# Airbus Service Bulletin A340-25-4354

Copy: No revision named ("A340-25-4354 R00"), 78 pages: PDF https://openairdocs.org/files/sha256/d4/94/d494165b27f530517055c82381c11a5a22fd60cf49925ac22aabccb69b968b90; text https://openairdocs.org/service-documents/airbus/a340-25-4354/file/d494165b27f5.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2015-0083; AD 2015-25-09 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: A340-25-4354
- Page: https://openairdocs.org/service-documents/airbus/a340-25-4354

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

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

- [AD 2015-25-09](https://openairdocs.org/ad/2015-25-09.md), effective Jan 28, 2016: No revision named

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a340-25-4354/proposed.md).

## Text (78 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2015-0083; AD 2015-25-09 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
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.
ATA SYSTEM: 25
TITLE: EQUIPMENT/FURNISHINGS - C OCKPIT - REINFORCE INSTRUMENT
PANEL BRACKET 6 (SB ONLY).
**CONF ALL
MODIFICATIONS
MODIFICATION CLASSIFICATION
MAJOR
 203405S32617
MINOR
 None
NOTE
: As per EASA IR 21, a minor change is one that has no appreciable effect on the
mass, balance, structural strength, reliability, operational characteristics affecting the
airworthiness of the product. All other changes are major changes.
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
During flight tests carried out with an A340-600, high stress level was measured on the bracket No.6
(PN F25110128200 Pre Mod No.55128S18242 or PN F25113734200 Post Mod No.55128S18242),
which is one of the 8 parts used to attach the cockpit instrument panel to the aircraft structure.
This is linked to a coupling between the vibration levels due to the bumps of runways and introduced
through the Nose Landing Gear (NGL), and the cockpit panel.
Resulting from accelerations introduced at pilot seat location, the bracket No.6 cannot sustain the
fatigue loads of the Long Range Design Service Goal (DSG).
This Service Bulletin recommends replacing the bracket No.6 PN F25110128200 Pre Mod
No.55128S18242 or PN F25113734200 Post Mod No.55128S18242 of the Cockpit Instrument Panel by
a reinforced titanium undrilled bracket PN F25114708200.
Accomplishment of this Service Bulletin cancels the requirements of the Inspection Service Bulletin No.
A330-25-4351.
Accomplishment of this Service Bulletin will contribute to prevent the risk of having the bracket No.6
fully broken and, consequently, limit further damage on the surrounding structure.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 2

@A340
SERVICE BULLETIN
SUMMARY
GENERAL EVALUATION
EVALUATION TABLE
COMPLIANCE
 RECOMMENDED (1)
 CANCELS INSPECTION SB
 YES
POTENTIAL AD
 NO
 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 recommended to be accomplished to prevent significant operational
disruptions.
MATERIAL PRICE INFORMATION
**CONF 001
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 254354A01R01
 1
 1,630.00
 Bracket, Bolt, Nut, Rivet
**CONF 002
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 254354A02R01
 1
 1,770.00
 Bracket, Bolt, Nut, Rivet, Washer, Pin
**CONF 003
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 254354A03R01
 1
 1,770.00
 Bracket, Bolt, Nut, Rivet, Washer, Pin
**CONF 004
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 254354A04R01
 1
 1,770.00
 Bracket, Bolt, Nut, Rivet, Washer, Pin
EFFECTIVITY
**CONF ALL
This Service Bulletin is applicable to this (these) operator(s) :
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 3

@A340
SERVICE BULLETIN
SUMMARY
15R 15T 56W 58X 83V ABD ABQ 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
 None
OEB
 None
AOT
 None
SIL
 None
LINE MAINTENANCE AFFECTED
 No
LIFE LIMIT
 None
OTHER
 None
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
HARD
 NO
SOFT
 NO
OBRM
 NO
MANPOWER
**CONF 001
Task 254354-831-801-001: Modification
TOTAL MANHOURS
 9.00
ELAPSED TIME (HOURS)
 9.00
**CONF 002
Task 254354-831-801-001: Modification
TOTAL MANHOURS
 9.00
ELAPSED TIME (HOURS)
 9.00
**CONF 003
Task 254354-831-801-001: Modification
TOTAL MANHOURS
 9.00
ELAPSED TIME (HOURS)
 9.00
**CONF 004
Task 254354-831-801-001: Modification
TOTAL MANHOURS
 9.00
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 3
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 4

@A340
SERVICE BULLETIN
SUMMARY
Task 254354-831-801-001: Modification
ELAPSED TIME (HOURS)
 9.00
APPENDICES
**CONF ALL
None
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 4
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 5

@A340
SERVICE BULLETIN
SUMMARY
**CONF ALL
A
A
BRACKET No 6
F_SB_254354_5_SAAA_01_00
Figure A-FSAAA - Sheet 01
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 5
5
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SERVICE BULLETIN
SUMMARY
This Page Intentionally Left Blank
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 6
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 7

@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
ATA SYSTEM: 25
TITLE: EQUIPMENT/FURNISHINGS - C OCKPIT - REINFORCE INSTRUMENT
PANEL BRACKET 6 (SB ONLY).
MODIFICATION No.: 203405S32617
This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the
property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with
any information contained in it. It is delivered on the express condition that said document and the
information contained in it shall be treated as confidential, shall not be used for any purpose other than
that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall
not be duplicated in any manner (except for the purposes of performing the tasks described hereunder
and provided that any recipient of such document shall comply with the conditions herein), without
AIRBUS prior written consent.
1. PLANNING INFORMATION
**CONF ALL
A. EFFECTIVITY
NOTE
: This modification is applicable by Service Bulletin only.
(1) Models
340-211 340-212 340-213 340-311 340-312 340-313
(2) Effectivity by MSN
0002 0004-0006 0009 0011 0013-0014 0018-0020 0022-0029 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: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 1
5
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### Page 8

@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
15R
 0151
15T
 0009
56W
 0011 0013 0018 0019
58X
 0004
83V
 0133
ABD
 0210
ABQ
 0216 0257
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
 0048 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
 0024 0027 0028 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 0282 0554
HFY
 0117 0190 0202
I2L
 0005
IBE
 0088 0125 0134 0145 0146 0217 0221 0329 0387 0414 0459 0474
0483
IRC
 0002
IRM
 0020 0056
KAC
 0089 0090 0101 0104
LAN
 0359 0363 0429 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
QAF
 0026 0528
RJA
 0014 0022 0038 0043
S3R
 0204
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 9

@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
 0139 0149 0163 0166 0185 0236
VCV
 0031
VIR
 0114 0164 0214 0225
XAX
 0273 0278
(4) Configuration by MSN
MSN
 CONFIGURATION
0002 0004 0005 0006 0009 0011 0013 0014 0018 0019 0020
0022 0023 0024 0025 0026 0027 0028 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
001
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
002
0668 0793 0800 0835 0844
 003
0921 0938 0955
 004
(5) Configuration definition
**CONF 001
Config. 001 is valid for aircraft on which Mod. No. 45411S13604, Mod. No.
53446S18217 and Mod. No. 55128S18242 are not embodied.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 3
5
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### Page 10

@A340
SERVICE BULLETIN
**CONF 002
Config. 002 is valid for aircraft on which Mod. No. 45411S13604 is embodied and Mod.
No. 53446S18217 and Mod. No. 55128S18242 are not embodied.
**CONF 003
Config. 003 is valid for aircraft on which Mod. No. 45411S13604 and Mod. No.
53446S18217 are embodied and Mod. No. 55128S18242 is not embodied.
**CONF 004
Config. 004 is valid for aircraft on which Mod. No. 45411S13604, Mod. No.
53446S18217 and Mod. No. 55128S18242 are embodied.
(6) Material Effectivity
**CONF 001
MATERIAL
 QTY PER A/C
 SEE NOTES
Consumable CMLA01
 1
Kit 254354A01R01
 1
**CONF 002
MATERIAL
 QTY PER A/C
 SEE NOTES
Consumable CMLA01
 1
Kit 254354A02R01
 1
**CONF 003
MATERIAL
 QTY PER A/C
 SEE NOTES
Consumable CMLA01
 1
Kit 254354A03R01
 1
**CONF 004
MATERIAL
 QTY PER A/C
 SEE NOTES
Consumable CMLA01
 1
Kit 254354A04R01
 1
**CONF ALL
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
During flight tests carried out with an A340-600, high stress level was measured on the
bracket No.6 (PN F25110128200 Pre Mod No.55128S18242 or PN F25113734200 Post
Mod No.55128S18242), which is one of the 8 parts used to attach the cockpit instrument
panel to the aircraft structure.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 4
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 11

@A340
SERVICE BULLETIN
This is linked to a coupling between the vibration levels due to the bumps of runways
and introduced through the Nose Landing Gear (NGL), and the cockpit panel.
Resulting from accelerations introduced at pilot seat location, the bracket No.6 cannot
sustain the fatigue loads of the Long Range Design Service Goal (DSG).
(2) Objective/Action
This Service Bulletin recommends replacing the bracket No.6 PN F25110128200 Pre
Mod No.55128S18242 or PN F25113734200 Post Mod No.55128S18242 of the Cockpit
Instrument Panel by a reinforced titanium undrilled bracket PN F25114708200.
(3) Advantages
Accomplishment of this Service Bulletin cancels the requirements of the Inspection
Service Bulletin No. A330-25-4351.
Accomplishment of this Service Bulletin will contribute to prevent the risk of having the
bracket No.6 fully broken and, consequently, limit further damage on the surrounding
structure.
(4) Operational/Maintenance Consequences
None
D. DESCRIPTION
To accomplish this Service Bulletin it is necessary to :
**CONF 001
Task 254354-831-801-001: Modification
(1) Replace the Bracket No. 6.
(2) Install/Close Items Removed/Opened for access
**CONF 002
Task 254354-831-801-001: Modification
(1) Replace the Bracket No. 6.
(2) Install/Close Items Removed/Opened for access
**CONF 003
Task 254354-831-801-001: Modification
(1) Replace the Bracket No. 6.
(2) Install/Close Items Removed/Opened for access
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 5
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 12

@A340
SERVICE BULLETIN
**CONF 004
Task 254354-831-801-001: Modification
(1) Replace the Bracket No. 6.
(2) Install/Close Items Removed/Opened for access
**CONF ALL
E. COMPLIANCE
(1) Classification
RECOMMENDED: Service Bulletin recommended to be accomplished to prevent
significant operational disruptions.
(2) Accomplishment Timescale
Accomplishment of this Service Bulletin is recommended at the earliest opportunity
where manpower and facilities are available.
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.
**CONF 001
Task 254354-831-801-001: Modification
Get Access
 2.50
On Aircraft
Replace the Bracket No. 6.
 2.00
Install/Close Items Removed/Opened for access
 0.50
Tests
 1.50
Close-Up
 2.50
TOTAL MANHOURS
 9.00
ELAPSED TIME (HOURS)
 9.00
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 6
5
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### Page 13

@A340
SERVICE BULLETIN
**CONF 002
Task 254354-831-801-001: Modification
Get Access
 2.50
On Aircraft
Replace the Bracket No. 6.
 2.00
Install/Close Items Removed/Opened for access
 0.50
Tests
 1.50
Close-Up
 2.50
TOTAL MANHOURS
 9.00
ELAPSED TIME (HOURS)
 9.00
**CONF 003
Task 254354-831-801-001: Modification
Get Access
 2.50
On Aircraft
Replace the Bracket No. 6.
 2
Install/Close Items Removed/Opened for access
 0.50
Tests
 1.50
Close-Up
 2.50
TOTAL MANHOURS
 9.00
ELAPSED TIME (HOURS)
 9.00
**CONF 004
Task 254354-831-801-001: Modification
Get Access
 2.50
On Aircraft
Replace the Bracket No. 6.
 2.00
Install/Close Items Removed/Opened for access
 0.50
Tests
 1.50
Close-Up
 2.50
TOTAL MANHOURS
 9.00
ELAPSED TIME (HOURS)
 9.00
**CONF ALL
H. WEIGHT AND BALANCE
Not Changed
I. ELECTRICAL LOAD DATA
Not Changed
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 7
5
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SERVICE BULLETIN
J. REFERENCES
**CONF 001
Aircraft Maintenance Manual (AMM)
 06-20-00 06-41-52 12-34-24
20-21-11 21-26-00 22-96-00
22-97-00 24-41-00 25-11-51
31-50-00 31-60-00 31-63-22
33-12-13 33-13-00 33-14-00
52-10-00
ATA Common Support Data Dictionary (CSDD),
Chapter 2
Elec. Std. Practices Manual (ESPM)
 20-52-20 20-55-00
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-24-00 51-42-00 51-43-00
51-44-00 51-75-12
**CONF 002
Aircraft Maintenance Manual (AMM)
 06-20-00 06-41-52 12-34-24
20-21-11 21-26-00 22-96-00
22-97-00 24-41-00 25-11-51
31-50-00 31-60-00 31-63-22
33-12-13 33-13-00 33-14-00
52-10-00
ATA Common Support Data Dictionary (CSDD),
Chapter 2
Elec. Std. Practices Manual (ESPM)
 20-52-20 20-55-00
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-24-00 51-42-00 51-43-00
51-44-00 51-75-12
**CONF 003
Aircraft Maintenance Manual (AMM)
 06-20-00 06-41-52 12-34-24
20-21-11 21-26-00 22-96-00
22-97-00 24-41-00 25-11-51
31-50-00 31-60-00 31-63-22
33-12-13 33-13-00 33-14-00
52-10-00
ATA Common Support Data Dictionary (CSDD),
Chapter 2
Elec. Std. Practices Manual (ESPM)
 20-52-20 20-55-00
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-24-00 51-42-00 51-43-00
51-44-00 51-75-12
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 8
5
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SERVICE BULLETIN
**CONF 004
Aircraft Maintenance Manual (AMM)
 06-20-00 06-41-52 12-34-24
20-21-11 21-26-00 22-96-00
22-97-00 24-41-00 25-11-51
31-50-00 31-60-00 31-63-22
33-12-13 33-13-00 33-14-00
52-10-00
ATA Common Support Data Dictionary (CSDD),
Chapter 2
Elec. Std. Practices Manual (ESPM)
 20-52-20 20-55-00
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-24-00 51-42-00 51-43-00
51-44-00 51-75-12
**CONF ALL
K. PUBLICATION AFFECTED
Illustrated Parts Catalog (IPC)
 25-14-01
L. INTERCHANGEABILITY/MIXABILITY
**CONF 001
DESCRIPTION
 OLD PART N˚
 NEW PART N˚
 INT
 MIXABILITY
 SEE
NOTES
Bracket
 F2511012820000
 F2511470820095
 03
 Not
Applicable
Bracket
 F2511012820095
 F2511470820095
 03
 Not
Applicable
NOTE
: For definitions of interchangeability codes in column INT., refer to ATA
Common Support Data Dictionary (CSDD), Chapter 2.
**CONF 002
DESCRIPTION
 OLD PART N˚
 NEW PART N˚
 INT
 MIXABILITY
 SEE
NOTES
Bracket
 F2511012820000
 F2511470820095
 03
 Not
Applicable
Bracket
 F2511012820095
 F2511470820095
 03
 Not
Applicable
NOTE
: For definitions of interchangeability codes in column INT., refer to ATA
Common Support Data Dictionary (CSDD), Chapter 2.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 9
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SERVICE BULLETIN
**CONF 003
DESCRIPTION
 OLD PART N˚
 NEW PART N˚
 INT
 MIXABILITY
 SEE
NOTES
Bracket
 F2511012820000
 F2511470820095
 03
 Not
Applicable
Bracket
 F2511012820095
 F2511470820095
 03
 Not
Applicable
NOTE
: For definitions of interchangeability codes in column INT., refer to ATA
Common Support Data Dictionary (CSDD), Chapter 2.
**CONF 004
DESCRIPTION
 OLD PART N˚
 NEW PART N˚
 INT
 MIXABILITY
 SEE
NOTES
Bracket
 F2511373420000
 F2511470820095
 03
 Not
Applicable
Bracket
 F2511373420095
 F2511470820095
 03
 Not
Applicable
NOTE
: For definitions of interchangeability codes in column INT., refer to ATA
Common Support Data Dictionary (CSDD), Chapter 2.
**CONF ALL
M. SPARES
None
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 10
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SERVICE BULLETIN
2. MATERIAL INFORMATION
**CONF ALL
A. MATERIAL - PRICE AND AVAILABILITY
(1) Procurement Addresses
Customers with aircraft shown in the effectivity of this Service Bulletin should send a
purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is :
Kit 254354A01R01
Kit 254354A02R01
Kit 254354A03R01
Kit 254354A04R01
AIRBUS Material, Logistics and Suppliers
Weg beim Jaeger 150
D-22335 HAMBURG
GERMANY
For ordering by internet :
http://spares.airbus.com
For ordering by fax : +49 40 50 76 2590
For ordering by E-mail :
airbus.kit@airbus.com
(2) Price and Availability
The Kit availability given above is the standard lead time from the date of your purchase
order. If items are required before this time, please include a retrofit planning schedule
with your order so that we can try to comply with your requirements.
The sales terms (costs and availability) are estimated in relation to economic conditions.
The latest valid price and lead time for ordering purposes shall be obtained through the
AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.
Kit 254354A01R01
Cost
 1,630.00 USD
Availability
 90 calendar days from receipt of order
Kit 254354A02R01
Cost
 1,770.00 USD
Availability
 90 calendar days from receipt of order
Kit 254354A03R01
Cost
 1,770.00 USD
Availability
 90 calendar days from receipt of order
Kit 254354A04R01
Cost
 1,770.00 USD
Availability
 90 calendar days from receipt of order
B. INDUSTRY SUPPORT INFORMATION
For aircraft under warranty at Jan 01/12, AIRBUS will share the costs of accomplishment of
this Service Bulletin by providing the kits at no charge for orders placed before Jun 30/16.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 11
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SERVICE BULLETIN
For aircraft under warranty at Jan 01/12 and for the accomplishment of this Service Bulletin
before Jun 30/16, AIRBUS will credit the manhours indicated in this Service Bulletin at
the agreed in-house warranty labor rate for claims received not later than 90 days after
completion of the last affected aircraft of your fleet.
C. LIST OF COMPONENTS
Kit 254354A01R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
7
 NAS6604-10
 1
 BOLT
8
 NAS1726-4E
 1
 NUT
11
 ASNA2050DCJ3215
 3
 RIVET
25
 F2511470820095
 1
 BRACKET
 (16)
 F2511012820000
 03
(16)
 F2511012820095
 03
26
 ABS0114V3-5
 4
 BOLT
27
 NSA5050-3
 4
 NUT
NOTE
: For definitions of interchangeability codes in column INT., refer to ATA
Common Support Data Dictionary (CSDD), Chapter 2.
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.
Kit 254354A02R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
11
 ASNA2050DCJ3215
 3
 RIVET
17
 NSA5042-04-160
 1
 BOLT
18
 NSA5060-3
 1
 NUT
19
 NSA5325-3
 1
 WASHER
20
 MS24665-134
 1
 PIN
25
 F2511470820095
 1
 BRACKET
 (16)
 F2511012820000
 03
(16)
 F2511012820095
 03
26
 ABS0114V3-5
 4
 BOLT
27
 NSA5050-3
 4
 NUT
NOTE
: For definitions of interchangeability codes in column INT., refer to ATA
Common Support Data Dictionary (CSDD), Chapter 2.
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.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 12
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SERVICE BULLETIN
Kit 254354A03R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
11
 ASNA2050DCJ3215
 3
 RIVET
17
 NSA5042-04-160
 1
 BOLT
18
 NSA5060-3
 1
 NUT
19
 NSA5325-3
 1
 WASHER
21
 MS24665-71
 1
 PIN
25
 F2511470820095
 1
 BRACKET
 (16)
 F2511012820000
 03
(16)
 F2511012820095
 03
26
 ABS0114V3-5
 4
 BOLT
27
 NSA5050-3
 4
 NUT
NOTE
: For definitions of interchangeability codes in column INT., refer to ATA
Common Support Data Dictionary (CSDD), Chapter 2.
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.
Kit 254354A04R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
11
 ASNA2050DCJ3215
 3
 RIVET
17
 NSA5042-04-160
 1
 BOLT
18
 NSA5060-3
 1
 NUT
19
 NSA5325-3
 1
 WASHER
21
 MS24665-71
 1
 PIN
25
 F2511470820095
 1
 BRACKET
 (6)
 F2511373420000
 03
(6)
 F2511373420095
 03
26
 ABS0114V3-5
 4
 BOLT
27
 NSA5050-3
 4
 NUT
NOTE
: For definitions of interchangeability codes in column INT., refer to ATA
Common Support Data Dictionary (CSDD), Chapter 2.
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.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 13
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SERVICE BULLETIN
D. LIST OF MATERIALS - OPERATOR SUPPLIED
(1) Consumable Materials
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
Synthetic Ester base Grease
 03HBD9
 As required
(2) Components
None
(3) Equipment
None
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
F. TOOLING
None
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 14
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3. ACCOMPLISHMENT INSTRUCTIONS
Task 254354-831-801-001 - Modification
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
: 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 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.
Task Associated Data
**CONF 001
Zone
212
Manpower
TOTAL MANHOURS
 9.00
ELAPSED TIME (HOURS)
 9.00
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 15
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SERVICE BULLETIN
**CONF 002
Zone
212
Manpower
TOTAL MANHOURS
 9.00
ELAPSED TIME (HOURS)
 9.00
**CONF 003
Zone
212
Manpower
TOTAL MANHOURS
 9.00
ELAPSED TIME (HOURS)
 9.00
**CONF 004
Zone
212
Manpower
TOTAL MANHOURS
 9.00
ELAPSED TIME (HOURS)
 9.00
**CONF ALL
A. GENERAL
**CONF 001
(1) Subtask 254354-910-001-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-20-00, Page Block 001
06-41-52, Page Block 001
Task 20-21-11-911-801
Structural Repair Manual (SRM)
 51-24-00
51-42-00
51-43-00
51-44-00
51-75-12
(a) For the specification of materials (Mat. No.) given in the Service Bulletin, refer to
the Consumable Materials List (CML).
(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.
(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 16
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(d) Remove and install fasteners in accordance with SRM 51-42-00.
(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.
(f) Obtain fasteners hole diameters and drill data in accordance with SRM 51-44-00.
(g) Cut the rivets to the necessary length.
(h) Renew the protective finish in accordance with SRM 51-75-12.
(i) Apply sealant in accordance with SRM 51-24-00.
(j) To torque tighten the standard threaded fasteners, refer to AMM Task
20-21-11-911-801.
(k) If the length of any fastener specified in this Service Bulletin does not meet
installation standards given in SRM Chapter 51, then a fastener of the same
specification, or an approved substitute, with a length which meets the installation
standards given in SRM Chapter 51 may be used. In addition, washers may be
installed for fastener grip length in accordance with SRM Chapter 51.
(2) Subtask 254354-839-001-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in applicable aircraft records that you have done all the work given in this Service
Bulletin.
**CONF 002
(1) Subtask 254354-910-001-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-20-00, Page Block 001
06-41-52, Page Block 001
Task 20-21-11-911-801
Structural Repair Manual (SRM)
 51-24-00
51-42-00
51-43-00
51-44-00
51-75-12
(a) For the specification of materials (Mat. No.) given in the Service Bulletin, refer to
the Consumable Materials List (CML).
(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.
(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 17
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(d) Remove and install fasteners in accordance with SRM 51-42-00.
(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.
(f) Obtain fasteners hole diameters and drill data in accordance with SRM 51-44-00.
(g) Cut the rivets to the necessary length.
(h) Renew the protective finish in accordance with SRM 51-75-12.
(i) Apply sealant in accordance with SRM 51-24-00.
(j) To torque tighten the standard threaded fasteners, refer to AMM Task
20-21-11-911-801.
(k) If the length of any fastener specified in this Service Bulletin does not meet
installation standards given in SRM Chapter 51, then a fastener of the same
specification, or an approved substitute, with a length which meets the installation
standards given in SRM Chapter 51 may be used. In addition, washers may be
installed for fastener grip length in accordance with SRM Chapter 51.
(2) Subtask 254354-839-001-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in applicable aircraft records that you have done all the work given in this Service
Bulletin.
**CONF 003
(1) Subtask 254354-910-001-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-20-00, Page Block 001
06-41-52, Page Block 001
Task 20-21-11-911-801
Structural Repair Manual (SRM)
 51-24-00
51-42-00
51-43-00
51-44-00
51-75-12
(a) For the specification of materials (Mat. No.) given in the Service Bulletin, refer to
the Consumable Materials List (CML).
(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.
(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 18
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(d) Remove and install fasteners in accordance with SRM 51-42-00.
(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.
(f) Obtain fasteners hole diameters and drill data in accordance with SRM 51-44-00.
(g) Cut the rivets to the necessary length.
(h) Renew the protective finish in accordance with SRM 51-75-12.
(i) Apply sealant in accordance with SRM 51-24-00.
(j) To torque tighten the standard threaded fasteners, refer to AMM Task
20-21-11-911-801.
(k) If the length of any fastener specified in this Service Bulletin does not meet
installation standards given in SRM Chapter 51, then a fastener of the same
specification, or an approved substitute, with a length which meets the installation
standards given in SRM Chapter 51 may be used. In addition, washers may be
installed for fastener grip length in accordance with SRM Chapter 51.
(2) Subtask 254354-839-001-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in applicable aircraft records that you have done all the work given in this Service
Bulletin.
**CONF 004
(1) Subtask 254354-910-001-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-20-00, Page Block 001
06-41-52, Page Block 001
Task 20-21-11-911-801
Structural Repair Manual (SRM)
 51-24-00
51-42-00
51-43-00
51-44-00
51-75-12
(a) For the specification of materials (Mat. No.) given in the Service Bulletin, refer to
the Consumable Materials List (CML).
(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.
(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 19
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SERVICE BULLETIN
(d) Remove and install fasteners in accordance with SRM 51-42-00.
(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.
(f) Obtain fasteners hole diameters and drill data in accordance with SRM 51-44-00.
(g) Cut the rivets to the necessary length.
(h) Renew the protective finish in accordance with SRM 51-75-12.
(i) Apply sealant in accordance with SRM 51-24-00.
(j) To torque tighten the standard threaded fasteners, refer to AMM Task
20-21-11-911-801.
(k) If the length of any fastener specified in this Service Bulletin does not meet
installation standards given in SRM Chapter 51, then a fastener of the same
specification, or an approved substitute, with a length which meets the installation
standards given in SRM Chapter 51 may be used. In addition, washers may be
installed for fastener grip length in accordance with SRM Chapter 51.
(2) Subtask 254354-839-001-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in applicable aircraft records that you have done all the work given in this Service
Bulletin.
**CONF ALL
B. PREPARATION
**CONF 001
(1) Subtask 254354-941-001-001 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 12-34-24-860-802
Task 25-11-51-000-801
Task 31-63-22-000-801
Task 33-12-13-000-801
Task 52-10-00-010-801
(a) The following items shall be considered as the basic aircraft configuration before
you start a maintenance task :
- Aircraft on the ground resting on landing gear (the ground safety locks and the
wheel chocks are in position on the landing gear).
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 20
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- Engine shut down, thrust revers closed and locked.
- Aircraft in clean configuration.
- Parking brake applied.
- Aircraft electrical network de-energized.
- Hydraulic systems depressurized.
- Access to the cockpit and cabin is available.
- All circuit breakers are in closed position.
- All controls in NORM, AUTO or OFF position.
(b) Make sure that the aircraft is electrically grounded, refer to AMM Task
12-34-24-860-802.
(c) Put the access platform in position at door 831 or 841.
(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.
(e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task
25-11-51-000-801.
(f) Do the Job Set-up procedure as specified in the removal of the Display Unit
(DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.
(g) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are
released :
- BAT 1, BAT 2, APU BAT,
- GEN 1, (2), APU GEN,
- EXT A (B).
(h) If necessary, remove the Light Unit (LU) (14LE), refer to AMM Task
33-12-13-000-801.
(i) Open, safety and tag this (these) circuit breaker(s) :
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
742
 701PP
 10PB1
 72S
742
 702PP
 10PB2
 71S
(j) Make sure that there (is) are warning notice(s) in the cockpit to tell persons not to
operate the pushbutton switches on the overhead panel :
- 211VU (EMER ELEC PWR)
- 235VU (ELEC)
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 21
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(k) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to
start the APU.
(l) Make sure that the external connector(s) is (are) not connected to the aircraft
receptacle(s) EXT PWR A (B).
(m) Make sure that there is a warning notice at the access door 121EL to tell persons
not to connect the external power connector(s).
(2) Subtask 254354-010-001-001 - Remove/Open for Access
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 31-63-22-000-801
Fig. A-FBCAA
Removal/Installation of the protection
plate and cover assembly panels
Sheet 01
Sheet 02
(a) Remove the protection plate.
Refer to Fig. A-FBCAA Sheet 01
 .
3 Stud Item (1) Retain
3 Washer Item (2) Retain
1 Panel Item (3) Retain
(b) Remove the cover assembly panel.
Refer to Fig. A-FBCAA Sheet 02
 .
3 Stud Item (5) Retain
1 Panel Item (4) Retain
(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.
**CONF 002
(1) Subtask 254354-941-001-001 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 22
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References
Aircraft Maintenance Manual (AMM)
 Task 12-34-24-860-802
Task 25-11-51-000-801
Task 31-63-22-000-801
Task 33-12-13-000-801
Task 52-10-00-010-801
(a) The following items shall be considered as the basic aircraft configuration before
you start a maintenance task :
- Aircraft on the ground resting on landing gear (the ground safety locks and the
wheel chocks are in position on the landing gear).
- Engine shut down, thrust revers closed and locked.
- Aircraft in clean configuration.
- Parking brake applied.
- Aircraft electrical network de-energized.
- Hydraulic systems depressurized.
- Access to the cockpit and cabin is available.
- All circuit breakers are in closed position.
- All controls in NORM, AUTO or OFF position.
(b) Make sure that the aircraft is electrically grounded, refer to AMM Task
12-34-24-860-802.
(c) Put the access platform in position at door 831 or 841.
(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.
(e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task
25-11-51-000-801.
(f) Do the Job Set-up procedure as specified in the removal of the Display Unit
(DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.
(g) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are
released :
- BAT 1, BAT 2, APU BAT,
- GEN 1, (2), APU GEN,
- EXT A (B).
(h) If necessary, remove the Light Unit (LU) (14LE), refer to AMM Task
33-12-13-000-801.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 23
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(i) Open, safety and tag this (these) circuit breaker(s) :
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
742
 701PP
 10PB1
 72S
742
 702PP
 10PB2
 71S
(j) Make sure that there (is) are warning notice(s) in the cockpit to tell persons not to
operate the pushbutton switches on the overhead panel :
- 211VU (EMER ELEC PWR)
- 235VU (ELEC)
(k) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to
start the APU.
(l) Make sure that the external connector(s) is (are) not connected to the aircraft
receptacle(s) EXT PWR A (B).
(m) Make sure that there is a warning notice at the access door 121EL to tell persons
not to connect the external power connector(s).
(2) Subtask 254354-010-001-001 - Remove/Open for Access
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 31-63-22-000-801
Fig. A-FBCAA
Removal/Installation of the protection
plate and cover assembly panels
Sheet 01
Sheet 02
(a) Remove the protection plate.
Refer to Fig. A-FBCAA Sheet 01
 .
3 Stud Item (1) Retain
3 Washer Item (2) Retain
1 Panel Item (3) Retain
(b) Remove the cover assembly panel.
Refer to Fig. A-FBCAA Sheet 02
 .
3 Stud Item (5) Retain
1 Panel Item (4) Retain
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 24
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(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.
**CONF 003
(1) Subtask 254354-941-001-001 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 12-34-24-860-802
Task 25-11-51-000-801
Task 31-63-22-000-801
Task 33-12-13-000-801
Task 52-10-00-010-801
(a) The following items shall be considered as the basic aircraft configuration before
you start a maintenance task :
- Aircraft on the ground resting on landing gear (the ground safety locks and the
wheel chocks are in position on the landing gear).
- Engine shut down, thrust revers closed and locked.
- Aircraft in clean configuration.
- Parking brake applied.
- Aircraft electrical network de-energized.
- Hydraulic systems depressurized.
- Access to the cockpit and cabin is available.
- All circuit breakers are in closed position.
- All controls in NORM, AUTO or OFF position.
(b) Make sure that the aircraft is electrically grounded, refer to AMM Task
12-34-24-860-802.
(c) Put the access platform in position at door 831 or 841.
(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.
(e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task
25-11-51-000-801.
(f) Do the Job Set-up procedure as specified in the removal of the Display Unit
(DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 25
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(g) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are
released :
- BAT 1, BAT 2, APU BAT,
- GEN 1, (2), APU GEN,
- EXT A (B).
(h) If necessary, remove the Light Unit (LU) (14LE), refer to AMM Task
33-12-13-000-801.
(i) Open, safety and tag this (these) circuit breaker(s) :
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
742
 701PP
 10PB1
 72S
742
 702PP
 10PB2
 71S
(j) Make sure that there (is) are warning notice(s) in the cockpit to tell persons not to
operate the pushbutton switches on the overhead panel :
- 211VU (EMER ELEC PWR)
- 235VU (ELEC)
(k) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to
start the APU.
(l) Make sure that the external connector(s) is (are) not connected to the aircraft
receptacle(s) EXT PWR A (B).
(m) Make sure that there is a warning notice at the access door 121EL to tell persons
not to connect the external power connector(s).
(2) Subtask 254354-010-001-001 - Remove/Open for Access
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 31-63-22-000-801
Fig. A-FBCAA
Removal/Installation of the protection
plate and cover assembly panels
Sheet 01
Sheet 02
(a) Remove the protection plate.
Refer to Fig. A-FBCAA Sheet 01
 .
3 Stud Item (1) Retain
3 Washer Item (2) Retain
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 26
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SERVICE BULLETIN
1 Panel Item (3) Retain
(b) Remove the cover assembly panel.
Refer to Fig. A-FBCAA Sheet 02
 .
3 Stud Item (5) Retain
1 Panel Item (4) Retain
(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.
**CONF 004
(1) Subtask 254354-941-001-001 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 12-34-24-860-802
Task 25-11-51-000-801
Task 31-63-22-000-801
Task 33-12-13-000-801
Task 52-10-00-010-801
(a) The following items shall be considered as the basic aircraft configuration before
you start a maintenance task :
- Aircraft on the ground resting on landing gear (the ground safety locks and the
wheel chocks are in position on the landing gear).
- Engine shut down, thrust revers closed and locked.
- Aircraft in clean configuration.
- Parking brake applied.
- Aircraft electrical network de-energized.
- Hydraulic systems depressurized.
- Access to the cockpit and cabin is available.
- All circuit breakers are in closed position.
- All controls in NORM, AUTO or OFF position.
(b) Make sure that the aircraft is electrically grounded, refer to AMM Task
12-34-24-860-802.
(c) Put the access platform in position at door 831 or 841.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 27
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(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.
(e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task
25-11-51-000-801.
(f) Do the Job Set-up procedure as specified in the removal of the Display Unit
(DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.
(g) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are
released :
- BAT 1, BAT 2, APU BAT,
- GEN 1, (2), APU GEN,
- EXT A (B).
(h) If necessary, remove the Light Unit (LU) (14LE), refer to AMM Task
33-12-13-000-801.
(i) Open, safety and tag this (these) circuit breaker(s) :
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
742
 701PP
 10PB1
 72S
742
 702PP
 10PB2
 71S
(j) Make sure that there (is) are warning notice(s) in the cockpit to tell persons not to
operate the pushbutton switches on the overhead panel :
- 211VU (EMER ELEC PWR)
- 235VU (ELEC)
(k) Make sure that there is (are) warning notice(s) in the cockpit to tell persons not to
start the APU.
(l) Make sure that the external connector(s) is (are) not connected to the aircraft
receptacle(s) EXT PWR A (B).
(m) Make sure that there is a warning notice at the access door 121EL to tell persons
not to connect the external power connector(s).
(2) Subtask 254354-010-001-001 - Remove/Open for Access
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 31-63-22-000-801
Fig. A-FBCAA
Removal/Installation of the protection
plate and cover assembly panels
Sheet 01
Sheet 02
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 28
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SERVICE BULLETIN
(a) Remove the protection plate.
Refer to Fig. A-FBCAA Sheet 01
 .
3 Stud Item (1) Retain
3 Washer Item (2) Retain
1 Panel Item (3) Retain
(b) Remove the cover assembly panel.
Refer to Fig. A-FBCAA Sheet 02
 .
3 Stud Item (5) Retain
1 Panel Item (4) Retain
(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.
**CONF ALL
C. PROCEDURE
**CONF 001
(1) Subtask 254354-911-001-001 - Replace the Bracket No. 6.
Work Zones and Access Panels
Zone
 Access/Work location
212
Manpower Resources
Manhours
 2.00
Minimum number of person
 1
Subtask elapsed time
 2.00
Skills
 AIRFRAME
Material necessary to do the job
Kit 254354A01R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
7
 NAS6604-10
 1
 BOLT
8
 NAS1726-4E
 1
 NUT
11
 ASNA2050DCJ3215
 3
 RIVET
25
 F2511470820095
 1
 BRACKET
26
 ABS0114V3-5
 4
 BOLT
27
 NSA5050-3
 4
 NUT
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 29
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Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Synthetic Ester base
Grease
03HBD9
 As required
References
Structural Repair Manual (SRM)
 51-42-00
51-44-00
Fig. A-FBBAA
Replacement of the bracket No. 6
Sheet 01
Sheet 02
Sheet 03
Sheet 04
(a) Remove the bracket No. 6.
Refer to Fig. A-FBBAA Sheet 01
 and Fig. A-FBBAA Sheet 02
 .
In accordance with SRM 51-42-00.
1
 Remove:
1 Screw Item (7) Discard
1 Nut Item (8) Discard
2
 Remove the rivets:
- Remove the head of the four rivets.
- Drill four holes through the cockpit main panel to remove the four rivets
and obtain a diameter comprised between 4.788 mm and 4.813 mm
(0.188 in. and 0.189 in.).
2 Rivet Item (12) Discard
2 Rivet Item (14) Discard
3
 Remove the bracket:
1 Bracket F2511012820000 Item (16) Discard
or
1 Bracket F2511012820095 Item (16) Discard
(b) Install the new bracket.
Refer to Fig. A-FBBAA Sheet 03
 and Fig. A-FBBAA Sheet 04
 .
In accordance with SRM 51-42-00 and SRM 51-44-00.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 30
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1
 Temporarily put the bracket item 25 on the RH side on the upper bracket on
the new bracket.
a
 If necessary, remove:
3 Rivet Item (11) Discard
b
 Mark the position of the hole of the upper bracket on the new bracket.
c
 If removed, install:
3 Rivet ASNA2050DCJ3215 Item 11
2
 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7
mm (0.256 and 0.264 in.).
3
 Put in position the new bracket item 25 with the bolt item 7.
Install:
1 Bracket F2511470820095 Item 25
1 Bolt NAS6604-10 Item 7
NOTE
: Install the bolt item 7 with:
Synthetic Ester
base Grease
03HBD9 As required
4
 Measure the clearance between the new bracket item 25 and the upper
bracket as shown in Fig. A-FBBAA Sheet 04
 .
a
 Check that the minimum clearance are 0.35 mm (0.014 in.) at LHS and
0.65 mm (0.026 in.) at RHS.
5
 Match and drill the four holes of the cockpit main instrument panel on the new
bracket item 25 to a diameter comprised between 4.788 mm (0.189 in.) and
4.813 mm (0.190 in.) as shown on Figure Fig. A-FBBAA Sheet 03
 .
6
 Install:
4 Bolt ABS0114V3-5 Item 26
4 Nut NSA5050-3 Item 27
7
 Install the nut item 8:
1 Nut NAS1726-4E Item 8
NOTE
: Torque the nut item 8 to a value between 0.28 and 0.37
m.daN (24.782 and 32.748 lbf.in.).
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 31
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SERVICE BULLETIN
(2) Subtask 254354-410-001-001 - Install/Close Items Removed/Opened for access
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 31-63-22-400-801
Fig. A-FBCAA
Removal/Installation of the protection
plate and cover assembly panels
Sheet 01
Sheet 02
(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.
(b) Install the cover assembly plate.
Refer to Fig. A-FBCAA Sheet 02
 .
3 Stud Item (5) Retained at
removal
1 Panel Item (4) Retained at
removal
(c) Install the protection plate.
Refer to Fig. A-FBCAA Sheet 01
 .
3 Stud Item (1) Retained at
removal
3 Washer Item (2) Retained at
removal
1 Panel Item (3) Retained at
removal
**CONF 002
(1) Subtask 254354-911-001-002 - Replace the Bracket No. 6.
Work Zones and Access Panels
Zone
 Access/Work location
212
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 32
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SERVICE BULLETIN
Manpower Resources
Manhours
 2.00
Minimum number of person
 1
Subtask elapsed time
 2.00
Skills
 AIRFRAME
Material necessary to do the job
Kit 254354A02R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
11
 ASNA2050DCJ3215
 3
 RIVET
17
 NSA5042-04-160
 1
 BOLT
18
 NSA5060-3
 1
 NUT
19
 NSA5325-3
 1
 WASHER
20
 MS24665-134
 1
 PIN
25
 F2511470820095
 1
 BRACKET
26
 ABS0114V3-5
 4
 BOLT
27
 NSA5050-3
 4
 NUT
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Synthetic Ester base
Grease
03HBD9
References
Structural Repair Manual (SRM)
 51-42-00
51-44-00
Fig. A-FBBAC
Replacement of the bracket No. 6
Sheet 01
Sheet 02
Sheet 03
Sheet 04
(a) Remove the bracket No. 6.
Refer to Fig. A-FBBAC Sheet 01
 and Fig. A-FBBAC Sheet 02
 .
In accordance with SRM 51-42-00.
1
 Remove:
1 Bolt Item (17) Discard
1 Nut Item (18) Discard
1 Whasher Item (19) Discard
1 Pin Item (20) Discard
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 33
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SERVICE BULLETIN
2
 Remove the rivets:
- Remove the head of the four rivets.
- Drill four holes through the cockpit main panel to remove the four rivets
and obtain a diameter comprised between 4.788 mm and 4.813 mm
(0.188 in. and 0.189 in.).
2 Rivet Item (12) Discard
2 Rivet Item (14) Discard
3
 Remove the bracket:
1 Bracket F2511012820000 Item (16) Discard
or
1 Bracket F2511012820095 Item (16) Discard
(b) Install the new bracket.
Refer to Fig. A-FBBAC Sheet 03
 and Fig. A-FBBAC Sheet 04
 .
In accordance with SRM 51-42-00 and SRM 51-44-00.
1
 Temporarily put the bracket item 25 on the RH side of the upper bracket.
a
 If necessary, remove:
3 Rivet Item (11) Discard
b
 Mark the position of the hole of the upper bracket on the new bracket.
c
 If removed, install:
3 Rivet ASNA2050DCJ3215 Item 11
2
 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7
mm (0.256 and 0.264 in.).
3
 Put in the position the new bracket item 25 with the bolt item 17.
1 Bracket F2511470820095 Item 25
1 Bolt NSA5042-04-160 Item 17
NOTE
: Install the bolt item 17 with:
Synthetic Ester
base Grease
03HBD9 As required
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 34
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SERVICE BULLETIN
4
 Measure the clearance between the new bracket item 25 and the upper
bracket as show in Fig. A-FBBAC Sheet 04
 .
a
 Check that the minimum clearances are 0.35 mm (0.014 in.) at LHS and
0.65 mm (0.026 in.) at RHS.
5
 Match and drill the four holes of the cockpit main instrument panel on the new
bracket item 25 to a diameter comprised between 4.788 mm (0.189 in.) and
4.813 mm (0.190 in.) as shown on Figure Fig. A-FBBAC Sheet 03
 .
6
 Install:
4 Bolt ABS0114V3-5 Item 26
4 Nut NSA5050-3 Item 27
7
 Install the nut item 18:
1 Nut NSA5060-3 Item 18
1 Washer NSA5325-3 Item 19
1 Pin-cotter MS24665-134 Item 20
NOTE
: Torque the nut item 18 to a value between 0.28 and 0.37
m.daN (24.782 and 32.748 lbf.in.).
(2) Subtask 254354-410-001-002 - Install/Close Items Removed/Opened for access
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 31-63-22-400-801
Fig. A-FBCAA
Removal/Installation of the protection
plate and cover assembly panels
Sheet 01
Sheet 02
(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.
(b) Install the cover assembly plate.
Refer to Fig. A-FBCAA Sheet 02
 .
3 Stud Item (5) Retained at
removal
1 Panel Item (4) Retained at
removal
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 35
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SERVICE BULLETIN
(c) Install the protection plate.
Refer to Fig. A-FBCAA Sheet 01
 .
3 Stud Item (1) Retained at
removal
3 Washer Item (2) Retained at
removal
1 Panel Item (3) Retained at
removal
**CONF 003
(1) Subtask 254354-911-001-003 - Replace the Bracket No. 6.
Work Zones and Access Panels
Zone
 Access/Work location
212
Manpower Resources
Manhours
 2
Minimum number of person
 1
Subtask elapsed time
 2
Skills
 AIRFRAME
Material necessary to do the job
Kit 254354A03R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
11
 ASNA2050DCJ3215
 3
 RIVET
17
 NSA5042-04-160
 1
 BOLT
18
 NSA5060-3
 1
 NUT
19
 NSA5325-3
 1
 WASHER
21
 MS24665-71
 1
 PIN
25
 F2511470820095
 1
 BRACKET
26
 ABS0114V3-5
 4
 BOLT
27
 NSA5050-3
 4
 NUT
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Synthetic Ester base
Grease
03HBD9
 As required
References
Structural Repair Manual (SRM)
 51-42-00
51-44-00
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 36
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References
Fig. A-FBBAD
Replacement of the bracket No. 6
Sheet 01
Sheet 02
Sheet 03
Sheet 04
(a) Remove the bracket No. 6.
Refer to Fig. A-FBBAD Sheet 01
 and Fig. A-FBBAD Sheet 02
 .
In accordance with SRM 51-42-00.
1
 Remove :
1 Bolt Item (17) Discard
1 Nut Item (18) Discard
1 Washer Item (19) Discard
1 Pin Item (21) Discard
2
 Remove the rivets:
- Remove the head of the four rivets.
- Drill four holes through the cockpit main panel to remove the four rivets
and obtain a diameter comprised between 4.788 mm and 4.813 mm
(0.188 in. and 0.189 in.).
2 Rivet Item (12) Discard
2 Rivet Item (14) Discard
3
 Remove the bracket:
1 Bracket F2511012820000 Item (16) Discard
or
1 Bracket F2511012820095 Item (16) Discard
(b) Install the new bracket.
Refer to Fig. A-FBBAD Sheet 03
 and Fig. A-FBBAD Sheet 04
 .
In accordance with SRM 51-42-00 and SRM 51-44-00.
1
 Temporarily put the bracket item 25 on the RH side of the upper bracket.
a
 If necessary, remove:
3 Rivet Item (11) Discard
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 37
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SERVICE BULLETIN
b
 Mark the position of the hole of the upper bracket on the new bracket.
c
 If removed, install:
3 Rivet ASNA2050DCJ3215 Item 11
2
 On bench, drill the marked hole to diameter comprised between 6.5 and 6.7
mm (0.256 and 0.264 in.).
3
 Put in position the new bracket item 25 with the bolt item 17.
Install:
1 Bracket F2511470820095 Item 25
1 Bolt NSA5042-04-160 Item 17
NOTE
: Install the bolt item 17 with:
Synthetic Ester
base Grease
03HBD9 As required
4
 Measure the clearance between the new bracket item 25 and the upper
bracket as show in Fig. A-FBBAD Sheet 04
 .
a
 Check that the minimum clearance are 0.35 mm (0.014 in.) at LHS and
0.65 mm (0.026 in.) at RHS.
5
 Match and drill the four holes of the cockpit main instrument panel on the new
bracket item 25 to a diameter comprised between 4.788 mm (0.189 in.) and
4.813 mm (0.190 in.) as shown on Figure Fig. A-FBBAD Sheet 03
 .
6
 Install:
4 Bolt ABS0114V3-5 Item 26
4 Nut NSA5050-3 Item 27
7
 Install the nut item 18:
1 Nut NSA5060-3 Item 18
1 Washer NSA5325-3 Item 19
1 Pin-Cotter MS24665-71 Item 21
NOTE
: Torque the nut item 18 to a value between 0.28 and 0.37
m.daN (24.782 and 32.748 lbf.in.).
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 38
5
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SERVICE BULLETIN
(2) Subtask 254354-410-001-003 - Install/Close Items Removed/Opened for access
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 31-63-22-400-801
Fig. A-FBCAA
Removal/Installation of the protection
plate and cover assembly panels
Sheet 01
Sheet 02
(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.
(b) Install the cover assembly plate.
Refer to Fig. A-FBCAA Sheet 02
 .
3 Stud Item (5) Retained at
removal
1 Panel Item (4) Retained at
removal
(c) Install the protection plate.
Refer to Fig. A-FBCAA Sheet 01
 .
3 Stud Item (1) Retained at
removal
3 Washer Item (2) Retained at
removal
1 Panel Item (3) Retained at
removal
**CONF 004
(1) Subtask 254354-911-001-004 - Replace the Bracket No. 6.
Work Zones and Access Panels
Zone
 Access/Work location
212
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 39
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SERVICE BULLETIN
Manpower Resources
Manhours
 2.00
Minimum number of person
 1
Subtask elapsed time
 2.00
Skills
 AIRFRAME
Material necessary to do the job
Kit 254354A04R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
11
 ASNA2050DCJ3215
 3
 RIVET
17
 NSA5042-04-160
 1
 BOLT
18
 NSA5060-3
 1
 NUT
19
 NSA5325-3
 1
 WASHER
21
 MS24665-71
 1
 PIN
25
 F2511470820095
 1
 BRACKET
26
 ABS0114V3-5
 4
 BOLT
27
 NSA5050-3
 4
 NUT
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Synthetic Ester base
Grease
03HBD9
 As required
References
Structural Repair Manual (SRM)
 51-42-00
51-44-00
Fig. A-FBBAB
Replacement of the bracket No. 6
Sheet 01
Sheet 02
Sheet 03
Sheet 04
(a) Remove the bracket No. 6.
Refer to Fig. A-FBBAB Sheet 01
 and Fig. A-FBBAB Sheet 02
 .
In accordance with SRM 51-42-00.
1
 Remove:
1 Bolt Item (17) Discard
1 Nut Item (18) Discard
1 Washer Item (19) Discard
1 Pin Item (21) Discard
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 40
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2
 Remove the fasteners:
4 Bolt Item (9) Discard
4 Nut Item (10) Discard
3
 Remove the bracket:
1 Bracket F2511373420000 Item (6) Discard
or
1 Bracket F2511373420095 Item (6) Discard
(b) Install the new bracket.
Refer to Fig. A-FBBAB Sheet 03
 and Fig. A-FBBAB Sheet 04
 .
In accordance with SRM 51-42-00 and SRM 51-44-00.
1
 Temporarily put the bracket item 25 on the RH side of the upper bracket.
a
 If necessary, remove:
3 Rivet Item (11) Discard
b
 Mark the position of the hole of the upper bracket on the new bracket.
c
 If removed, install:
3 Rivet ASNA2050DCJ3215 Item 11
2
 On bench, drill the marked hole to a diameter comprise between 6.5 and 6.7
mm (0.256 and 0.264 in.).
3
 Put the position the new bracket item 25 with the bolt item 17.
1 Bracket F2511470820095 Item 25
1 Bolt NSA5042-04-160 Item 17
NOTE
: Install the bolt item 17 with:
Synthetic Ester
base Grease
03HBD9 As required
4
 Measure the clearance between the new bracket item 25 and the upper
bracket as show in Fig. A-FBBAB Sheet 04
 .
a
 Check that the minimum clearance are 0.35 mm (0.014 in.) at LHS and
0.65 mm (0.026 in.) at RHS.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 41
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SERVICE BULLETIN
5
 Match and drill the four holes of the cockpit main instrument panel on the new
bracket item 25 to a diameter comprised between 4.788 mm (0.189 in.) and
4.813 mm (0.190 in.) as shown on Figure Fig. A-FBBAB Sheet 03
 .
6
 Install:
4 Bolt ABS0114V3-5 Item 26
4 Nut NSA5050-3 Item 27
7
 Install the nut item 18:
1 Nut NSA5060-3 Item 18
1 Washer NSA5325-3 Item 19
1 Pin-Cotter MS24665-71 Item 21
NOTE
: Torque the nut item 18 to a value between 0.28 and 0.37
m.daN (24.782 and 32.748 lbd.in.).
(2) Subtask 254354-410-001-004 - Install/Close Items Removed/Opened for access
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 31-63-22-400-801
Fig. A-FBCAA
Removal/Installation of the protection
plate and cover assembly panels
Sheet 01
Sheet 02
(a) Install the DU (FINs 1WK2 and 3WK2, refer to AMM Task 31-63-22-400-801.
(b) Install the cover assembly plate.
Refer to Fig. A-FBCAA Sheet 02
 .
3 Stud Item (5) Retained at
removal
1 Panel Item (4) Retained at
removal
(c) Install the protection plate.
Refer to Fig. A-FBCAA Sheet 01
 .
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 42
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3 Stud Item (1) Retained at
removal
3 Washer Item (2) Retained at
removal
1 Panel Item (3) Retained at
removal
**CONF ALL
D. TEST
**CONF 001
(1) Subtask 254354-700-001-001 - Test
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 21-26-00-710-803
Task 22-96-00-740-801
Task 22-97-00-740-801
Task 24-41-00-861-801
Task 25-11-51-400-801
Task 31-50-00-710-803
Task 31-50-00-740-801
Task 31-60-00-710-802
Task 33-12-13-400-801
Task 33-13-00-710-801
Task 33-14-00-710-801
Elec. Std. Practices Manual (ESPM)
 20-52-20
NOTE
: This test procedure is to be accomplished after the installation of
the equipment removed for access, refer to 253548-410-002 001
Install/Close Items Removed/Opened for access.
(a) In the cockpit, on the panel 235VU, push these pushbutton switches :
- BAT 1, BAT 2, APU BAT,
- GEN 1, (2), APU GEN,
- EXT A (B).
(b) Remove the warning notices.
(c) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 43
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(d) Remove the Safety clips and tags and close this (these) following circuit breaker(s):
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
742VU
 701PP
 10PB1
 72S
742VU
 702PP
 10PB2
 71S
(e) Preliminary Tests :
NOTE
: If the aircraft is operated in actual CAT III conditions, you must
also do the LAND CAT III capability test, (Refer to AMM Task
22-97-00-740-801).
1
 On each connector which was disconnected :
- Do the check as defined by ESPM 20-52-20.
NOTE
: The functional test and/or operational test requested by this
ESPM procedure is g iven hereafter.
2
 Do the O/T of the Instrument and Panel Integral Lighting, (Refer to AMM Task
33-13-00-710-801).
3
 Do the O/T of Lights, (Refer to AMM Task 33-14-00-710-801)
4
 Do the O/T of the Avionics-Equipment Ventilation System, (Refer to AMM
Task 21-26-00-710-803).
5
 Do the B/T of the Auto Flight System (SYSTEM TEST), (Refer to AMM Task
22-96-00-740-801).
6
 Do the O/T of the ECAM Control Panel,(Refer to AMM Task
31-50-00-710-803) .
7
 Do the test of FWS, (Refer to AMM Task 31-50-00-740-801).
8
 Do the O/T of the EIS, (Refer to AMM Task 31-60-00-710-802).
(f) Procedure :
1
 If removed, do the test procedure as specified after the Installation of the
Captain/First Officer Seat (Refer to AMM Task 25-11-51-400-801).
2
 If removed, do the test after the removal/installation of the Light Unit
(LU) (14LE of the center main instrument panel, (Refer to AMM Task
33-12-13-400-801).
**CONF 002
(1) Subtask 254354-700-001-001 - Test
Manpower Resources
Skills
 NON SPECIFIC
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 44
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SERVICE BULLETIN
References
Aircraft Maintenance Manual (AMM)
 Task 21-26-00-710-803
Task 22-96-00-740-801
Task 22-97-00-740-801
Task 24-41-00-861-801
Task 25-11-51-400-801
Task 31-50-00-710-803
Task 31-50-00-740-801
Task 31-60-00-710-802
Task 33-12-13-400-801
Task 33-13-00-710-801
Task 33-14-00-710-801
Elec. Std. Practices Manual (ESPM)
 20-52-20
NOTE
: This test procedure is to be accomplished after the installation of
the equipment removed for access, refer to 253548-410-002 001
Install/Close Items Removed/Opened for access.
(a) In the cockpit, on the panel 235VU, push these pushbutton switches :
- BAT 1, BAT 2, APU BAT,
- GEN 1, (2), APU GEN,
- EXT A (B).
(b) Remove the warning notices.
(c) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).
(d) Remove the Safety clips and tags and close this (these) following circuit breaker(s):
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
742VU
 701PP
 10PB1
 72S
742VU
 702PP
 10PB2
 71S
(e) Preliminary Tests :
NOTE
: If the aircraft is operated in actual CAT III conditions, you must
also do the LAND CAT III capability test, (Refer to AMM Task
22-97-00-740-801).
1
 On each connector which was disconnected :
- Do the check as defined by ESPM 20-52-20.
NOTE
: The functional test and/or operational test requested by this
ESPM procedure is g iven hereafter.
2
 Do the O/T of the Instrument and Panel Integral Lighting, (Refer to AMM Task
33-13-00-710-801).
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 45
5
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3
 Do the O/T of Lights, (Refer to AMM Task 33-14-00-710-801)
4
 Do the O/T of the Avionics-Equipment Ventilation System, (Refer to AMM
Task 21-26-00-710-803).
5
 Do the B/T of the Auto Flight System (SYSTEM TEST), (Refer to AMM Task
22-96-00-740-801).
6
 Do the O/T of the ECAM Control Panel,(Refer to AMM Task
31-50-00-710-803) .
7
 Do the test of FWS, (Refer to AMM Task 31-50-00-740-801).
8
 Do the O/T of the EIS, (Refer to AMM Task 31-60-00-710-802).
(f) Procedure :
1
 If removed, do the test procedure as specified after the Installation of the
Captain/First Officer Seat (Refer to AMM Task 25-11-51-400-801).
2
 If removed, do the test after the removal/installation of the Light Unit
(LU) (14LE of the center main instrument panel, (Refer to AMM Task
33-12-13-400-801).
**CONF 003
(1) Subtask 254354-700-001-001 - Test
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 21-26-00-710-803
Task 22-96-00-740-801
Task 22-97-00-740-801
Task 24-41-00-861-801
Task 25-11-51-400-801
Task 31-50-00-710-803
Task 31-50-00-740-801
Task 31-60-00-710-802
Task 33-12-13-400-801
Task 33-13-00-710-801
Task 33-14-00-710-801
Elec. Std. Practices Manual (ESPM)
 20-52-20
NOTE
: This test procedure is to be accomplished after the installation of
the equipment removed for access, refer to 253548-410-002 001
Install/Close Items Removed/Opened for access.
(a) In the cockpit, on the panel 235VU, push these pushbutton switches :
- BAT 1, BAT 2, APU BAT,
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 46
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- GEN 1, (2), APU GEN,
- EXT A (B).
(b) Remove the warning notices.
(c) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).
(d) Remove the Safety clips and tags and close this (these) following circuit breaker(s):
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
742VU
 701PP
 10PB1
 72S
742VU
 702PP
 10PB2
 71S
(e) Preliminary Tests :
NOTE
: If the aircraft is operated in actual CAT III conditions, you must
also do the LAND CAT III capability test, (Refer to AMM Task
22-97-00-740-801).
1
 On each connector which was disconnected :
- Do the check as defined by ESPM 20-52-20.
NOTE
: The functional test and/or operational test requested by this
ESPM procedure is g iven hereafter.
2
 Do the O/T of the Instrument and Panel Integral Lighting, (Refer to AMM Task
33-13-00-710-801).
3
 Do the O/T of Lights, (Refer to AMM Task 33-14-00-710-801)
4
 Do the O/T of the Avionics-Equipment Ventilation System, (Refer to AMM
Task 21-26-00-710-803).
5
 Do the B/T of the Auto Flight System (SYSTEM TEST), (Refer to AMM Task
22-96-00-740-801).
6
 Do the O/T of the ECAM Control Panel,(Refer to AMM Task
31-50-00-710-803) .
7
 Do the test of FWS, (Refer to AMM Task 31-50-00-740-801).
8
 Do the O/T of the EIS, (Refer to AMM Task 31-60-00-710-802).
(f) Procedure :
1
 If removed, do the test procedure as specified after the Installation of the
Captain/First Officer Seat (Refer to AMM Task 25-11-51-400-801).
2
 If removed, do the test after the removal/installation of the Light Unit
(LU) (14LE of the center main instrument panel, (Refer to AMM Task
33-12-13-400-801).
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 47
5
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**CONF 004
(1) Subtask 254354-700-001-001 - Test
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 21-26-00-710-803
Task 22-96-00-740-801
Task 22-97-00-740-801
Task 24-41-00-861-801
Task 25-11-51-400-801
Task 31-50-00-710-803
Task 31-50-00-740-801
Task 31-60-00-710-802
Task 33-12-13-400-801
Task 33-13-00-710-801
Task 33-14-00-710-801
Elec. Std. Practices Manual (ESPM)
 20-52-20
NOTE
: This test procedure is to be accomplished after the installation of
the equipment removed for access, refer to 253548-410-002 001
Install/Close Items Removed/Opened for access.
(a) In the cockpit, on the panel 235VU, push these pushbutton switches :
- BAT 1, BAT 2, APU BAT,
- GEN 1, (2), APU GEN,
- EXT A (B).
(b) Remove the warning notices.
(c) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801).
(d) Remove the Safety clips and tags and close this (these) following circuit breaker(s):
PANEL
 DESIGNATION
 FIN
 LOCATION
 SEE
NOTES
742VU
 701PP
 10PB1
 72S
742VU
 702PP
 10PB2
 71S
(e) Preliminary Tests :
NOTE
: If the aircraft is operated in actual CAT III conditions, you must
also do the LAND CAT III capability test, (Refer to AMM Task
22-97-00-740-801).
1
 On each connector which was disconnected :
- Do the check as defined by ESPM 20-52-20.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 48
5
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### Page 55

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NOTE
: The functional test and/or operational test requested by this
ESPM procedure is g iven hereafter.
2
 Do the O/T of the Instrument and Panel Integral Lighting, (Refer to AMM Task
33-13-00-710-801).
3
 Do the O/T of Lights, (Refer to AMM Task 33-14-00-710-801)
4
 Do the O/T of the Avionics-Equipment Ventilation System, (Refer to AMM
Task 21-26-00-710-803).
5
 Do the B/T of the Auto Flight System (SYSTEM TEST), (Refer to AMM Task
22-96-00-740-801).
6
 Do the O/T of the ECAM Control Panel,(Refer to AMM Task
31-50-00-710-803) .
7
 Do the test of FWS, (Refer to AMM Task 31-50-00-740-801).
8
 Do the O/T of the EIS, (Refer to AMM Task 31-60-00-710-802).
(f) Procedure :
1
 If removed, do the test procedure as specified after the Installation of the
Captain/First Officer Seat (Refer to AMM Task 25-11-51-400-801).
2
 If removed, do the test after the removal/installation of the Light Unit
(LU) (14LE of the center main instrument panel, (Refer to AMM Task
33-12-13-400-801).
**CONF ALL
E. CLOSE-UP
**CONF 001
(1) Subtask 254354-942-001-001 - Close-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 25-11-51-400-801
Task 31-63-22-400-801
Task 33-12-13-400-801
Task 52-10-00-010-801
(a) Make sur that the work areas are clean and clear of tools and other items.
(b) Parts and/or equipment removed for access, to be installed before the subtask
253548-700-003 001 Test
1
 If removed, install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 49
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2
 If removed, install the First Officer Seat (FIN 4MS), refer to AMM Task
25-11-51-400-801.
(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and
3WK2, refer to AMM Task 31-63-22-400-801.
(d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.
(e) Remove the access platform.
(f) Restore the systems and the aircr aft to normal operation conditions.
**CONF 002
(1) Subtask 254354-942-001-001 - Close-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 25-11-51-400-801
Task 31-63-22-400-801
Task 33-12-13-400-801
Task 52-10-00-010-801
(a) Make sur that the work areas are clean and clear of tools and other items.
(b) Parts and/or equipment removed for access, to be installed before the subtask
253548-700-003 001 Test
1
 If removed, install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801.
2
 If removed, install the First Officer Seat (FIN 4MS), refer to AMM Task
25-11-51-400-801.
(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and
3WK2, refer to AMM Task 31-63-22-400-801.
(d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.
(e) Remove the access platform.
(f) Restore the systems and the aircr aft to normal operation conditions.
**CONF 003
(1) Subtask 254354-942-001-001 - Close-up
Manpower Resources
Skills
 NON SPECIFIC
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 50
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References
Aircraft Maintenance Manual (AMM)
 Task 25-11-51-400-801
Task 31-63-22-400-801
Task 33-12-13-400-801
Task 52-10-00-010-801
(a) Make sur that the work areas are clean and clear of tools and other items.
(b) Parts and/or equipment removed for access, to be installed before the subtask
253548-700-003 001 Test
1
 If removed, install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801.
2
 If removed, install the First Officer Seat (FIN 4MS), refer to AMM Task
25-11-51-400-801.
(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and
3WK2, refer to AMM Task 31-63-22-400-801.
(d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.
(e) Remove the access platform.
(f) Restore the systems and the aircr aft to normal operation conditions.
**CONF 004
(1) Subtask 254354-942-001-001 - Close-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 25-11-51-400-801
Task 31-63-22-400-801
Task 33-12-13-400-801
Task 52-10-00-010-801
(a) Make sur that the work areas are clean and clear of tools and other items.
(b) Parts and/or equipment removed for access, to be installed before the subtask
253548-700-003 001 Test
1
 If removed, install the LU (FIN 14LE), refer to AMM Task 33-12-13-400-801.
2
 If removed, install the First Officer Seat (FIN 4MS), refer to AMM Task
25-11-51-400-801.
(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and
3WK2, refer to AMM Task 31-63-22-400-801.
(d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 51
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(e) Remove the access platform.
(f) Restore the systems and the aircr aft to normal operation conditions.
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 52
5
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**CONF 001
BRACKET No 6
A
A
B C
F_SB_254354_5_BBAA_01_00
Figure A-FBBAA - Sheet 01
Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 53
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**CONF 001
(16)
FWD
BEFORE
(7)
(8)
B
HOLE
SYMBOL ITEM OLD PN DESCRIPTION
RIVET
RIVET
ASNA2050DCJ3215 RIVET
(12)
(14)
(11)
ASNA2051DEJ4020
ASNA2050DEJ4020
F_SB_254354_5_BBAA_02_00
Figure A-FBBAA - Sheet 02
Replacement of the bracket No. 6
DATE: Oct 31/13 SERVICE BULLETIN No.: A340-25-4354
REVISION No.: 00 - Oct 31/13 Page: 54
5
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