig. A-FBAAA.

(b) Do a HFEC inspection of the TAC rods as per NTM 51-10-08.

Refer to Fig. A-FBBAA.

1 If no crack is found, no further action is required.

2 If crack is found, do the following steps.

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

(2) Subtask 534185-833-001-001 - Replace the Upper Rods of the Belly Fairing

Structure at FR39

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 39

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 F0003010400500 2 ROD

NOTE: The necessary quantity of rods depends on the inspection results.

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 MS24665-153 4 PIN

NOTE: The necessary quantity of pins depends on the inspection results.

References

Fig. A-FBCAA

Replacement of the rods

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove from LH side :

Fig. A-FBCAA Sheet 03, Detail F

2 Bolt Item (11) Retain

2 Nut Item (12) Retain

2 Washer Item (13) Retain

2 Washer Item (14) Retain

2 Pin Item (15) Discard

2 Bush Item (16) Retain

2 Bush Item (17) Retain

1 Rod Item (4) Discard

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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(b) Install on LH side :

Fig. A-FBCAA Sheet 03, Detail F

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010400500 Item 4

2 Bush Item (16) Retained at

removal

2 Bush Item (17) Retained at

removal

2 Bolt Item (11) Retained at

removal

2 Nut Item (12) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Washer Item (14) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

(c) Remove from RH side :

Fig. A-FBCAA Sheet 03, Detail F

2 Bolt Item (11) Retain

2 Nut Item (12) Retain

2 Washer Item (13) Retain

2 Washer Item (14) Retain

2 Pin Item (15) Discard

2 Bush Item (16) Retain

2 Bush Item (17) Retain

1 Rod Item (4) Discard

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

(d) Install on RH side :

Fig. A-FBCAA Sheet 03, Detail F

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010400500 Item 4

2 Bush Item (16) Retained at

removal

2 Bush Item (17) Retained at

removal

2 Bolt Item (11) Retained at

removal

2 Nut Item (12) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Washer Item (14) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

(3) Subtask 534185-833-002-001 - Replace the Lateral Rods of the Belly Fairing

Structure at FR39

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 39

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 F0003010400100 2 ROD

NOTE: The necessary quantity of rods depends on the inspection results.

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 MS24665-153 4 PIN

NOTE: The necessary quantity of pins depends on the inspection results.

References

Fig. A-FBCAA

Replacement of the rods

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove from LH side :

Fig. A-FBCAA Sheet 03, Detail F

2 Bolt Item (11) Retain

2 Nut Item (12) Retain

2 Washer Item (13) Retain

2 Washer Item (14) Retain

2 Pin Item (15) Discard

2 Bush Item (16) Retain

2 Bush Item (17) Retain

1 Rod Item (1) Discard

(b) Install on LH side :

Fig. A-FBCAA Sheet 03, Detail F

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010400100 Item 1

2 Bush Item (16) Retained at

removal

2 Bush Item (17) Retained at

removal

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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2 Bolt Item (11) Retained at

removal

2 Nut Item (12) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Washer Item (14) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

(c) Remove from RH side :

Fig. A-FBCAA Sheet 03, Detail F

2 Bolt Item (11) Retain

2 Nut Item (12) Retain

2 Washer Item (13) Retain

2 Washer Item (14) Retain

2 Pin Item (15) Discard

2 Bush Item (16) Retain

2 Bush Item (17) Retain

1 Rod Item (1) Discard

(d) Install on RH side :

Fig. A-FBCAA Sheet 03, Detail F

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010400100 Item 1

2 Bush Item (16) Retained at

removal

2 Bush Item (17) Retained at

removal

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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2 Bolt Item (11) Retained at

removal

2 Nut Item (12) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Washer Item (14) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

(4) Subtask 534185-833-003-001 - Replace the Lateral Rods of the Belly Fairing

Structure at FR47

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 47

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 F0003010401100 2 ROD

NOTE: The necessary quantity of rods depends on the inspection results.

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 MS24665-153 2 PIN

18 MS24665-300 2 PIN

NOTE: The necessary quantity of pins depends on the inspection results.

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

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SERVICE BULLETIN

References

Fig. A-FBCAA

Replacement of the rods

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove from LH side :

Fig. A-FBCAA Sheet 04, Detail G

1 Bolt Item (20) Retain

1 Bolt Item (21) Retain

2 Nut Item (19) Retain

2 Washer Item (22) Retain

2 Washer Item (23) Retain

1 Pin Item (15) Discard

1 Pin Item (18) Discard

1 Bush Item (24) Retain

1 Bush Item (25) Retain

1 Bush Item (26) Retain

1 Bush Item (27) Retain

1 Rod Item (8) Discard

(b) Install on LH side :

Fig. A-FBCAA Sheet 04, Detail G

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010401100 Item 8

1 Bush Item (24) Retained at

removal

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 31

5

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

SERVICE BULLETIN

1 Bush Item (25) Retained at

removal

1 Bush Item (26) Retained at

removal

1 Bush Item (27) Retained at

removal

1 Bolt Item (20) Retained at

removal

1 Bolt Item (21) Retained at

removal

2 Nut Item (19) Retained at

removal

2 Washer Item (22) Retained at

removal

2 Washer Item (23) Retained at

removal

1 Pin-Cotter MS24665-153 Item 15

1 Pin-Cotter MS24665-300 Item 18

(c) Remove from RH side :

Fig. A-FBCAA Sheet 04, Detail G

1 Bolt Item (20) Retain

1 Bolt Item (21) Retain

2 Nut Item (19) Retain

2 Washer Item (22) Retain

2 Washer Item (23) Retain

1 Pin Item (15) Discard

1 Pin Item (18) Discard

1 Bush Item (24) Retain

1 Bush Item (25) Retain

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 32

5

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

SERVICE BULLETIN

1 Bush Item (26) Retain

1 Bush Item (27) Retain

1 Rod Item (8) Discard

(d) Install on RH side :

Fig. A-FBCAA Sheet 04, Detail G

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010401100 Item 8

1 Bush Item (24) Retained at

removal

1 Bush Item (25) Retained at

removal

1 Bush Item (26) Retained at

removal

1 Bush Item (27) Retained at

removal

1 Bolt Item (20) Retained at

removal

1 Bolt Item (21) Retained at

removal

2 Nut Item (19) Retained at

removal

2 Washer Item (22) Retained at

removal

2 Washer Item (23) Retained at

removal

1 Pin-Cotter MS24665-153 Item 15

1 Pin-Cotter MS24665-300 Item 18

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 33

5

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

SERVICE BULLETIN

(5) Subtask 534185-833-004-001 - Replace the Central Rod of the Belly Fairing

Structure at FR47

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 47

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

7 F0003010400900 1 ROD

NOTE: The necessary quantity of rods depends on the inspection results.

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 MS24665-153 2 PIN

NOTE: The necessary quantity of pins depends on the inspection results.

References

Fig. A-FBCAA

Replacement of the rods

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove :

Fig. A-FBCAA Sheet 03, Detail F

2 Bolt Item (11) Retain

2 Nut Item (12) Retain

2 Washer Item (13) Retain

2 Washer Item (14) Retain

2 Pin Item (15) Discard

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 34

5

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

SERVICE BULLETIN

2 Bush Item (16) Retain

2 Bush Item (17) Retain

1 Rod Item (7) Discard

(b) Install :

Fig. A-FBCAA Sheet 03, Detail F

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010400900 Item 7

2 Bush Item (16) Retained at

removal

2 Bush Item (17) Retained at

removal

2 Bolt Item (11) Retained at

removal

2 Nut Item (12) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Washer Item (14) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

(6) Subtask 534185-833-005-001 - Replace the Upper Rods of the Belly Fairing

Structure at FR53.2

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 53.2

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 35

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

SERVICE BULLETIN

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

10 F0003010401400 2 ROD

NOTE: The necessary quantity of rods depends on the inspection results.

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 MS24665-153 4 PIN

NOTE: The necessary quantity of pins depends on the inspection results.

References

Fig. A-FBCAA

Replacement of the rods

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove from LH side :

Fig. A-FBCAA Sheet 03, Detail F

2 Bolt Item (11) Retain

2 Nut Item (12) Retain

2 Washer Item (13) Retain

2 Washer Item (14) Retain

2 Pin Item (15) Discard

2 Bush Item (16) Retain

2 Bush Item (17) Retain

1 Rod Item (10) Discard

(b) Install on LH side :

Fig. A-FBCAA Sheet 03, Detail F

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 36

5

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

SERVICE BULLETIN

1 Rod F0003010401400 Item 10

2 Bush Item (16) Retained at

removal

2 Bush Item (17) Retained at

removal

2 Bolt Item (11) Retained at

removal

2 Nut Item (12) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Washer Item (14) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

(c) Remove from RH side :

Fig. A-FBCAA Sheet 03, Detail F

2 Bolt Item (11) Retain

2 Nut Item (12) Retain

2 Washer Item (13) Retain

2 Washer Item (14) Retain

2 Pin Item (15) Discard

2 Bush Item (16) Retain

2 Bush Item (17) Retain

1 Rod Item (10) Discard

(d) Install on RH side :

Fig. A-FBCAA Sheet 03, Detail F

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010401400 Item 10

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 37

5

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

SERVICE BULLETIN

2 Bush Item (16) Retained at

removal

2 Bush Item (17) Retained at

removal

2 Bolt Item (11) Retained at

removal

2 Nut Item (12) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Washer Item (14) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

(7) Subtask 534185-833-006-001 - Replace the Lateral Rods of the Belly Fairing

Structure at FR53.2

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 53.2

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

5 F0003010400700 2 ROD

NOTE: The necessary quantity of rods depends on the inspection results.

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

18 MS24665-300 4 PIN

NOTE: The necessary quantity of pins depends on the inspection results.

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 38

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

SERVICE BULLETIN

References

Fig. A-FBCAA

Replacement of the rods

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove from LH side :

Fig. A-FBCAA Sheet 04, Detail H

2 Bolt Item (21) Retain

2 Nut Item (19) Retain

4 Washer Item (22) Retain

2 Pin Item (18) Discard

2 Bush Item (26) Retain

2 Bush Item (27) Retain

1 Rod Item (5) Discard

(b) Install on LH side

Fig. A-FBCAA Sheet 04, Detail H

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010400700 Item 5

2 Bush Item (26) Retained at

removal

2 Bush Item (27) Retained at

removal

2 Bolt Item (21) Retained at

removal

2 Nut Item (19) Retained at

removal

4 Washer Item (22) Retained at

removal

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 39

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

SERVICE BULLETIN

2 Pin-Cotter MS24665-300 Item 18

(c) Remove from RH side :

Fig. A-FBCAA Sheet 04, Detail H

2 Bolt Item (21) Retain

2 Nut Item (19) Retain

4 Washer Item (22) Retain

2 Pin Item (18) Discard

2 Bush Item (26) Retain

2 Bush Item (27) Retain

1 Rod Item (5) Discard

(d) Install on RH side

Fig. A-FBCAA Sheet 04, Detail H

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010400700 Item 5

2 Bush Item (26) Retained at

removal

2 Bush Item (27) Retained at

removal

2 Bolt Item (21) Retained at

removal

2 Nut Item (19) Retained at

removal

4 Washer Item (22) Retained at

removal

2 Pin-Cotter MS24665-300 Item 18

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 40

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

SERVICE BULLETIN

(8) Subtask 534185-833-007-001 - Replace the Center Rods of the Belly Fairing

Structure at FR53.2

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 53.2

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

6 F0003010400800 2 ROD

NOTE: The necessary quantity of rods depends on the inspection results.

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 MS24665-153 4 PIN

NOTE: The necessary quantity of pins depends on the inspection results.

References

Fig. A-FBCAA

Replacement of the rods

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove from LH side :

Fig. A-FBCAA Sheet 05, Detail J

2 Bolt Item (11) Retain

2 Nut Item (12) Retain

4 Washer Item (13) Retain

2 Pin Item (15) Discard

2 Bush Item (17) Retain

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 41

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

SERVICE BULLETIN

2 Bush Item (16) Retain

1 Rod Item (6) Discard

(b) Install on LH side :

Fig. A-FBCAA Sheet 05, Detail J

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010400800 Item 6

2 Bush Item (17) Retained at

removal

2 Bush Item (16) Retained at

removal

2 Bolt Item (11) Retained at

removal

2 Nut Item (12) Retained at

removal

4 Washer Item (13) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

(c) Remove from RH side :

Fig. A-FBCAA Sheet 05, Detail J

2 Bolt Item (11) Retain

2 Nut Item (12) Retain

4 Washer Item (13) Retain

2 Pin Item (15) Discard

2 Bush Item (17) Retain

2 Bush Item (16) Retain

1 Rod Item (6) Discard

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 42

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

SERVICE BULLETIN

(d) Install on RH side :

Fig. A-FBCAA Sheet 05, Detail J

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010400800 Item 6

2 Bush Item (17) Retained at

removal

2 Bush Item (16) Retained at

removal

2 Bolt Item (11) Retained at

removal

2 Nut Item (12) Retained at

removal

4 Washer Item (13) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

(9) Subtask 534185-833-008-001 - Replace the Upper Rods of the Belly Fairing

Structure at FR53.4

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 53.4

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 F0003010400400 2 ROD

NOTE: The necessary quantity of rods depends on the inspection results.

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 43

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

SERVICE BULLETIN

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 MS24665-153 4 PIN

NOTE: The necessary quantity of pins depends on the inspection results.

References

Fig. A-FBCAA

Replacement of the rods

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove from LH side :

Fig. A-FBCAA Sheet 05, Detail K

2 Bolt Item (11) Retain

2 Nut Item (12) Retain

4 Washer Item (14) Retain

2 Pin Item (15) Discard

2 Bush Item (17) Retain

2 Bush Item (28) Retain

1 Rod Item (3) Discard

(b) Install on LH side :

Fig. A-FBCAA Sheet 05, Detail K

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010400400 Item 3

2 Bush Item (17) Retained at

removal

2 Bush Item (28) Retained at

removal

2 Bolt Item (11) Retained at

removal

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 44

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

SERVICE BULLETIN

2 Nut Item (12) Retained at

removal

4 Washer Item (14) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

(c) Remove from RH side :

Fig. A-FBCAA Sheet 05, Detail K

2 Bolt Item (11) Retain

2 Nut Item (12) Retain

4 Washer Item (14) Retain

2 Pin Item (15) Discard

2 Bush Item (17) Retain

2 Bush Item (28) Retain

1 Rod Item (3) Discard

(d) Install on RH side :

Fig. A-FBCAA Sheet 05, Detail K

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010400400 Item 3

2 Bush Item (17) Retained at

removal

2 Bush Item (28) Retained at

removal

2 Bolt Item (11) Retained at

removal

2 Nut Item (12) Retained at

removal

4 Washer Item (14) Retained at

removal

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 45

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

SERVICE BULLETIN

2 Pin-Cotter MS24665-153 Item 15

(10) Subtask 534185-833-009-001 - Replace the Lateral Rods of the Belly Fairing

Structure at FR53.4

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 53.4

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 F0003010400300 2 ROD

NOTE: The necessary quantity of rods depends on the inspection results.

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 MS24665-153 4 PIN

NOTE: The necessary quantity of pins depends on the inspection results.

References

Fig. A-FBCAA

Replacement of the rods

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove from LH side :

Fig. A-FBCAA Sheet 05, Detail K

2 Bolt Item (11) Retain

2 Nut Item (12) Retain

4 Washer Item (14) Retain

2 Pin Item (15) Discard

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 46

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@A340

SERVICE BULLETIN

2 Bush Item (17) Retain

2 Bush Item (28) Retain

1 Rod Item (2) Discard

(b) Install at LH side :

Fig. A-FBCAA Sheet 05, Detail K

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010400300 Item 2

2 Bush Item (17) Retained at

removal

2 Bush Item (28) Retained at

removal

2 Bolt Item (11) Retained at

removal

2 Nut Item (12) Retained at

removal

4 Washer Item (14) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

(c) Remove from RH side :

Fig. A-FBCAA Sheet 05, Detail K

2 Bolt Item (11) Retain

2 Nut Item (12) Retain

4 Washer Item (14) Retain

2 Pin Item (15) Discard

2 Bush Item (17) Retain

2 Bush Item (28) Retain

1 Rod Item (2) Discard

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 47

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

SERVICE BULLETIN

(d) Install at RH side :

Fig. A-FBCAA Sheet 05, Detail K

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010400300 Item 2

2 Bush Item (17) Retained at

removal

2 Bush Item (28) Retained at

removal

2 Bolt Item (11) Retained at

removal

2 Nut Item (12) Retained at

removal

4 Washer Item (14) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

(11) Subtask 534185-833-010-001 - Replace the Lateral Rods of the Belly Fairing

Structure at FR53.9

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 53.9

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 F0003010400500 2 ROD

NOTE: The necessary quantity of rods depends on the inspection results.

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 48

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

SERVICE BULLETIN

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 MS24665-153 4 PIN

NOTE: The necessary quantity of pins depends on the inspection results.

References

Fig. A-FBCAA

Replacement of the rods

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

(a) Remove from LH side :

Fig. A-FBCAA Sheet 03, Detail F

2 Bolt Item (11) Retain

2 Nut Item (12) Retain

2 Washer Item (13) Retain

2 Washer Item (14) Retain

2 Pin Item (15) Discard

2 Bush Item (16) Retain

2 Bush Item (17) Retain

1 Rod Item (4) Discard

(b) Install at LH side :

Fig. A-FBCAA Sheet 03, Detail F

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010400500 Item 4

2 Bush Item (16) Retained at

removal

2 Bush Item (17) Retained at

removal

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 49

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@A340

SERVICE BULLETIN

2 Bolt Item (11) Retained at

removal

2 Nut Item (12) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Washer Item (14) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

(c) Remove from RH side :

Fig. A-FBCAA Sheet 03, Detail F

2 Bolt Item (11) Retain

2 Nut Item (12) Retain

2 Washer Item (13) Retain

2 Washer Item (14) Retain

2 Pin Item (15) Discard

2 Bush Item (16) Retain

2 Bush Item (17) Retain

1 Rod Item (4) Discard

(d) Install at RH side :

Fig. A-FBCAA Sheet 03, Detail F

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010400500 Item 4

2 Bush Item (16) Retained at

removal

2 Bush Item (17) Retained at

removal

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 50

5

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@A340

SERVICE BULLETIN

2 Bolt Item (11) Retained at

removal

2 Nut Item (12) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Washer Item (14) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

(12) Subtask 534185-833-011-001 - Replace the Rods of the Supports of the MLG Door

Uplock at FR48

Work Zones and Access Panels

Zone Access/Work location

190 Work location Frame 48

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 F0003010401200 2 ROD

NOTE: The necessary quantity of rods depends on the inspection results.

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 MS24665-153 4 PIN

NOTE: The necessary quantity of pins depends on the inspection results.

References

Fig. A-FBCAA

Replacement of the rods

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Sheet 05

Sheet 06

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 51

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@A340

SERVICE BULLETIN

(a) Remove from LH side :

Fig. A-FBCAA Sheet 06, Detail L

1 Bolt Item (11) Retain

1 Bolt Item (21) Retain

2 Nut Item (12) Retain

2 Washer Item (13) Retain

2 Washer Item (14) Retain

2 Pin Item (15) Discard

1 Bush Item (17) Retain

1 Bush Item (28) Retain

1 Rod Item (9) Discard

(b) Install on LH side :

Fig. A-FBCAA Sheet 06, Detail L

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010401200 Item 9

1 Bush Item (17) Retained at

removal

1 Bush Item (28) Retained at

removal

1 Bolt Item (11) Retained at

removal

1 Bolt Item (21) Retained at

removal

2 Nut Item (12) Retained at

removal

2 Washer Item (13) Retained at

removal

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 52

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SERVICE BULLETIN

2 Washer Item (14) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

(c) Remove from RH side :

Fig. A-FBCAA Sheet 06, Detail L

1 Bolt Item (11) Retain

1 Bolt Item (21) Retain

2 Nut Item (12) Retain

2 Washer Item (13) Retain

2 Washer Item (14) Retain

2 Pin Item (15) Discard

1 Bush Item (17) Retain

1 Bush Item (28) Retain

1 Rod Item (9) Discard

(d) Install on RH side :

Fig. A-FBCAA Sheet 06, Detail L

NOTE: For the installation of the rod, it has to be adjusted to the correct

length and secured with lock wire on both sides then you can

torque the fasteners.

1 Rod F0003010401200 Item 9

1 Bush Item (17) Retained at

removal

1 Bush Item (28) Retained at

removal

1 Bolt Item (11) Retained at

removal

1 Bolt Item (21) Retained at

removal

2 Nut Item (12) Retained at

removal

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 53

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SERVICE BULLETIN

2 Washer Item (13) Retained at

removal

2 Washer Item (14) Retained at

removal

2 Pin-Cotter MS24665-153 Item 15

D. TEST

None

E. CLOSE-UP

(1) Subtask 534185-420-003-001 - Install the Aft Fillet Fairing at LH side

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-400-802

Fig. A-FBDAA

Remove/Install the Aft Fillet Fairing for

access

Sheet 01

(a) Install :

Fig. A-FBDAA

(Refer to AMM Task 53-35-11-400-802)

1 Aft Fillet Fairing Item (30) Retained at

removal

(2) Subtask 534185-420-004-001 - Install the Aft Fillet Fairing at RH side

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 53-35-11-400-802

Fig. A-FBDAA

Remove/Install the Aft Fillet Fairing for

access

Sheet 01

(a) Install :

Fig. A-FBDAA

(Refer to AMM Task 53-35-11-400-802)

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 54

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SERVICE BULLETIN

1 Aft Fillet Fairing Item (31) Retained at

removal

(3) Subtask 534185-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001

Task 32-12-00-410-801

Task 53-35-11-000-801

Task 53-35-13-000-801

Task 53-35-13-000-802

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

equipment.

(b) Remove the access platform(s).

(c) Install the following belly fairing access panels :

(Refer to AMM 06-41-53, Page Block 001, AMM Task 53-35-11-000-801, AMM

Task 53-35-13-000-801 and AMM Task 53-35-13-000-802).

191BB, 191CB, 191QB, 192BB, 192CB, 192QB, 195CB or 195AB, 196GB or

196AB, 197BB, 197EB, 197GB, 197HB, 198BB, 198EB, 198GB and 198HB

(d) Close the MLG doors (Refer to AMM Task 32-12-00-410-801).

(e) Restore the systems and the aircraft to normal operating conditions.

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 55

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SERVICE BULLETIN

**CONF ALL

A

Z190

FR53.9

FR53.2

FR48

FR37

FR39

B

C

D

E

A

E

F_SB_534185_5_BAAA_01_01

Figure A-FBAAA - Sheet 01

Area to be Inspected

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 56

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SERVICE BULLETIN

**CONF ALL

FR53.4

FR53.9

FR53.2

FR47

FR39

F

F

F

F

F

F

F

F

F

F

F

F

F

F

F

F

F

F

F

B

C

D

F_SB_534185_5_BAAA_02_00

Figure A-FBAAA - Sheet 02

Area to be Inspected

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 57

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@A340

SERVICE BULLETIN

**CONF ALL

MANUFACTURER AND PN TO BE IDENTIFIED

F

FR48

F

LH SIDE SHOWN

RH SIDE SYMMETRICAL

E

TYPICAL

F_SB_534185_5_BAAA_03_01

G

G

Figure A-FBAAA - Sheet 03

Area to be Inspected

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 58

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SERVICE BULLETIN

**CONF ALL

AREA TO BE

TYPICAL CRACK

INSPECTED

LOCATION

TYPICAL

F_SB_534185_5_BAAA_04_00

G

Figure A-FBAAA - Sheet 04

Area to be Inspected

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 59

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@A340

SERVICE BULLETIN

**CONF ALL

AT THE THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.2.

THE MANUFACTURER

NO YES

REPORT TO AIRBUS

REFER TO APPENDIX 01

AS PER NTM 51−10−08 AT THRESHOLD

DO A HFEC INSPECTION OF THE ROD

GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.2.

NO FURTHER ACTION

NO CRACKS YES

DO A ONE TIME DETAILED INSPECTION OF THE RODS

IDENTIFY THE PART NUMBER AND

THE MANUFACTURER OF THE ROD

OF THE ROD IS TAC OR THE

SEND THE INSPECTION

REPORT TO AIRBUS

REFER TO APPENDIX 01

NO FURTHER ACTION

SEND THE INSPECTION

A−FBBAA SHEET 2

REFER TO FIGURE

QUESTION

ACTION

FINDING

NOTE:

WE RECOMMEND TO PERFORM THE PRELIMINARY DETAILED INSPECTION AT THE FIRST C−

CHECK FROM SB ISSUANCE DATE, IN ORDER TO HAVE TIME TO CONTACT AIRBUS MATERIAL,

LOGISTICS AND SUPPLIERS (SMM) AND TO ENSURE ALL RODS (AND B/E AEROSPACE FOR

ASSOCIATED HARWARE) AVAILABILITY DURING THE MONTH WHEN THE HFEC INSPECTION

WILL BE PERFORMED ON THE AIRCRAFT.

*

*

IT IS NOT NECESSARY TO PERFORM THE HFEC INSPECTION ON TAC RODS IMMEDIATELY AFTER

IDENTIFICATION OF THE ROD MANUFACTURER.

AIRCRAFT CAN GO BACK INTO SERVICE AND THE HFEC INSPECTION CAN BE PERFORMED LATER.

HOWEVER, HFEC INSPECTION MUST BE PERFORMED WITHIN SIX YEARS FROM THE INSPECTION

SERVICE BULLETIN REVISION 00 ISSUANCE.

MANUFACTURER CANNOT

BE IDENTIFIED

F_SB_534185_5_BBAA_01_04

Figure A-FBBAA - Sheet 01

Flow Chart

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 60

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SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

MANUFACTURER OF

NO YES

OF THE NEW ROD

DO A HFEC INSPECTION

NO CRACKS YES

THE

THE NEW ROD TO BE

REPORT TO AIRBUS

REFER TO APPENDIX 01

NO FURTHER ACTION

SEND THE INSPECTION

A−FBBAA SHEET 1

FROM FIGURE

INSTALLED IS TAC

AS PER NTM 51−10−08

AS DESCRIBED IN SUBTASK 534185−833−001−001

THRU 534185−833−011−001 BEFORE NEXT FLIGHT

REPLACE THE ROD

TO BE INSTALLED

AND GET A NEW ONE

DISCARD THE ROD

F_SB_534185_5_BBAA_02_01

Figure A-FBBAA - Sheet 02

Flow Chart

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 61

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@A340

SERVICE BULLETIN

**CONF ALL

A

Z190

FR53.9

FR53.2

FR48

FR37

FR39

B

C

D

E

A

E

F_SB_534185_5_BCAA_01_02

Figure A-FBCAA - Sheet 01

Replacement of the rods

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 62

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@A340

SERVICE BULLETIN

**CONF ALL

FR53.4

FR53.9

FR53.2

FR47

FR39

F

F

F

F

F

F

F

F

F

B

C

D

(1)

1

(4)

4

(4)

4

(1)

1

(8)

8

(8)

8

(7)

7

(10)

10

(5)

5

(6)

6

(5)

5

(10)

10

(2)

2

(3)

3

(4)

4

(4)

4

(3)

3 (2)

2

G

K

K

H

J

J

H

K

K

G

F_SB_534185_5_BCAA_02_02

Figure A-FBCAA - Sheet 02

Replacement of the rods

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 63

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@A340

SERVICE BULLETIN

**CONF ALL

FR48

(9)

9

LH SIDE SHOWN

RH SIDE SYMMETRICAL

E

(11)

(14)

(13)

(12)

15

(11)

(14) (13)

(12)

(15)

TYPICAL

F

(15)

(17)

(16)

(16)

15 (17)

L

F_SB_534185_5_BCAA_03_02

Figure A-FBCAA - Sheet 03

Replacement of the rods

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 64

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@A340

SERVICE BULLETIN

**CONF ALL

(21)

(22)

(22)

(19)

18

(21)

(22) (22)

(19)

(18)

TYPICAL

(18)

(27)

(26)

(26)

18 (27)

(20)

(22)

(23)

(19)

15

(21)

(22) (23)

(19)

(18)

TYPICAL

(15)

(24)

(25)

(26)

18 (27)

G

H

F_SB_534185_5_BCAA_04_01

Figure A-FBCAA - Sheet 04

Replacement of the rods

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 65

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@A340

SERVICE BULLETIN

**CONF ALL

(11)

(14)

(14)

(12)

15

(11)

(14) (14)

(12)

(15)

TYPICAL

(15)

(17)

(28)

(28)

15 (17)

(11)

(13)

(13)

(12)

15

(11)

(13) (13)

(12)

(15)

TYPICAL

(15)

(17)

(16)

(16)

15 (17)

J

K

F_SB_534185_5_BCAA_05_01

Figure A-FBCAA - Sheet 05

Replacement of the rods

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 66

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SERVICE BULLETIN

**CONF ALL

(11)

(13)

(12)

15

(21)

(14) (13)

(12)

(15)

TYPICAL

(15)

(17)

15 (28)

L

(14)

F_SB_534185_5_BCAA_06_01

Figure A-FBCAA - Sheet 06

Replacement of the rods

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 67

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@A340

SERVICE BULLETIN

**CONF ALL

A

FR37.4

FR39.1

B

(30)

(31)

LH

RH

LH SIDE SHOWN

RH SIDE SYMMETRICAL

B

A

F_SB_534185_5_BDAA_01_00

Figure A-FBDAA - Sheet 01

Remove/Install the Aft Fillet Fairing for access

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 68

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SERVICE BULLETIN

Appendix 01

**CONF ALL

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

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

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 1

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SERVICE BULLETIN

Appendix 01

**CONF ALL

INSPECTION REPORT

DETAIL LH

TAC ROD

YES

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A340−53−4185

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE −

INSPECTION METHOD :

CENTER WING BOX (WB/LR)

1 ROUND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

ROD LOCATION CRACK FOUND ROD REPLACED

B NO YES NO YES NO

DETAIL RH B YES NO YES NO YES NO

DETAIL LH C YES NO YES NO YES NO

DETAIL RH C YES NO YES NO YES NO

DETAIL LH D YES NO YES NO YES NO

DETAIL RH D YES NO YES NO YES NO

DETAIL E YES NO YES NO YES NO

DETAIL LH F YES NO YES NO YES NO

DETAIL RH F YES NO YES NO YES NO

DETAIL LH G YES NO YES NO YES NO

DETAIL RH G YES NO YES NO YES NO

DETAIL LH H YES NO YES NO YES NO

DETAIL RH H YES NO YES NO YES NO

DETAIL LH J YES NO YES NO YES NO

DETAIL RH J YES NO YES NO YES NO

DETAIL LH K YES NO YES NO YES NO

DETAIL RH K YES NO YES NO YES NO

DETAIL LH L YES NO YES NO YES NO

DETAIL RH L YES NO YES NO YES NO

DETAIL LH M YES NO YES NO YES NO

DETAIL RH M YES NO YES NO YES NO

F_SB_534185_5_AAAA_01_00

Figure A-FAAAA - Sheet 01

Inspection Report

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 2

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SERVICE BULLETIN

Appendix 01

**CONF ALL

A Z190

FR53.9

FR53.2

FR48

FR37

FR39

A

B

C B

C

G

F

H

E

D

M

K

G F

J

H

L

L

J

K

F_SB_534185_5_AAAA_02_01

M D

Figure A-FAAAA - Sheet 02

Inspection Report

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 3

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SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - CENTER FUSELAGE - INSPECTION OF RODS IN BELLY

FAIRING

MODIFICATION No.: None

Please complete the appropriate item (A or B):

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

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

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

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

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

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

Or : Intermediate revision YES/NO

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

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

the next feasible revision, this will result in

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

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

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

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

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

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

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 1

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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 4 3 2 1

- Quality rating of the Accomplishment Instructions 4 3 2 1

- Quality rating of the Illustrations 4 3 2 1

- Is this SB easy to understand ? Y / N

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

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

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

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Jan 17/11 SERVICE BULLETIN No.: A340-53-4185

REVISION No.: 01 - Apr 07/11 Page: 1

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