# Airbus Service Bulletin A340-53-4208

Copy: Revision 03 ("FAA-2014-1046 A340-53-4208R3"), 48 pages: PDF https://openairdocs.org/files/sha256/a9/2f/a92fa84425f806e9c14cbd9c7b316a66f6deba44d6f0f66e678d8146b74905a3; text https://openairdocs.org/service-documents/airbus/a340-53-4208/file/a92fa84425f8.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2014-1043; AD 2015-23-05 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A340-53-4208
- Latest revision known: A340-53-4208, Revision 03, dated February 28, 2014 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a340-53-4208

## ADs that cite it (1) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2015-23-05](https://openairdocs.org/ad/2015-23-05.md), effective Dec 28, 2015: Revisions 01, 02 and 03

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a340-53-4208/proposed.md).

## Text (48 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2014-1043; AD 2015-23-05 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

@A340
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
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
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 2

@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
REVISION No.: 03 - Feb 28/14 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 3

@A340
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
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208
REVISION No.: 03 - Feb 28/14 Page: 3
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 4

@A340
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
This Page Intentionally Left Blank
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208
REVISION No.: 03 - Feb 28/14 Page: 4
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 5

@A340
SERVICE BULLETIN
SUMMARY
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
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
REVISION No.: 03 - Feb 28/14 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 6

@A340
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
REVISION No.: 03 - Feb 28/14 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 7

@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
REVISION No.: 03 - Feb 28/14 Page: 3
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 8

@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
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 9

@A340
SERVICE BULLETIN
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
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
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208
REVISION No.: 03 - Feb 28/14 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 10

@A340
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
REVISION No.: 03 - Feb 28/14 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 11

@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
REVISION No.: 03 - Feb 28/14 Page: 3
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 12

@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
REVISION No.: 03 - Feb 28/14 Page: 4
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 13

@A340
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.
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208
REVISION No.: 03 - Feb 28/14 Page: 5
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 14

@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 Av iation Safety Agenc y (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
REVISION No.: 03 - Feb 28/14 Page: 6
6
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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
REVISION No.: 03 - Feb 28/14 Page: 7
6
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SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208
REVISION No.: 03 - Feb 28/14 Page: 8
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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
REVISION No.: 03 - Feb 28/14 Page: 9
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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
T e l:( 3 3 )56 71 90 62 2
F a x:( 3 3 )56 19 32 74 5
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 Compound-
Water Displacing &
12ADB1
 As required
Textile-Lint Free Cotton -
 14SBA1
 As required
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208
REVISION No.: 03 - Feb 28/14 Page: 10
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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
REVISION No.: 03 - Feb 28/14 Page: 11
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SERVICE BULLETIN
(3) Special Tools
None
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208
REVISION No.: 03 - Feb 28/14 Page: 12
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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
REVISION No.: 03 - Feb 28/14 Page: 13
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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 .
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208
REVISION No.: 03 - Feb 28/14 Page: 15
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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 Cleaner-
General - -
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: 16
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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.
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208
REVISION No.: 03 - Feb 28/14 Page: 17
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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 Cleaner-
General - -
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
REVISION No.: 03 - Feb 28/14 Page: 18
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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
REVISION No.: 03 - Feb 28/14 Page: 19
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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 Cleaner-
General - -
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 th e 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
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208
REVISION No.: 03 - Feb 28/14 Page: 20
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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 Sealant-
Low 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
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208
REVISION No.: 03 - Feb 28/14 Page: 21
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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
REVISION No.: 03 - Feb 28/14 Page: 22
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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
6
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### Page 32

@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
6
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### Page 33

@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 - Specifi c/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 Cleaner-
General - -
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
6
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### Page 34

@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
6
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### Page 35

@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
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 36

@A340
SERVICE BULLETIN
**CONF ALL
Z310
A
A
FR91
B
B
B
B
B
B
NOTE:
CHECK DIAMETER D01
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
6
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### Page 37

@A340
SERVICE BULLETIN
**CONF ALL
CHECK THE STRUT ENDS FOR
THE INSTALLATION OF CLAMPS
NO YESINSTALLED
CLAMPS
CHECK THE DIAMETER OF
THE STRUT END
YES
NOTHAN 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:
IT IS POSSIBLE THAT A MIXTURE OF01
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
6
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### Page 38

@A340
SERVICE BULLETIN
**CONF ALL
 HIGH FREQUENCY EDDY CURRENT
INSPECTION OF THE STRUT ENDS
FOR CRACKS
DO A 
NOON AT LEAST ONE 
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:
NEW STRUT DIAMETER    43.0mm (1.69in.) TAC02
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
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 39

@A340
SERVICE BULLETIN
**CONF ALL
 HIGH FREQUENCY EDDY CURRENT
INSPECTION OF THE STRUT ENDS
FOR CRACKS
DO A 
NOON AT LEAST ONE 
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:
NEW STRUT DIAMETER    43.0mm (1.69in.) TAC02
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
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 40

@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
ENSURE THAT THERE IS NO CONTACT02
BETWEEN THE CLAMPS, ITEM (1) AND THE NUT
CYLINDRICAL AREA
01
ENSURE THAT THERE IS NO CONTACT01
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
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 41

@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
6
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### Page 42

@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
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 43

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

### Page 44

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

### Page 45

@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
YES NOFINDINGS:
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
6
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### Page 46

@A340
SERVICE BULLETIN
Appendix 01 - Inspection Report
**CONF ALL
INSPECTION REPORT
STRUT
NUMBER
1
2
3
4
DIAMETER ENDPOS. CRACKQUANTITY LENGTHCRACK 1 LENGTHCRACK 2 LENGTHCRACK 3 LENGTHCRACK 4 LENGTHCRACK 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
6
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### Page 47

@A340
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 concer ned (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
F A X :( + 3 3 )56 19 32 80 6
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
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 48

@A340
SERVICE BULLETIN
QUALITY PERCEPTION FORM
Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data
that you provide us will be used to analyse areas of difficulties and to take corrective action to further
improve the quality of our Service Bulletins.
We thank you for the time you have taken in completing this form.
(Please rate on a scale of 1 to 4, with 4 being the highest score)
- Quality rating of this SB 4321
- Quality rating of the Accomplishment Instructions 4321
- Quality rating of the Illustrations 4321
- Is this SB easy to understand ? Y/N
If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a
short description of the issue.
Planning Material Instructions
X Effectivity X Kit content X Preparation
X Reason X List of Materials Operator Supplied X Mod/Inspection
X Manpower X Industry support X Test
X References X Re-identification X Close-Up
X Publication X Tooling X Illustrations
Comments:
Operator: Date:
Name/Title:
Please return this form to:
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX FRANCE
Attn : SEM4 Service Bulletins Management
F A X:( 3 3 )56 19 34 25 1
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
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

---
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