@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 - TAIL CONE - THS SUPPORT STRUTS AT FR91 -

INSPECTION FOR CRACKS

MODIFICATION No.: None

This page transmits Revision No.03 of Service Bulletin No.A340-53-4208

ADDITIONAL WORK

**CONF ALL

Additional work is required by this revision for aircraft modified by any previous issue.

The additional work involves a repetitive inspection for strut-end diameter less than 43mm (1.69in).

REASON

Revision No. 03 issued to update the effectivity, the compliance time, the inspection procedure and the

flow chart.

CHANGES

SUMMARY

EFFECTIVITY OPERATOR LIST UPDATED R

MANPOWER MANPOWER UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED R

COMPLIANCE

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

MANPOWER MANPOWER UPDATED R

PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED R

PUBLICATIONS AFFECTED ADDED N

MATERIAL INFORMATION

LIST OF MATERIALS - OPERATOR

SUPPLIED

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 1

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Consumable Materials

Consumable CMLD01 CONSUMABLE MATERIAL SET UPDATED

CONSUMABLE UPDATED

R

ACCOMPLISHMENT INSTRUCTIONS

TASK 534208- 832-848-001-Inspection of

the THS support struts

TASK SOLUTION UPDATED

NOTE UPDATED

R

Task associated data - 001 ELAPSED TIME UPDATED R

Subtask 534208-832-201-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 534208-280-201-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 534208-280-202-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 534208-020-201-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

MATERIAL LIST UPDATED

R

Subtask 534208-420-201-001 SUBTASK SOLUTION UPDATED

CONSUMABLE UPDATED

NOTE UPDATED

MATERIAL LIST UPDATED

R

TASK 534208- 832-850-001-Inspection -

ADDITIONAL WORK

TASK SOLUTION ADDED N

Task associated data - 001 TASK ASSOCIATED DATA ADDED N

Subtask 534208-910-202-001 SUBTASK SOLUTION ADDED N

Subtask 534208-839-202-001 SUBTASK SOLUTION ADDED N

Subtask 534208-941-202-001 SUBTASK SOLUTION ADDED N

Subtask 534208-280-203-001 SUBTASK SOLUTION ADDED N

Subtask 534208-942-202-001 SUBTASK SOLUTION ADDED N

Fig. A-GFAAA

Fig. A-GFAAA Sheet 01 SHEET UPDATED R

Fig. A-GFAAA Sheet 02 SHEET UPDATED R

Fig. A-GFAAA Sheet 03 SHEET UPDATED R

Fig. A-GBAAA

Fig. A-GBAAA Sheet 01 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

Revision No. 01 issued to amend the compliance sentence due to the issue of the AD, add a check of

the strut-end diameter and to amend the procedure accordingly.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Revision No. 02 issued to update the effectivity and Fig. A-GBAAA and reduce the gap from 2.50mm

(0.098in) to 1.00mm (0.039in).

REVISION SEQUENCE

ORIGINAL: Feb 07/13

REVISION No. : 01 - Jun 10/13

REVISION No. : 02 - Aug 08/13

REVISION No. : 03 - Feb 28/14

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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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 - TAIL CONE - THS SUPPORT STRUTS AT FR91 -

INSPECTION FOR CRACKS

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

The Trimmable Horizontal Stabilizer (THS) is supported and articulated at Frame (FR)91. Any lateral

movement is prevented by 4 diagonal support struts. During routine maintenance done on several

aircraft in this area, support struts have been found cracked. The affected area is the strut end and

typical cracks are longitudinal. On some aircraft several cracks per support strut have been found.

The Airbus Technical Disposition, LR5350D12005293, has been released to do a sampling inspection

on selected aircraft to confirm the issue.

Further investigation has shown that there are two different suppliers of the struts which makes it

possible to have a mixture of both struts installed on the aircraft. It is therefore necessary to do a check

of the strut-end diameter to determine the correct inspection procedure.

To prevent a support strut rupture, Airbus has decided to do a dedicated repeat inspection of the

affected area on all A330 and A340 aircraft.

After the inspection, depending on the supplier and result, it is necessary to install a clamping device to

the strut end through the accomplishment of the modification Service Bulletin, A330-53-4199.

The installation of the clamping device is temporary pending a permanent solution which will be

introduced through a modification Service Bulletin at a later date.

Airbus has issued an SBIT, Ref 13-0015 dated Apr 29/13 and an AMOC, Ref 10044559R01 dated Apr

23/13 to inform operators.

The accomplishment of this Service Bulletin will detect potential damage at the support strut end and

limit the risk of THS lateral movement.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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SERVICE BULLETIN

SUMMARY

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.

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPD01 See SB

Component COMPD02 See SB

EFFECTIVITY

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

06Y 15R 15T 36V 38W 58X 83V 98X ABD AFR AIB ALK ARG

CAL CCA CPA DGA DLH FIN GAF GFA HFY I2L IBE IRC IRM

KAC LAN M3R MAU MDG MSR NMB OAL PAL QAF RJA S3R SAA

SAS SFB SLM SVW SWR TAP THT THY UAE VCV VIR XAX

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU 53.53.04.001

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

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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@A340

SERVICE BULLETIN

SUMMARY

MANPOWER

Task 534208-832-848-001: Inspection of the THS support struts

TOTAL MANHOURS 6.50

ELAPSED TIME (HOURS) 6.50

Task 534208-832-850-001: Inspection - ADDITIONAL WORK

TOTAL MANHOURS 3.00

ELAPSED TIME (HOURS) 3.00

APPENDICES

Appendix 01 - Inspection Report

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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@A340

SERVICE BULLETIN

SUMMARY

**CONF ALL

B

FR91

Z310

A

TYPICAL

A

B

B

B

B

AREA TO BE

INSPECTED

AREA TO BE

INSPECTED

F_SB_534208_6_SAAA_01_00

Figure A-GSAAA - Sheet 01

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 4

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@A340

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - TAIL CONE - THS SUPPORT STRUTS AT FR91 -

INSPECTION FOR CRACKS

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 0004 0006 0009 0014 0020 0022-0026 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 0101 0104 0114-0115 0117 0123 0125-0126 0128 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

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 0377-0379 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

06Y 0139 0149

15R 0151

15T 0009

36V 0024

38W 0282

58X 0004

83V 0133

98X 0429

ABD 0210

AFR 0029 0078 0084 0186 0207 0237 0245 0246 0260 0307 0310 0377

0399

AIB 0131 0141 0161 0182

ALK 0032 0033 0034 0367 0374 0381

ARG 0063 0074 0080 0085 0093 0094 0123 0126 0128 0170 0193 0373

CAL 0402 0406 0411 0415 0433 0541

CCA 0192 0199 0201 0242 0243 0264

CPA 0136 0137 0142 0147 0157 0160 0208 0218 0220 0227 0228

DGA 0075 0081

DLH 0035 0052 0053 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 0355

GFA 0212 0215 0554

HFY 0117 0190 0202

I2L 0048 0216 0257

IBE 0088 0125 0134 0145 0146 0217 0221 0329 0414 0459 0474 0483

IRC 0002

IRM 0020 0056

KAC 0089 0090 0101 0104

LAN 0359 0363 0442

M3R 0061

MAU 0076 0152 0194 0268 0793 0800

MDG 0319

MSR 0156 0159 0178

NMB 0047 0051

OAL 0280 0292

PAL 0173 0176 0187 0196 0302 0318 0332 0387

QAF 0026 0528

RJA 0014 0022 0038 0043

S3R 0204

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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@A340

SERVICE BULLETIN

OPERATOR MSN

SAA 0006 0197 0378 0544 0582 0590 0643 0646 0651

SAS 0167 0413 0424 0430 0435 0450 0467 0470

SFB 0046

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 0270 0331

UAE 0163 0166 0185 0236

VCV 0031

VIR 0114 0164 0214 0225

XAX 0273 0278

(4) Configuration by MSN

MSN CONFIGURATION

0002 0004 0006 0009 0014 0020 0022 0023 0024 0025 0026

0029 0031 0032 0033 0034 0035 0038 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 0101 0104 0114 0115 0117 0123 0125

0126 0128 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 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 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

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

standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Component COMPD01 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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@A340

SERVICE BULLETIN

MATERIAL QTY PER A/C SEE NOTES

Component COMPD02 As required

Consumable CMLD01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

The Trimmable Horizontal Stabilizer (THS) is supported and articulated at Frame (FR)91.

Any lateral movement is prevented by 4 diagonal support struts. During routine

maintenance done on several aircraft in this area, support struts have been found

cracked. The affected area is the strut end and typical cracks are longitudinal. On some

aircraft several cracks per support strut have been found.

The Airbus Technical Disposition, LR5350D12005293, has been released to do a

sampling inspection on selected aircraft to confirm the issue.

Further investigation has shown that there are two different suppliers of the struts which

makes it possible to have a mixture of both struts installed on the aircraft. It is therefore

necessary to do a check of the strut-end diameter to determine the correct inspection

procedure.

(2) Objective/Action

To prevent a support strut rupture, Airbus has decided to do a dedicated repeat

inspection of the affected area on all A330 and A340 aircraft.

After the inspection, depending on the supplier and result, it is necessary to install a

clamping device to the strut end through the accomplishment of the modification Service

Bulletin, A330-53-4199.

The installation of the clamping device is temporary pending a permanent solution which

will be introduced through a modification Service Bulletin at a later date.

Airbus has issued an SBIT, Ref 13-0015 dated Apr 29/13 and an AMOC, Ref

10044559R01 dated Apr 23/13 to inform operators.

(3) Advantages

The accomplishment of this Service Bulletin will detect potential damage at the support

strut end and limit the risk of THS lateral movement.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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SERVICE BULLETIN

Task 534208-832-848-001: Inspection of the THS support struts

(1) Do a check of the Strut-End Diameter

(2) Do a High Frequency Eddy Current Inspection of the support struts with an end dia

equal to or more than 43mm

(3) Do a High Frequency Eddy Current Inspection of the support struts with an end dia

of less than 43mm

(4) Remove the clamps from the THS support struts

(5) Install the clamps on the THS support struts

Task 534208-832-850-001: Inspection - ADDITIONAL WORK

(1) Specific/Special Inspection/Check

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

For the first batch of aircraft (MSN 0002 up to MSN 0210):

- This Service Bulletin must be accomplished within 6 months from Service Bulletin

original issue date.

- Repetitive inspections are to be accomplished at intervals of 42 months or 20000

FH whichever occurs first, from the last inspection date for TAC strut-end dia. equal

or more than 43mm (1.69in).

For SARMA strut-end dia. less than 43mm (1.69in.) the repetitive inspections are to

be accomplished at intervals of 12 months from the last inspection date or within 3

months after ISB revision 03 issue date, whatever occurs later and thereafter at

intervals not to exceed 12 months since the last inspection, inspect in accordance

with SB A330-53-4208.

For the second batch of aircraft (MSN 0212 up to MSN 0447):

- This Service Bulletin must be accomplished within 24 months from Service Bulletin

original issue date.

- Repetitive inspections are to be accomplished at intervals of 42 months or 20000

FH whichever occurs first, from the last inspection date for TAC strut-end dia. equal

or more than 43mm (1.69in).

For SARMA strut-end dia. less than 43mm (1.69in.) the repetitive inspections are to

be accomplished at intervals of 12 months from the last inspection date or within 3

months after ISB revision 03 issue date, whatever occurs later and thereafter at

intervals not to exceed 12 months since the last inspection, inspect in accordance

with SB A330-53-4208.

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@A340

SERVICE BULLETIN

For the third batch of aircraft (MSN 0450 up to MSN 0955):

- This Service Bulletin must be accomplished within 36 months from Service Bulletin

original issue date.

- Repetitive inspections are to be accomplished at intervals of 42 months or 20000

FH whichever occurs first, from the last inspection date for TAC strut-end dia. equal

or more than 43mm (1.69in).

For SARMA strut-end dia. less than 43mm (1.69in.) the repetitive inspections are to

be accomplished at intervals of 12 months from the last inspection date or within 3

months after ISB revision 03 issue date, whatever occurs later and thereafter at

intervals not to exceed 12 months since the last inspection, inspect in accordance

with SB A330-53-4208.

NOTE: Aircraft previously inspected by AIRBUS Technical Disposition,

LR5350D12005293 have to be considered as part of the third batch of

aircraft.

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for 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.

NOTE: The elapsed time is calculated for only one of the possible HFEC inspections

of all four struts taking into account the possible removal/installation of

clamps. If clamps are not installed then the elapsed time is reduced

accordingly.

Task 534208-832-848-001: Inspection of the THS support struts

Get Access 0.50

On Aircraft

Do a check of the Strut-End Diameter 0.50

Do a High Frequency Eddy Current Inspection of the

support struts with an end dia equal to or more than

43mm

2.00

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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@A340

SERVICE BULLETIN

Task 534208-832-848-001: Inspection of the THS support struts

Do a High Frequency Eddy Current Inspection of the

support struts with an end dia of less than 43mm

2.00

Remove the clamps from the THS support struts 0.50

Install the clamps on the THS support struts 0.50

Close-Up 0.50

TOTAL MANHOURS 6.50

ELAPSED TIME (HOURS) 6.50

Task 534208-832-850-001: Inspection - ADDITIONAL WORK

Get Access 0.50

On Aircraft

Specific/Special Inspection/Check 2.00

Close-Up 0.50

TOTAL MANHOURS 3.00

ELAPSED TIME (HOURS) 3.00

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53

12-34-24 20-21-11 24-42-00

53-53-11

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 53-56-10

Service Bulletin (SB) A340-53-4199

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-00

K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 535127-01-1

535127-01-2

535127-01-3

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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SERVICE BULLETIN

This Page Intentionally Left Blank

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@A340

SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.

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 COMPD01 AIRBUS Material, Logistics and Suppliers

IFD - In Flight Desk

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 4012

For ordering by E-mail:

ifd.spares@airbus.com

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

multiple suppliers ensure access to minimum prices. AIRBUS recommends Customers

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

B/E Aerospace. The address is:

Component COMPD02 B/E AEROSPACE INC.

CONSUMABLES MANAGEMENT

10000 NW 15th Terrace Miami

FL 33172

USA

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

Tel US: +1 305 925 2600

Tel ASIA: +1 310 900 1300

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

Fax US: +1 305 507 7191

Fax ASIA: +1 310 819 1200

SITA: MIAMMCR

E-Mail: AOGdesk_CMG@beaerospace.com

internet: http://www.beconsumables.com

or, alternatively any other source on the open

market.

(2) Price and Availability

No AIRBUS kit will be provided.

Operator supplied AIRBUS parts required to accomplish this Service Bulletin are to be

purchased by a spares purchase order.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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SERVICE BULLETIN

Operator supplied standard hardware parts required to accomplish this Service Bulletin

are to be supplied from the Operator’s stock.

B. INDUSTRY SUPPORT INFORMATION

As a special policy applied to this Service Bulletin, and in case of findings only, AIRBUS will

provide the material at no charge for orders placed before Dec 31/15.

For the organisation of this retrofit, you are kindly requested to contact AIRBUS retrofit

management department.

AIRBUS CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

France

E-mail : monitored.retrofit@airbus.com

Tel : (33) 5 67 19 06 22

Fax : (33) 5 61 93 27 45

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

NOTE: To accomplish this Service Bulletin, and in case of strut replacement, it is

necessary to use the expendable parts listed in AMM 53-53-11, Page

Block 401.

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Varnish-- Electrical Bonding

Structure

04TMB2 As required

Polysulfide Sealant-Low Adhesion

Fillet Structure

06AEB2 As required

Non Hardening Jointing Putty-High

Temp. Area - St

06LDG2 As required

Non Aqueous Cleaner-General - - 08BAA9 As required

Corrosion Preventive CompoundWater Displacing &12ADB1 As required

Textile-Lint Free Cotton - 14SBA1 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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SERVICE BULLETIN

(2) Components

Component COMPD01

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

NOTES

F5357414000000 STRUT

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

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only required if the replacement of a

support strut is necessary. The quantity of these items are to be ordered

as required.

Component COMPD02

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

NOTES

MS24665-153 PIN

MS24665-157 PIN

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

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

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

correct part number to part number relationship.

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

shall be ordered as necessary through the given channel.

NOTE: The components listed above are only required if the replacement of a

support strut is necessary. The quantity of these items are to be ordered

as required.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

If it is required to replace a support strut to accomplish this Service Bulletin it is

necessary to use the tools listed in AMM 53-53-11, Page Block 401.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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SERVICE BULLETIN

(3) Special Tools

None

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 534208-832-848-001 - Inspection of the THS support struts

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.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words ’refer to’ are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words ’in accordance with’ are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

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

and Compliance paragraphs and not to serve as the primary source for tasks or

compliance times given in this Service Bulletin.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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SERVICE BULLETIN

Task Associated Data

Zone

310

Access

Door 312AR 313AL

Manpower

TOTAL MANHOURS 6.50

ELAPSED TIME (HOURS) 6.50

A. GENERAL

(1) Subtask 534208-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

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

51-42-00

(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

the Consumable Materials List (CML).

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

(c) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

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

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

20-21-11-911-801.

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

(g) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 534208-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 14

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SERVICE BULLETIN

B. PREPARATION

(1) Subtask 534208-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

310 Access Door 312AR, Door 313AL

Manpower Resources

Skills NON SPECIFIC

References

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

Task 24-42-00-861-801

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

12-34-24-860-802.

(b) Energize the ground service network, refer to AMM Task 24-42-00-861-801.

(c) Put an access platform in position below the access door 312AR.

(d) Open the access doors 312AR and 313AL.

(e) Set the light switch 4LJ to ON.

C. PROCEDURE

(1) Subtask 534208-832-201-001 - Do a check of the Strut-End Diameter

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

References

Fig. A-GFAAA

Inspection Flow Chart

Sheet 01

Sheet 02

Sheet 03

Fig. A-GDAAA

Check of Strut-end Diameter

Sheet 01

Refer to Fig. A-GFAAA Sheet 01 and Fig. A-GDAAA

(a) Inspect the strut ends for the installation of clamps.

1 If clamps are installed:

- Remove them in accordance with SUBTASK 534208-020-201 001

Remove the clamps from the THS support struts .

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SERVICE BULLETIN

- Continue with the inspection detailed in SUBTASK 534208-280-201 001

Do a High Frequency Eddy Current Inspection of the support struts with

an end dia equal to or more than 43mm .

NOTE: If clamps are installed then the diameter of the strut end is

equal to or more than 43mm (1.69in.).

2 If clamps are not installed:

a Do a check of the strut end diameter "D", refer to Fig. A-GDAAA Sheet

01.

<1> If the diameter "D" is equal to or more than 43mm (1.69in.), continue

with the inspection detailed in SUBTASK 534208-280-201 001 Do a

High Frequency Eddy Current Inspection of the support struts with

an end dia equal to or more than 43mm .

<2> If the diameter "D" is less than 43mm (1.69in.), continue with the

inspection detailed in SUBTASK 534208-280-202 001 Do a High

Frequency Eddy Current Inspection of the support struts with an end

dia of less than 43mm .

(2) Subtask 534208-280-201-001 - Do a High Frequency Eddy Current Inspection of the

support struts with an end dia equal to or more than 43mm

Work Zones and Access Panels

Zone Access/Work location

310 Access Door 312AR

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral - -08BAA9 As required

Textile-Lint Free Cotton - 14SBA1 As required

References

Aircraft Maintenance Manual (AMM) 53-53-11, Page Block 401

Non Destructive Test Manual (NTM) 53-56-10

Service Bulletin (SB) A340-53-4199

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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SERVICE BULLETIN

References

Fig. A-GFAAA

Inspection Flow Chart

Sheet 01

Sheet 02

Sheet 03

Fig. A-GCAAA

Inspection Area - Strut-end dia. equal to

or more than 43mm

Sheet 01

Sheet 02

Refer to Fig. A-GFAAA Sheet 02, Fig. A-GCAAA and Appendix 01 - Inspection Report

(a) If necessary, clean the support struts with:

Non Aqueous

Cleaner-General - -

08BAA9 As required

Textile-Lint Free

Cotton -

14SBA1 As required

(b) Do a High Frequency Eddy Current (HFEC) inspection of the strut ends for cracks

in accordance with NTM 53-56-10.

1 No cracks found:

- If previously installed, reinstall the clamps before next flight, in accordance

with SUBTASK 534208-420-201 001 Install the clamps on the THS

support struts .

or

- If no clamps where previously installed, accomplish Service Bulletin

A340-53-4199 before next flight, to install them.

2 Individual crack with a max length less than 15 mm (0.59 in.) or no more than

4 cracks less than or equal to 15 mm (0.59 in.) found on at least one strut

end:

- If previously installed, reinstall the clamps before next flight, in accordance

with SUBTASK 534208-420-201 001 Install the clamps on the THS

support struts .

or

- If no clamps where previously installed, accomplish Service Bulletin

A340-53-4199 before next flight, to install them.

3 Individual crack with a max length equal to or more than 15 mm (0.59 in.) or

more than 4 cracks less than or equal to 15 mm (0.59 in.) found on at least

one strut end:

- Replace the affected strut with a new strut, which has an end diameter

equal to or more than 43mm (1.69in.), before next flight, refer to AMM

53-53-11, Page Block 401 and use the parts listed in Component

COMPD01 and Component COMPD02.

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SERVICE BULLETIN

- If previously installed, reinstall the clamps before next flight, in accordance

with SUBTASK 534208-420-201 001 Install the clamps on the THS

support struts .

or

- Replace the affected strut with a new strut, which has an end diameter

equal to or more than 43mm (1.69in.), before next flight, refer to AMM

53-53-11, Page Block 401 and use the parts listed in Component

COMPD01 and Component COMPD02.

- If no clamps where previously installed, accomplish Service Bulletin

A340-53-4199 before next flight, to install them.

(c) Report the results of this inspection to AIRBUS within 10 days, refer to Appendix 01

- Inspection Report .

(d) Repeat the inspection at the intervals given in Paragraph 1.E.(2) of this Service

Bulletin.

(3) Subtask 534208-280-202-001 - Do a High Frequency Eddy Current Inspection of the

support struts with an end dia of less than 43mm

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral - -08BAA9 As required

Textile-Lint Free Cotton - 14SBA1 As required

References

Aircraft Maintenance Manual (AMM) 53-53-11, Page Block 401

Non Destructive Test Manual (NTM) 53-56-10

Service Bulletin (SB) A340-53-4199

Fig. A-GFAAA

Inspection Flow Chart

Sheet 01

Sheet 02

Sheet 03

Fig. A-GEAAA

Inspection Area - Strut-end dia. less

than 43mm

Sheet 01

Refer to Fig. A-GFAAA Sheet 03, Fig. A-GEAAA and Appendix 01 - Inspection Report

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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SERVICE BULLETIN

(a) If necessary, clean the support struts with:

Non Aqueous

Cleaner-General - -

08BAA9 As required

Textile-Lint Free

Cotton -

14SBA1 As required

(b) Do a High Frequency Eddy Current (HFEC) inspection of the strut ends for cracks

in accordance with NTM 53-56-10.

1 No cracks found:

- Report the results of this inspection to AIRBUS within one month, refer to

Appendix 01 - Inspection Report .

- Repeat the inspection at the intervals given in Paragraph 1.E.(2) of this

Service Bulletin.

2 Cracks found on at least one strut end:

- Replace the affected strut with a new strut, which has an end diameter

equal to or more than 43mm (1.69in.), before next flight, refer to AMM

53-53-11, Page Block 401 and use the parts listed in Component

COMPD01 and Component COMPD02.

- Accomplish Service Bulletin A340-53-4199 before next flight.

- Report the results of this inspection to AIRBUS within 10 days, refer to

Appendix 01 - Inspection Report .

- Repeat the inspection at the intervals given in Paragraph 1.E.(2) of this

Service Bulletin.

(4) Subtask 534208-020-201-001 - Remove the clamps from the THS support struts

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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SERVICE BULLETIN

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral - -08BAA9 As required

Textile-Lint Free Cotton - 14SBA1 As required

References

Fig. A-GBAAA

Removal/Installation of the clamps

Sheet 01

Refer to Fig. A-GBAAA Sheet 01

(a) From each support strut, remove:

2 Nut NAS1726-5E Item (4) Retain

2 Washer NAS1149D0563K Item (3) Retain

2 Bolt NSA5031-5-42 Item (2) Retain

2 Clamp F5357685020000 Item (1) Retain

(b) Remove the remaining sealant from the support struts and clean them with:

Non Aqueous

Cleaner-General - -

08BAA9 As required

Textile-Lint Free

Cotton -

14SBA1 As required

(5) Subtask 534208-420-201-001 - Install the clamps on the THS support struts

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

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SERVICE BULLETIN

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Varnish-- Electrical Bonding

Structure

04TMB2 As required

Polysulfide Sealant-Low

Adhesion Fillet Structure

06AEB2 As required

Non Hardening Jointing

Putty-High Temp. Area - St

06LDG2 As required

Corrosion Preventive

Compound-Water

Displacing &

12ADB1 As required

NOTE: Slightly rotate the clamp to maintain a sufficient gap between the clamp

and the rudder servo-command hydraulic tube to prevent interference.

(a) To the interface surfaces of the clamps, Item (1), apply:

Polysulfide SealantLow Adhesion Fillet

Structure

06AEB2 As required

NOTE: Application of the sealant is required at the interfaces between the

two clamp halves and at the interfaces between the clamps and the

support struts.

(b) To the bolts, item (2), apply:

Non Hardening

Jointing Putty-High

Temp. Area - St

06LDG2 As required

(c) On each support strut, install:

2 Nut NAS1726-5E Item (4) Retained at

removal

2 Washer NAS1149D0563K Item (3) Retained at

removal

2 Bolt NSA5031-5-42 Item (2) Retained at

removal

2 Clamp F5357685020000 Item (1) Retained at

removal

(d) Protect the visible edges of the sealant, 09-019, with:

Varnish-- Electrical

Bonding Structure

04TMB2 As required

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SERVICE BULLETIN

(e) On the clamps and fasteners which you have installed, apply:

Corrosion

Preventive

Compound-Water

Displacing &

12ADB1 As required

D. TEST

None

E. CLOSE-UP

(1) Subtask 534208-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

310

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-42-00-862-801

(a) Make sure that the work area is clean and clear of tools and other items of

equipment.

(b) Set the light switch 4LJ to OFF.

(c) Close the access doors 312AR and 313AL.

(d) Remove the access platform.

(e) De-energize the ground service network, refer to AMM Task 24-42-00-862-801.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

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@A340

SERVICE BULLETIN

Task 534208-832-850-001 - Inspection - ADDITIONAL WORK

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.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words ’refer to’ are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words ’in accordance with’ are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

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

and Compliance paragraphs and not to serve as the primary source for tasks or

compliance times given in this Service Bulletin.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 23

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@A340

SERVICE BULLETIN

Task Associated Data

Zone

310

Access

Door 312AL 312AR

Manpower

TOTAL MANHOURS 3.00

ELAPSED TIME (HOURS) 3.00

A. GENERAL

(1) Subtask 534208-910-202-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

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

51-42-00

(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

the Consumable Materials List (CML).

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

(c) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

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

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

20-21-11-911-801.

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

(g) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 534208-839-202-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 24

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@A340

SERVICE BULLETIN

B. PREPARATION

(1) Subtask 534208-941-202-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

310 Access Door 312AR, Door 312AL

Manpower Resources

Skills NON SPECIFIC

References

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

Task 24-42-00-861-801

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

12-34-24-860-802.

(b) Energize the ground service network, refer to AMM Task 24-42-00-861-801.

(c) Put an access platform in position below the access door 312AR.

(d) Open the access doors 312AR and 313AL.

(e) Set the light switch 4LJ to ON.

C. PROCEDURE

(1) Subtask 534208-280-203-001 - Specific/Special Inspection/Check

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral - -08BAA9 As required

Textile-Lint Free Cotton - 14SBA1 As required

References

Aircraft Maintenance Manual (AMM) 53-53-11, Page Block 401

Non Destructive Test Manual (NTM) 53-56-10

Service Bulletin (SB) A340-53-4199

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 25

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@A340

SERVICE BULLETIN

References

Fig. A-GEAAA

Inspection Area - Strut-end dia. less

than 43mm

Sheet 01

Fig. A-GFAAA

Inspection Flow Chart

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-GFAAA Sheet 03, Fig. A-GEAAA and Appendix 01 - Inspection Report

(a) If necessary, clean the support struts with:

Non Aqueous

Cleaner-General - -

08BAA9 As required

Textile-Lint Free

Cotton -

14SBA1 As required

(b) Do a High Frequency Eddy Current (HFEC) inspection of the strut ends for cracks

in accordance with NTM 53-56-10.

1 No cracks found:

- Report the results of this inspection to AIRBUS within one month, refer to

Appendix 01 - Inspection Report .

- Repeat the inspection at the intervals given in Paragraph 1.E.(2) of this

Service Bulletin.

2 Cracks found on at least one strut end:

- Replace the affected strut with a new strut, which has an end diameter

equal to or more than 43mm (1.69in.), before next flight, refer to AMM

53-53-11, Page Block 401 and use the parts listed in Component

COMPD01 and Component COMPD02.

- Accomplish Service Bulletin A340-53-4199 before next flight.

- Report the results of this inspection to AIRBUS within 10 days, refer to

Appendix 01 - Inspection Report .

- Repeat the inspection at the intervals given in Paragraph 1.E.(2) of this

Service Bulletin.

D. TEST

None

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 26

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@A340

SERVICE BULLETIN

E. CLOSE-UP

(1) Subtask 534208-942-202-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 24-42-00-862-801

(a) Make sure that the work area is clean and clear of tools and other items of

equipment.

(b) Set the light switch 4LJ to OFF.

(c) Close the access doors 312AR and 313AL.

(d) Remove the access platform.

(e) De-energize the ground service network, refer to AMM Task 24-42-00-862-801.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 27

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@A340

SERVICE BULLETIN

**CONF ALL

Z310

A

A

FR91

B

B

B

B

B

B

NOTE:

01 CHECK DIAMETER D

D 01

F_SB_534208_6_DAAA_01_00

Figure A-GDAAA - Sheet 01

Check of Strut-end Diameter

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 28

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@A340

SERVICE BULLETIN

**CONF ALL

CHECK THE STRUT ENDS FOR

THE INSTALLATION OF CLAMPS

NO INSTALLED YES

CLAMPS

CHECK THE DIAMETER OF

THE STRUT END

YES

NO THAN 43.0mm (1.69in.)

DIA. LESS

NOTE:

THE PURPOSE OF FLOW CHARTS IS

TO SUPPLEMENT THE INFORMATION

GIVEN IN THE PROCEDURE AND

COMPLIANCE PARAGRAPHS AND

NOT TO SERVE AS THE PRIMARY

SOURCE FOR TASKS OR 

COMPLIANCE TIMES GIVEN IN THIS 

SERVICE BULLETIN.

REMOVE CLAMPS

CONTINUE ON

SHEET 02

CONTINUE ON

SHEET 03

NOTE:

01 IT IS POSSIBLE THAT A MIXTURE OF

BOTH STRUTS MAY BE INSTALLED

ON THE AIRCRAFT

01

F_SB_534208_6_FAAA_01_04

Figure A-GFAAA - Sheet 01

Inspection Flow Chart

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 29

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@A340

SERVICE BULLETIN

**CONF ALL

 HIGH FREQUENCY EDDY CURRENT

INSPECTION OF THE STRUT ENDS

FOR CRACKS

DO A 

ON AT LEAST ONE NO

STRUT END

CRACKS FOUND

YES

REPLACE THE AFFECTED

SUPPORT STRUT

INSTALL THE

REMOVED CLAMPS

ACCOMPLISH

A340−53−4199

SERVICE BULLETIN

PARA. 1.E.(2) OF THIS SERVICE BULLETIN

REPEAT THE INSPECTION AT THE INTERVALS GIVEN IN

RESULTS TO AIRBUS

REPORT THE INSPECTION

CONTINUED

FROM SHEET 01

YES

WITHIN THE

GIVEN LIMITS

CRACKS 

NO

INSTALLED ON

THE STRUT

WERE CLAMPS

ENDS

YES NO

NOTE:

02 NEW STRUT DIAMETER 43.0mm (1.69in.) TAC

02

F_SB_534208_6_FAAA_02_03

Figure A-GFAAA - Sheet 02

Inspection Flow Chart

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 30

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@A340

SERVICE BULLETIN

**CONF ALL

 HIGH FREQUENCY EDDY CURRENT

INSPECTION OF THE STRUT ENDS

FOR CRACKS

DO A 

ON AT LEAST ONE NO

STRUT END

CRACKS FOUND

YES

REPLACE THE AFFECTED

SUPPORT STRUT

ACCOMPLISH

A340−53−4199

SERVICE BULLETIN

PARA. 1.E.(2) OF THIS SERVICE BULLETIN

REPEAT THE INSPECTION AT THE INTERVALS GIVEN IN

RESULTS TO AIRBUS

REPORT THE INSPECTION

WITHIN 10 DAYS

RESULTS TO AIRBUS

REPORT THE INSPECTION

WITHIN ONE MONTH

EVERY 12 MONTHS

REPEAT INSPECTION

CONTINUED

FROM SHEET 01

NOTE:

02 NEW STRUT DIAMETER 43.0mm (1.69in.) TAC

02

F_SB_534208_6_FAAA_03_02

Figure A-GFAAA - Sheet 03

Inspection Flow Chart

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 31

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@A340

SERVICE BULLETIN

**CONF ALL

C

C

B

FR91

Z310

A

TYPICAL

(1)

(2)

(3)

(4)

C

D

B

A

B

B

B

(2)

(3)

(4)

(1)

D

D

NOTE:

02

02 ENSURE THAT THERE IS NO CONTACT

BETWEEN THE CLAMPS, ITEM (1) AND THE NUT

CYLINDRICAL AREA

01

01 ENSURE THAT THERE IS NO CONTACT

BETWEEN THE CLAMPS, ITEM (1) AND THE CONICAL AREA

F_SB_534208_6_BAAA_01_04

Figure A-GBAAA - Sheet 01

Removal/Installation of the clamps

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 32

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@A340

SERVICE BULLETIN

**CONF ALL

Z310

A

A

B

C

FR91

F_SB_534208_6_CAAA_01_01

Figure A-GCAAA - Sheet 01

Inspection Area - Strut-end dia. equal to or more than 43mm

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 33

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@A340

SERVICE BULLETIN

**CONF ALL

POSSIBLE CRACK

POSSIBLE CRACKS

B

C

F_SB_534208_6_CAAA_02_01

Figure A-GCAAA - Sheet 02

Inspection Area - Strut-end dia. equal to or more than 43mm

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 34

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@A340

SERVICE BULLETIN

**CONF ALL

FR91

Z310

A

A

B

B

B

B

B

F_SB_534208_6_EAAA_01_00

Figure A-GEAAA - Sheet 01

Inspection Area - Strut-end dia. less than 43mm

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 35

6

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@A340

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 36

6

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@A340

SERVICE BULLETIN

Appendix 01 - Inspection Report

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN NO:

DATE OF INSPECTION:

AIRCRAFT MSN:

FLIGHT CYCLES:

FLIGHT HOURS:

PLEASE SEND REPORTING SHEET TO:

 AIRBUS CUSTOMER SERVICES ENGINEERING

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

E−MAIL: structure.sbinspectionresult@airbus.com

A340−53−4208

SEES1

FINDINGS: YES NO

INSPECTION METHOD: SPECIAL DETAILED INSPECTION

FAX: +33(0)561 93 36 14

TYPICAL

AREA TO BE

INSPECTED

AREA TO BE

INSPECTED

Z310

A

B

FR91

A

B

B

A

A

B

B

A

A

B

B

B

B

4

3

1

2

F_SB_534208_6_AAAA_01_02

Figure A-GAAAA - Sheet 01

Inspection Report

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 1

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@A340

SERVICE BULLETIN

Appendix 01 - Inspection Report

**CONF ALL INSPECTION REPORT

STRUT

NUMBER

1

2

3

4

DIAMETER END POS. CRACK QUANTITY LENGTH CRACK 1 LENGTH CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 LENGTH CRACK 5

A

B

A

B

A

B

A

B

F_SB_534208_6_AAAA_02_01

Figure A-GAAAA - Sheet 02

Inspection Report

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 2

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SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - TAIL CONE - THS SUPPORT STRUTS AT FR91 -

INSPECTION FOR CRACKS

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: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 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 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: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208

REVISION No.: 03 - Feb 28/14 Page: 1

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