# Airbus Service Bulletin A340-53-4238

Copy: No revision named ("A340-53-4238 R00"), 71 pages: PDF https://openairdocs.org/files/sha256/36/51/36518ee667533037809e4635dd360d2a028d5bdf6d63dc225c50d4d51d7fb7fd; text https://openairdocs.org/service-documents/airbus/a340-53-4238/file/36518ee66753.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2018-0583; AD 2018-20-19 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: A340-53-4238
- Page: https://openairdocs.org/service-documents/airbus/a340-53-4238

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

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

- [AD 2018-20-19](https://openairdocs.org/ad/2018-20-19.md), effective Nov 20, 2018: No revision named

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a340-53-4238/proposed.md).

## Text (71 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2018-0583; AD 2018-20-19 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: 53
TITLE: FUSELAGE - REAR FUSELAGE - REMOVE TSA IN THE FINAL HOLES
OF S17 BULK CARGO DOOR FRAME C67 AND C69
**CONF ALL
MODIFICATIONS
MODIFICATION CLASSIFICATION
MAJOR
 None
MINOR
 206409D52230
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 A330 Extended Service Goal (ESG) justification, fatigue analysis of bulk cargo door frames
shows some thresholds below Design Service Goal (DSG) values.
It has been identified that Tartaric Sulfuric Anodizing (TSA) / Chromic Acid Anodizing (CAA) surface
treatment is present in the door fittings attachment holes of FR67 and FR69 of the lower side shell RH
in Section 17. This leads to a detrimental effect on fatigue behavior.
This condition, if not detected and corrected, could lead to critical cracks in the primary structure.
This Service Bulletin details the necessary instructions to remove the TSA in the final holes of the bulk
door frames FR67 and FR69.
The accomplishment of this Service Bulletin will contribute to maintain the structural integrity in the
frames of the bulk cargo door.
Accomplishment of this Service Bulletin cancels the requirements of Inspection Service Bulletin (ISB)
No. A340-53-4239.
GENERAL EVALUATION
EVALUATION TABLE
COMPLIANCE
 RECOMMENDED (1)
 CANCELS INSPECTION SB
 YES
POTENTIAL AD
 NO
 A/C OPERATION AFFECTED
 NO
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 2

@A340
SERVICE BULLETIN
SUMMARY
EVALUATION TABLE
RELIABILITY AFFECTED
 NO
 PAX COMFORT AFFECTED
 NO
COST SAVING
 NO
 LROPS AFFECTED
 NO
STRUCTURAL LIFE EXTN
 YES
 VENDOR SB INVOLVED
 NO
NOTE
 (1)
: Service Bulletin recommended to be accomplished to prevent significant operational
disruptions.
MATERIAL PRICE INFORMATION
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 534238D01R03
 1
 5,100.00
 Bushes, bolts, nuts, collars, washers,
tape
Component COMPD01
 1
 See SB
 Rivets
Standard tool TOOLD01
 1
 See SB
 FTI tooling for cold expansion
Standard tool TOOLD02
 1
 See SB
 WCI tooling for cold expansion
EFFECTIVITY
This Service Bulletin is applicable to this (these) operator(s) :
01V 06Y 09M 14S 15R 17M 31V 39N 41N 65W 74W 78U 83Q
83V 85Z 98W ABD AFR AIB ALD ARG AXY BOE CAL CPA DGA
DLH EDW F2I FIN GAF HFM HFY IBE IRC IRM KAC KMF M3R
MAU MDG MRJ PAL PUE QQE ROI S3R SAA SAS SFB SLM SWR
SYR TAP THT THY VCV
CONCURRENT REQUIREMENTS
None
REFERENCES / REPERCUSSIONS
TFU
 53.40.00.005
OEB
 None
AOT
 None
SIL
 None
ISI
 51.48.00001
LINE MAINTENANCE AFFECTED
 No
LIFE LIMIT
 None
OTHER
 None
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
HARD
 NO
SOFT
 NO
OBRM
 NO
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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@A340
SERVICE BULLETIN
SUMMARY
MANPOWER
Task 534238-831-848-001: Modification
TOTAL MANHOURS
 31.25
ELAPSED TIME (HOURS)
 16.50
APPENDICES
Appendix 01 - Manpower Gantt Chart
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 3
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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@A340
SERVICE BULLETIN
SUMMARY
**CONF ALL
ALL ATTACHMENT
FITTINGS
A
FR69
FR67
NOTE:
AREA TO BE MODIFIED.
A
823
ALL ATTACHMENT
FITTINGS
F_SB_534238_6_SAAA_01_01
Figure A-GSAAA - Sheet 01
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 4
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 5

@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: 53
TITLE: FUSELAGE - REAR FUSELAGE - REMOVE TSA IN THE FINAL HOLES
OF S17 BULK CARGO DOOR FRAME C67 AND C69
MODIFICATION No.: 206409D52230
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 0009 0014 0020 0022-0023 0025-0026 0029 0031 0038 0041 0043-0044
0046-0047 0049 0051 0056-0058 0061 0063 0074-0076 0078-0081 0084 0089-0091
0093-0094 0101 0104 0114-0115 0117 0123 0125-0126 0128 0134-0135 0139
0145-0146 0149-0152 0154 0156-0160 0163-0164 0166-0170 0174-0175 0178-0180
0185-0186 0190 0192-0194 0197 0199 0201-0202 0204 0207-0208 0210 0212-0215
0217-0218 0221 0227 0233 0236-0237 0242-0243 0245-0246 0252 0257 0260
0263-0264 0268 0270 0274 0278 0280 0282 0292 0297 0302 0304 0307 0310
0318-0319 0321 0325 0327 0329 0331-0332 0335 0347 0352 0354-0355 0367
0373-0374 0377-0379 0381 0385 0387 0390 0395 0399 0402 0406 0411 0413 0415
0424 0430 0433-0435 0438 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: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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SERVICE BULLETIN
(3) Effectivity by Operator
The Operator/MSN relationship is provided for information only and is correct at the time
of issue in accordance with the information available to AIRBUS. Any future changes
resulting from transfer of an aircraft from one operator to another will not be reflected in
this list unless the Service Bulletin is revised for another reason.
OPERATOR
 MSN
01V
 0146
06Y
 0139 0149
09M
 0483
14S
 0058
15R
 0151
17M
 0955
31V
 0093
39N
 0168 0174
41N
 0009
65W
 0029
74W
 0047 0051
78U
 0175 0179
83Q
 0150
83V
 0280 0292
85Z
 0263
98W
 0014 0022
ABD
 0210
AFR
 0078 0084 0186 0207 0237 0245 0246 0260 0307 0310 0377
AIB
 0192 0243 0264 0835 0844
ALD
 0156 0159 0178
ARG
 0063 0074 0080 0123 0126 0128 0170 0193 0373
AXY
 0374
BOE
 0554
CAL
 0402 0406 0411 0415 0433 0541
CPA
 0157 0160 0208 0218 0227
DGA
 0075 0081
DLH
 0135 0158 0213 0233 0252 0297 0304 0321 0325 0327 0335 0347
0352 0354 0379 0390 0434 0447
EDW
 0562
F2I
 0038 0043 0094 0114 0214
FIN
 0921 0938
GAF
 0274 0355
HFM
 0117 0163 0166 0185 0236 0367
HFY
 0190 0202
IBE
 0125 0134 0145 0217 0221 0329
IRC
 0002
IRM
 0020 0056 0164 0282
KAC
 0089 0090 0101 0104
KMF
 0278
M3R
 0061
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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@A340
SERVICE BULLETIN
OPERATOR
 MSN
MAU
 0076 0152 0194 0268 0793 0800
MDG
 0319
MRJ
 0257
PAL
 0302 0318 0332 0387 0459 0474
PUE
 0212 0215 0399
QQE
 0026 0528
ROI
 0199 0201
S3R
 0004 0204
SAA
 0197 0378 0544 0582 0590 0643 0646 0651
SAS
 0167 0413 0424 0430 0435 0450 0467 0470
SFB
 0046
SLM
 0049 0242
SWR
 0154 0169 0538 0545 0546 0556 0559 0561 0585 0598
SYR
 0381
TAP
 0041 0044 0079 0091
THT
 0385 0395 0438 0446 0668
THY
 0023 0025 0057 0115 0180 0270 0331
VCV
 0031
(4) Configuration by MSN
MSN
 CONFIGURATION
0002 0004 0009 0014 0020 0022 0023 0025 0026 0029 0031
0038 0041 0043 0044 0046 0047 0049 0051 0056 0057 0058
0061 0063 0074 0075 0076 0078 0079 0080 0081 0084 0089
0090 0091 0093 0094 0101 0104 0114 0115 0117 0123 0125
0126 0128 0134 0135 0139 0145 0146 0149 0150 0151 0152
0154 0156 0157 0158 0159 0160 0163 0164 0166 0167 0168
0169 0170 0174 0175 0178 0179 0180 0185 0186 0190 0192
0193 0194 0197 0199 0201 0202 0204 0207 0208 0210 0212
0213 0214 0215 0217 0218 0221 0227 0233 0236 0237 0242
0243 0245 0246 0252 0257 0260 0263 0264 0268 0270 0274
0278 0280 0282 0292 0297 0302 0304 0307 0310 0318 0319
0321 0325 0327 0329 0331 0332 0335 0347 0352 0354 0355
0367 0373 0374 0377 0378 0379 0381 0385 0387 0390 0395
0399 0402 0406 0411 0413 0415 0424 0430 0433 0434 0435
0438 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.
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 3
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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@A340
SERVICE BULLETIN
(6) Material Effectivity
MATERIAL
 QTY PER A/C
 SEE NOTES
Kit 534238D01R03
 1
Component COMPD01
 1
Standard tool TOOLD01
 1
Standard tool TOOLD02
 1
Consumable CMLD01
 1
Reidentified part set REIDD01
 1
Reidentified part set REIDD02
 1
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
During A330 Extended Service Goal (ESG) justification, fatigue analysis of bulk cargo
door frames shows some thresholds below Design Service Goal (DSG) values.
It has been identified that Tartaric Sulfuric Anodizing (TSA) / Chromic Acid Anodizing
(CAA) surface treatment is present in the door fittings attachment holes of FR67 and
FR69 of the lower side shell RH in Section 17. This leads to a detrimental effect on
fatigue behavior.
This condition, if not detected and corrected, could lead to critical cracks in the primary
structure.
(2) Objective/Action
This Service Bulletin details the necessary instructions to remove the TSA in the final
holes of the bulk door frames FR67 and FR69.
(3) Advantages
The accomplishment of this Service Bulletin will contribute to maintain the structural
integrity in the frames of the bulk cargo door.
Accomplishment of this Service Bulletin cancels the requirements of Inspection Service
Bulletin (ISB) No. A340-53-4239.
(4) Operational/Maintenance Consequences
None
D. DESCRIPTION
To accomplish this Service Bulletin it is necessary to :
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 4
6
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@A340
SERVICE BULLETIN
Task 534238-831-848-001: Modification
(1) Get Access at the Location of the Door Support Fitting-Upper FR67
(2) Remove the Fasteners and the Support Assemblies at the Bulk Cargo Door FR67
(3) Get Access at the Location of the Door Support Fitting-Upper FR69
(4) Remove the Fasteners and the Support Assemblies at the Bulk Cargo Door FR69
(5) Do the Eddy Current Rotating Probe Inspection of the Fastener Holes at FR67
(6) Do the Eddy Current Rotating Probe Inspection of the Fastener Holes at FR69
(7) Do the Cold Working Process of the Fastener Holes at FR67 (Fuselage Frame Only)
(8) Do the Cold Working Process of the Fastener Holes at FR69 (Fuselage Frame Only)
(9) Do the Installation of the Support and Spigot Assemblies at FR67
(10) Do the Installation of the Support and Spigot Assemblies at FR69
(11) Re-identify the Support Assembly and Serrated Plate on FR67
(12) Re-identify the Support Assembly on FR69
(13) Apply the Sealants and Corrosion Preventive Compounds to the Support and Spigot
Assemblies at FR67 and FR69
(14) Install the Items Removed for Access at the Location of the Door Support Fitting-
Upper FR67
(15) Install the Items Removed for Access at the Location of the Door Support Fitting-
Upper FR69
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.
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 5
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 10

@A340
SERVICE BULLETIN
If an aircraft listed in the effectivity has a modification or repair embodied that is not of
AIRBUS origin, and which affects the content of this Service Bulletin, the operator is
responsible for obtaining approval by its airworthiness authority for any adaptation necessary
before incorporation of the Service Bulletin.
G. MANPOWER
The manpower estimates given in this Service Bulletin are based on the direct labor cost to
do the work. These estimates assume that the work will be done by experienced personnel,
and may need to be revised upwards to suit operator’s circumstances. The estimates do not
include the time to prepare, plan or inspect the work. Manufacture and procurement of parts
and tools, drying times for paints, sealants, etc., and general administration work are also not
included.
Task 534238-831-848-001: Modification
Get Access
 3.00
On Aircraft
Get Access at the Location of the Door Support Fitting-
Upper FR67
1.00
Remove the Fasteners and the Support Assemblies at
the Bulk Cargo Door FR67
1.50
Get Access at the Location of the Door Support Fitting-
Upper FR69
1.50
Remove the Fasteners and the Support Assemblies at
the Bulk Cargo Door FR69
1.50
Do the Eddy Current Rotating Probe Inspection of the
Fastener Holes at FR67
1.00
Do the Eddy Current Rotating Probe Inspection of the
Fastener Holes at FR69
1.00
Do the Cold Working Process of the Fastener Holes at
FR67 (Fuselage Frame Only)
3.00
Do the Cold Working Process of the Fastener Holes at
FR69 (Fuselage Frame Only)
3.00
Do the Installation of the Support and Spigot
Assemblies at FR67
3.00
Do the Installation of the Support and Spigot
Assemblies at FR69
3.00
Re-identify the Support Assembly and Serrated Plate
on FR67
0.50
Re-identify the Support Assembly on FR69
 0.25
Apply the Sealants and Corrosion Preventive
Compounds to the Support and Spigot Assemblies at
FR67 and FR69
2.00
Install the Items Removed for Access at the Location
of the Door Support Fitting-Upper FR67
1.00
Install the Items Removed for Access at the Location
of the Door Support Fitting-Upper FR69
1.50
Tests
 0.50
Close-Up
 3.00
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 6
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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@A340
SERVICE BULLETIN
Task 534238-831-848-001: Modification
TOTAL MANHOURS
 31.25
ELAPSED TIME (HOURS)
 16.50
NOTE
: For an explanation of the manhours and elapsed time, refer to the Gantt
Chart, Fig. A-GAAAA
 given in Appendix 01 - Manpower Gantt Chart .
H. WEIGHT AND BALANCE
Not Changed
I. ELECTRICAL LOAD DATA
Not Changed
J. REFERENCES
Aircraft Maintenance Manual (AMM)
 06-20-00 06-31-53 12-34-24
20-21-11 52-33-32 53-43-11
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
In Service Information (ISI)
 ISI 51.48.00001
Non Destructive Test Manual (NTM)
 51-10-01
Process and Material Specification (PMS)
 Process and Material Specification
(PMS) 01-06-12
Service Bulletin (SB)
 A340-53-4239
Service Information Letter (SIL)
 SIL 51-012
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-21-00 51-23-12 51-24-00
51-40-00 51-42-00 51-43-00
51-44-00 51-44-11 51-46-11
51-48-00 51-75-12 51-76-11
NOTE
: SIL 51-012 has been migrated into ISI article 51.48.00001.
K. PUBLICATION AFFECTED
Aircraft Maintenance Manual (AMM)
 52-33-32
Illustrated Parts Catalog (IPC)
 52-33-32
L. INTERCHANGEABILITY/MIXABILITY
Not Applicable
M. SPARES
None
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 7
6
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SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 8
6
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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 534238D01R03
 AIRBUS Material, Logistics and Suppliers
ATP II B
Hein-Sass-Weg 24
21129 HAMBURG
GERMANY
For ordering by internet:
http://spares.airbus.com
For ordering by E-mail: airbus.kit@airbus.com
Telephone Hotline: +49 40 743 51616
For standard hardware the purchase order shall be addressed to AIRBUS. Quote the
number of this Service Bulletin, the MSN and, if applicable the Retrofit Information Letter
(RIL) reference. Please send your request to:
Component COMPD01
 AIRBUS Material, Logistics and Suppliers
Standard Parts
For ordering by internet:
http://spares.airbus.com or vi a SPEC2000
For ordering by E-mail:
standard.parts@airbus.com
Phone: +49 (0) 40 50 76 40 03
(2) Price and Availability
Kit 534238D01R03
Cost
 5,100.00 USD
Availability
 210 calendar days from receipt of order
The 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
Airbus Spares portal or through a request for quotation to airbus.kit@airbus.com.
Component COMPD01
Operator supplied standard hardware parts required to accomplish this Service Bulletin
are to be supplied from the operator’s stock.
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 9
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SERVICE BULLETIN
B. INDUSTRY SUPPORT INFORMATION
AIRBUS will not provide industry support for accomplishment of this Service Bulletin.
This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.
For the organization 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
C. LIST OF COMPONENTS
Kit 534238D01R03
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
1
 F5327127020200
 4
 BUSH
3
 NAS1149C0332R
 4
 WASHER
4
 NAS1149C0432R
 4
 WASHER
5
 F5347598420000
 1
 TAPE
6
 NAS1726-3E
 4
 NUT
7
 NAS1726-4E
 44
 NUT
8
 NSA5031-3-8
 2
 BOLT
9
 NSA5031-3-10
 2
 BOLT
10
 ABS0114T4-5Y
 20
 BOLT
11
 ABS0114T4-7Y
 20
 BOLT
12
 NSA5031-4-8
 2
 BOLT
13
 NSA5031-4-10
 2
 BOLT
14
 DIN65399-2412BF
 2
 RIVET
15
 NSA5075W6
 4
 COLLAR
17
 DAN6-6-6
 4
 PIN
32
 F5327127020800
 4
 BUSH
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: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 10
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SERVICE BULLETIN
D. LIST OF MATERIALS - OPERATOR SUPPLIED
(1) Consumable Materials
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
Wash Primer
 04CMA2
 As required
Primer Epoxy Paint-Corrosion
Inhibiting
04DAB2
 As required
Top Coat Polyurethane-Gray
Internal Structure
04JME4
 As required
Coating-Flexible Structure
 04QAB2
 As required
Polysulfide Sealant-General
Purpose Brushable
06AAA1
 As required
Polysulfide Sealant-General
Purpose Fillet
06AAB1
 As required
Polysulfide Sealant-General
Purpose Interfay
06AAC1
 As required
Non Hardening Jointing Putty
 06LCB1
 As required
Non Aqueous Cleaner-General
 08BAA9
 As required
Corrosion Preventive Compound-
Hard
12ABB1
 As required
Corrosion Preventive Compound-
Soft
12ABC1
 As required
Textile-Lint Free Cotton
 14SBA1
 As required
(2) Components
Component COMPD01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
50
 DIN65399-4020BF
 16
 RIVET
52
 NAS1921B05S03U
 3
 RIVET
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.
(3) Equipment
None
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 11
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SERVICE BULLETIN
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
Reidentified part set REIDD01
ITEM
 NEW PART N˚
 KEYWORD
 ITEM
 OLD PART N˚
 SEE
NOTES
19
 A5397802600800
 SUPPORT
 (19)
 A5397802600400
26
 A5397805221600
 PLATE
 (26)
 A5397805221200
Reidentified part set REIDD02
ITEM
 NEW PART N˚
 KEYWORD
 ITEM
 OLD PART N˚
 SEE
NOTES
20
 A5397802601000
 SUPPORT
 (20)
 A5397802600600
F. TOOLING
(1) Tooling - Price and Availability
(a) Procurement Addresses
Operators interested in obtaining the Fatigue Technology Incorporated (FTI) tool kit
should contact:
Standard tool TOOLD01
 Fatigue Technology Inc.
401 Andover Park East
SEATTLE, WA 98188-7605
USA
Internet: http://www.fatiguetech.com
Phone: (206) 2462010
Fax: (206) 2449886
Operators interested in obtaining the West Coast Industries (WCI) tool kit should
contact:
Standard tool TOOLD02
 West Coast Industries Inc.
14900 Whitman Ave. N
SEATTLE
WA 98133
USA
Email: info@coldwork.com
Phone: (206) 365-7513
Fax: (206) 365-7483
Europe, Middle East, Africa and Russia:
customer@capaero.com / +33 5 61 92 04 91
(France)
(b) Price and Availability
Procurement to be negotiated directly with Fatigue Technology Incorporated (FTI)
or
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 12
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SERVICE BULLETIN
Procurement to be negotiated directly with West Coast Industries (WCI).
(2) Tools
To accomplish this Service Bulletin it will be necessary to use the tools and equipment
listed in NTM Task 51-10-01-250-801.
Standard tool TOOLD01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA340534238-1
 Durable Tooling
 1
 (1)
EKA340534238-1
 Expendable Tooling
 1
 (2)
FTIA340534238-1
 Capital Tooling
 1
 (3)
NOTE
: Fatigue Technology Incorporated (FTI) has allocated the following tool kit
numbers for cold expansion:
For the definition of capital, durable and expendable tools, refer to ISI
51.48.00001.
NOTE
 (1)
: Durable Tooling: Ref. DKA340534238-1
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to SIL
51-012 (corresponding to ISI 51.48.00001).
NOTE
 (2)
: Expendable Tooli ng: Ref. EKA340534238-1
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
NOTE
 (3)
: Capital Tooling: Ref. FTIA340534238-1
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operators’ stock as a long-
term investment or can be loaned from FTI.
Standard tool TOOLD02
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA340534238-1
 Durable Tooling
 1
 (1)
EKA340534238-1
 Expendable Tooling
 1
 (2)
WCIA340534238-1
 Capital Tooling
 1
 (3)
NOTE
: West Coast Industries (WCI) has allocated the following tool kit numbers
for cold expansion:
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 13
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SERVICE BULLETIN
For the definition of capital, durable and expendable tools, refer to ISI
51.48.00001.
NOTE
 (1)
: Durable Tooling: Ref. DKA340534238-1
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to SIL
51-012 (corresponding to ISI 51.48.00001).
NOTE
 (2)
: Expendable Tooli ng: Ref. EKA340534238-1
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
NOTE
 (3)
: Capital Tooling: Ref. WCIA340534238-1
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operators’ stock as a long
term investment or can be loaned from WCI.
(3) Special Tools
None
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 14
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3. ACCOMPLISHMENT INSTRUCTIONS
Task 534238-831-848-001 - 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.
IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.
NOTE
: The accomplishment instructions of this Service Bulletin include procedures given
in other documents or in other sections of the Service Bulletin. When the words
’refer to’ are used and the operator has a procedure accepted by the local authority
he belongs to, the accepted alternative procedure can be used. When the words ’in
accordance with’ are used then the given procedure must be followed.
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
: This Service Bulletin contains the instructions for the on-aircraft maintenance
necessary to ensure the continued airworthiness of the aircraft.
For any deviations to the instructions contained herein, contact AIRBUS for further
instructions and approval.
NOTE
: Discarded parts must be managed at the operator’s discretion.
Task Associated Data
Zone
823
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 15
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SERVICE BULLETIN
Manpower
TOTAL MANHOURS
 31.25
ELAPSED TIME (HOURS)
 16.50
A. GENERAL
(1) Subtask 534238-910-201-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-20-00, Page Block 001
06-31-53, Page Block 001
Task 20-21-11-911-801
Consumable Material List (CML)
Process and Material Specification
(PMS)
Process and Material Specification (PMS)
01-06-12
Structural Repair Manual (SRM)
 51-21-00
51-24-00
51-40-00
51-42-00
51-43-00
51-44-00
51-44-11
51-46-11
51-48-00
51-75-12
51-76-11
(a) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer
to the Consumable Materials List (CML).
(b) If you find process and material specifications that you do not know in the design
drawings, refer to the cross-reference list in the Process and Material Specification
(PMS).
(c) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.
(d) For the identification of zones, refer to AMM 06-20-00, Page Block 001.
(e) Do the removal and installation of fasteners in accordance with SRM 51-42-00.
(f) Do the cold working of the fastener holes in accordance with SRM 51-48-00.
(g) Get fastener hole diameters and drill deburr data in accordance with SRM 51-44-00
and SRM 51-44-11.
(h) Protect the areas to prevent damage to the equipment and structure and all the
parts.
(i) Do sealant application in accordance with SRM 51-24-00 and SRM 51-76-11.
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 16
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SERVICE BULLETIN
(j) To torque tighten the standard threaded fasteners, refer to AMM Task
20-21-11-911-801.
(k) Get alternative and substitute fastener data in accordance with SRM 51-43-00.
(l) In case alternative and substitute fasteners are to be used, you must check that the
associated nut/collar are compatible in accordance with SRM 51-40-00.
(m) 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.
(n) Get countersinking of fastener holes data in accordance with SRM 51-46-11.
(o) Put all the retained hardware in identified plastic bags and attach the bags to the
related unit.
(p) Renew the protective finish in accordance with SRM 51-75-12.
(q) Apply protective treatments in accordance with SRM 51-21-00.
(r) Part mark with indelible ink in accordance with Process and Material Specification
(PMS) 01-06-12.
(2) Subtask 534238-839-201-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
B. PREPARATION
(1) Subtask 534238-941-201-001 - Job Set-up
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 67
Frame 69
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 12-34-24-860-802
Task 52-33-32-000-801
Task 52-33-32-000-802
NOTE
: For the basic Aircraft configuration, refer to AMM Chapter ’Introduction -
Aircraft status for maintenance’ in Manual Front Matter section.
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 17
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SERVICE BULLETIN
(a) Make sure that the aircraft is electrically grounded, refer to AMM Task
12-34-24-860-802.
(b) Put access platforms in position at bulk cargo door 823 RH at Frame 67 and Frame
69.
(c) Do the job set-up as specified in the removal of the support assembly, refer to
AMM Task 52-33-32-000-801.
(d) Do the job set-up as specified in the removal of the latch spigot assembly, refer to
AMM Task 52-33-32-000-802.
C. PROCEDURE
(1) Subtask 534238-010-201- 001 - Get Access at the Location of the Door Support
Fitting-Upper FR67
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 67
Manpower Resources
Manhours
 1.00
Minimum number of person
 1
Subtask elapsed time
 1.00
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)
 Task 53-43-11-000-801
Structural Repair Manual (SRM)
 51-42-00
Fig. A-GBBAA
Removal/Installation of the Covers for
Modification of FR67 and FR69 at the
Location of the Door Support Fittings-
Upper
Sheet 01
Sheet 02
Sheet 03
Sheet 04
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 18
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SERVICE BULLETIN
(a) Remove the cover at Frame 67 to get access to the modification area, refer to
Fig. A-GBBAA Sheet 01
 ,V i e wAa n d Fig. A-GBBAA Sheet 02
 ,V i e wBa n di n
accordance with SRM 51-42-00:
1
 Remove:
1 Cover Item (51) Retain
attached with:
3 Rivet Item (52) Discard
8 Rivet Item (50) Discard
2
 Remove the old sealant with a plastic scrapper.
3
 Clean the work area with:
Textile-Lint Free
Cotton
14SBA1 As required
made moist with:
Non Aqueous
Cleaner-General
08BAA9 As required
4
CAUTION
: DO NOT REMOVE THE ATTACHMENT PARTS OF THE RH
SUPPORT STRUTS AT FRAME 67 AND FRAME 69 AT THE
SAME TIME. IF YOU DO NOT SUPPORT THE CABIN
FLOOR STRUCTURE BEFORE THE REMOVAL OF TWO
ADJACENT STRUTS, YOU CAN CAUSE STRUCTURAL
FAILURE OF THE CABIN FLOOR STRUCTURE.
Remove the lower attachment parts of the RH support strut at Frame 67, refer
to AMM Task 53-43-11-000-801.
5
 Move the lower end of the support strut to get access to the modification area.
(2) Subtask 534238-831-201- 001 - Remove the Fasteners and the Support Assemblies
at the Bulk Cargo Door FR67
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 67
Manpower Resources
Manhours
 1.50
Minimum number of person
 1
Subtask elapsed time
 1.50
Skills
 AIRFRAME
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 19
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SERVICE BULLETIN
References
Fig. A-GBAAA
Modification of the Bulk Cargo Door
Frames at FR67 and FR69
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
CAUTION
: MAKE SURE THAT THE FASTENER HOLE EDGE DISTANCE IS
CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO
AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION
AREA.
(a) Remove the fasteners and the support assembly at the bulk cargo door Frame 67.
1
 At Frame 67 between positions STGR37 and STGR43 remove, as shown
on Fig. A-GBAAA Sheet 01
 , View A and Fig. A-GBAAA Sheet 04
 ,V i e wF ,
Section D-D:
20 Nut NAS1726-4E Item (7) Discard
10 Bolt NSA5031-4-5 Item (10) Discard
10 Bolt NSA5031-4-7 Item (11) Discard
5 Support Assy A5397802600400 Item (19) Retain
(b) Remove the fasteners and the spigot assembly at the bulk cargo door Frame 67.
1
 At Frame 67 at position STGR42A remove, as shown on Fig. A-GBAAA Sheet
01
, View A and Fig. A-GBAAA Sheet 04
 , View F, Section E-E and Fig. A-
GBAAA Sheet 05
 View J:
2 Nut NAS1726-4E Item (7) Discard
2 Bolt NSA5031-4-7 Item (11) Discard
2 Bolt NSA5031-3-10 Item (9) Discard
2 Nut NAS1726-3E Item (6) Discard
2 Pin Hi-Lok DAN6-5-6 Item (17) Discard
2 Collar NSA5075W5 Item (15) Discard
1 Spigot Assy-Latch F 5347597600600 Item (23) Retain
1 Plate-Serrated A5397805220800 Item (25) Retain
1 Plate-Serrated A5397805221200 Item (26) Retain
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 20
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SERVICE BULLETIN
2 Rivet DIN65399-2400BF Item (14) Discard
1 Nut-Plate MS21059L06 Item (27) Retain
2 Bush F5327127020200 Item (1) Discard
2 Bush F5327127020800 Item (32) Discard
(3) Subtask 534238-010-202- 001 - Get Access at the Location of the Door Support
Fitting-Upper FR69
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 69
Manpower Resources
Manhours
 1.50
Minimum number of person
 1
Subtask elapsed time
 1.50
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)
 Task 53-43-11-000-801
Structural Repair Manual (SRM)
 51-42-00
Fig. A-GBBAA
Removal/Installation of the Covers for
Modification of FR67 and FR69 at the
Location of the Door Support Fittings-
Upper
Sheet 01
Sheet 02
Sheet 03
Sheet 04
(a) Remove the cover at Frame 69 to get access to the modification area, refer to Fig.
A-GBBAA Sheet 01
,V i e wA ,Fig. A-GBBAA Sheet 02
 and Fig. A-GBBAA Sheet 03
 ,
View C and in accordance with SRM 51-42-00:
1
 Remove:
1 Cover Item (53) Retain
attached with:
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 21
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SERVICE BULLETIN
1 Screw Item (55) Retain
1 Washer Item (56) Retain
and as per the applicable alternative installation shown on Fig. A-GBBAA
Sheet 03
,V i e wC ,w i t h :
8 Rivet Item (50) Discard
or
7 Rivet Item (50) Discard
2
 Remove the old sealant with a plastic scrapper.
3
 Clean the work area with:
Textile-Lint Free
Cotton
14SBA1 As required
made moist with:
Non Aqueous
Cleaner-General
08BAA9 As required
(b) Remove the section between Frame 69 and Frame 71 to get access to the
modification area, refer to Fig. A-GBBAA Sheet 01
 , View A and Fig. A-GBBAA
Sheet 04
, View D and in accordance with SRM 51-42-00:
1
 Remove:
1 Section Item (54) Retain
attached with:
4 Screw NAS1102E3-8 Item (55) Retain
4 Washer NAS1169-10L Item (56) Retain
3 Nut NAS1291C3M Item (58) Retain
3 Washer NAS1149D1165K Item (57) Retain
1 Screw NAS1102E08-7 Item (59) Retain
1 Washer NAS1169C8L Item (60) Retain
2
 Remove the old sealant with a plastic scrapper.
3
 Clean the work area with:
Textile-Lint Free
Cotton
14SBA1 As required
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 22
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SERVICE BULLETIN
made moist with:
Non Aqueous
Cleaner-General
08BAA9 As required
4
CAUTION
: DO NOT REMOVE THE ATTACHMENT PARTS OF THE RH
SUPPORT STRUTS AT FRAME 67 AND FRAME 69 AT THE
SAME TIME. IF YOU DO NOT SUPPORT THE CABIN
FLOOR STRUCTURE BEFORE THE REMOVAL OF TWO
ADJACENT STRUTS, YOU CAN CAUSE STRUCTURAL
FAILURE OF THE CABIN FLOOR STRUCTURE.
Remove the lower attachment parts of the RH support strut at Frame 69, refer
to AMM Task 53-43-11-000-801.
5
 Move the lower end of the support strut to get access to the modification area.
(4) Subtask 534238-831-202- 001 - Remove the Fasteners and the Support Assemblies
at the Bulk Cargo Door FR69
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 69
Manpower Resources
Manhours
 1.50
Minimum number of person
 1
Subtask elapsed time
 1.50
Skills
 AIRFRAME
References
Fig. A-GBAAA
Modification of the Bulk Cargo Door
Frames at FR67 and FR69
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
CAUTION
: MAKE SURE THAT THE FASTENER HOLE EDGE DISTANCE IS
CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO
AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION
AREA.
(a) Remove the fasteners and the support assembly at the bulk cargo doorFrame 69.
1
 At Frame 69 between positions STGR38 and STGR45 remove, as shown on
Fig. A-GBAAA Sheet 01
 , View A and Fig. A-GBAAA Sheet 02
 ,V i e wBa n d
Section B-B:
20 Nut NAS1726-4E Item (7) Discard
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 23
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SERVICE BULLETIN
10 Bolt NSA5031-4-5 Item (10) Discard
10 Bolt NSA5031-4-7 Item (11) Discard
5 Support Assy A5397802600600 Item (20) Retain
(b) Remove the fasteners and the spigot assembly at the bulk cargo door Frame 69.
1
 At Frame 69 at position STGR44 remove, as shown on Fig. A-GBAAA Sheet
01
, View A and Fig. A-GBAAA Sheet 02
 , View B, Section C-C and Fig. A-
GBAAA Sheet 03
 View E:
2 Nut NAS1726-4E Item (7) Discard
2 Bolt NSA5031-4-7 Item (11) Discard
2 Bolt NSA5031-3-10 Item (9) Discard
2 Nut NAS1726-3E Item (6) Discard
2 Pin Hi-Lok DAN6-5-6 Item (17) Discard
2 Collar NSA5075W5 Item (15) Discard
1 Spigot Assy-Latch F 5347598000400 Item (21) Retain
1 Plate-Serrated A5397805220800 Item (25) Retain
1 Plate-Serrated A5397805221200 Item (26) Retain
2 Bush F5327127020200 Item (1) Discard
2 Bush F5327127020800 Item (32) Discard
(5) Subtask 534238-250-201-001 - Do the Eddy Current Rotating Probe Inspection of
the Fastener Holes at FR67
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 67
Manpower Resources
Manhours
 1.00
Minimum number of person
 1
Subtask elapsed time
 1.00
Skills
 NON DESTRUCTIVE
TESTING
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 24
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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
Non Destructive Test Manual (NTM)
 Task 51-10-01-250-801 Procedure A
Service Bulletin (SB)
 A340-53-4239
Fig. A-GBAAA
Modification of the Bulk Cargo Door
Frames at FR67 and FR69
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
NOTE
: If this Service Bulletin is applied at the same time as Inspection Service
Bulletin No. A340-53-4239, then this subtask is not necessary.
(a) Clean the working area Frame 67 with:
Non Aqueous
Cleaner-General
08BAA9 As required
and
Textile-Lint Free
Cotton
14SBA1 As required
(b) Do the Eddy Current Rotating Probe Testing of the support fittings and the frame
holes at Frame 67 between positions STGR37 and STGR43, as shown on Fig. A-
GBAAA Sheet 04
 and in accordance with NTM Task 51-10-01-250-801 Procedure
A.
1
 In case of no crack finding, continue with the accomplishment of the
modification.
2
 In case of crack finding, contact AIRBUS.
(6) Subtask 534238-250-202-001 - Do the Eddy Current Rotating Probe Inspection of
the Fastener Holes at FR69
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 69
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 25
6
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### Page 30

@A340
SERVICE BULLETIN
Manpower Resources
Manhours
 1.00
Minimum number of person
 1
Subtask elapsed time
 1.00
Skills
 NON DESTRUCTIVE
TESTING
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
Non Destructive Test Manual (NTM)
 Task 51-10-01-250-801 Procedure A
Service Bulletin (SB)
 A340-53-4239
Fig. A-GBAAA
Modification of the Bulk Cargo Door
Frames at FR67 and FR69
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
NOTE
: If this Service Bulletin is applied at the same time as Inspection Service
Bulletin No. A340-53-4239, then this subtask is not necessary.
(a) Clean the working area Frame 69 with:
Non Aqueous
Cleaner-General
08BAA9 As required
and
Textile-Lint Free
Cotton
14SBA1 As required
(b) Do the Eddy Current Rotating Probe Testing of the support fittings and the frame
holes at Frame 69 between positions STGR38 and STGR45, as shown on Fig. A-
GBAAA Sheet 02
 and Fig. A-GBAAA Sheet 03
 and in accordance with NTM Task
51-10-01-250-801 Procedure A.
1
 In case of no crack finding, continue with the accomplishment of the
modification.
2
 In case of crack finding, contact AIRBUS.
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 26
6
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### Page 31

@A340
SERVICE BULLETIN
(7) Subtask 534238-831-203-001 - Do the Cold Working Process of the Fastener Holes
at FR67 (Fuselage Frame Only)
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 67
Manpower Resources
Manhours
 3.00
Minimum number of person
 1
Subtask elapsed time
 3.00
Skills
 AIRFRAME
Material necessary to do the job
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Wash Primer
 04CMA2
 As required
Non Aqueous Cleaner-
General
08BAA9
 As required
Textile-Lint Free Cotton
 14SBA1
 As required
Standard tool TOOLD01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA340534238-1
 Durable Tooling
 1
 (1)
EKA340534238-1
 Expendable Tooling
 1
 (2)
FTIA340534238-1
 Capital Tooling
 1
 (3)
NOTE
: Fatigue Technology Incorporated (FTI) has allocated the following tool kit
numbers for cold expansion:
For the definition of capital, durable and expendable tools, refer to ISI
51.48.00001.
NOTE
 (1)
: Durable Tooling: Ref. DKA340534238-1
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to SIL
51-012 (corresponding to ISI 51.48.00001).
NOTE
 (2)
: Expendable Tooli ng: Ref. EKA340534238-1
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 27
6
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### Page 32

@A340
SERVICE BULLETIN
NOTE
 (3)
: Capital Tooling: Ref. FTIA340534238-1
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operators’ stock as a long-
term investment or can be loaned from FTI.
Standard tool TOOLD02
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA340534238-1
 Durable Tooling
 1
 (1)
EKA340534238-1
 Expendable Tooling
 1
 (2)
WCIA340534238-1
 Capital Tooling
 1
 (3)
NOTE
: West Coast Industries (WCI) has allocated the following tool kit numbers
for cold expansion:
For the definition of capital, durable and expendable tools, refer to ISI
51.48.00001.
NOTE
 (1)
: Durable Tooling: Ref. DKA340534238-1
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to SIL
51-012 (corresponding to ISI 51.48.00001).
NOTE
 (2)
: Expendable Tooli ng: Ref. EKA340534238-1
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
NOTE
 (3)
: Capital Tooling: Ref. WCIA340534238-1
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operators’ stock as a long
term investment or can be loaned from WCI.
References
Consumable Material List (CML)
Structural Repair Manual (SRM)
 51-48-00
Fig. A-GBAAA
Modification of the Bulk Cargo Door
Frames at FR67 and FR69
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 28
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 33

@A340
SERVICE BULLETIN
CAUTION
: MAKE SURE THAT THE FASTENER HOLE EDGE DISTANCE IS
CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO
AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION
AREA.
(a) Clean the working area with:
Non Aqueous
Cleaner-General
08BAA9 As required
and
Textile-Lint Free
Cotton
14SBA1 As required
(b) Measure the size of the fastener holes and define the next stage of drill hole
diameter in accordance with SRM 51-48-00 for cold working and as shown on Fig.
A-GBAAA Sheet 06
.
(c) Drill and ream the fastener holes for cold working with the correct start drill/reamer,
refer to Fig. A-GBAAA Sheet 06
 .
(d) Cold expand the fastener holes in accordance with SRM 51-48-00 and Fig. A-
GBAAA Sheet 04
, Views F, G and H:
1
 Refer to FTI tool list No.
DKA340534238-1 Durable Tooling 1
or
Refer to WCI tool list No.
DKA340534238-1 Durable Tooling 1
2
 Clean the working area with:
Non Aqueous
Cleaner-General
08BAA9 As required
and
Textile-Lint Free
Cotton
14SBA1 As required
3
 Install the sleeves in accordance with SRM 51-48-00.
Refer to FTI tool list No.
EKA340534238-1 Expendable Tooling 1
or
Refer to WCI tool list No.
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 29
6
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### Page 34

@A340
SERVICE BULLETIN
EKA340534238-1 Expendable Tooling 1
4
 Do the cold expansion of the fastener holes in accordance with SRM
51-48-00.
Refer to FTI tool list No.
FTIA340534238-1 Capital Tooling 1
or
Refer to WCI tool list No.
WCIA340534238-1 Capital Tooling 1
5
 Remove the sleeves.
6
 Ream and deburr the fastener holes with the correct gage finish reamer refer
to Fig. A-GBAAA Sheet 06
 and in accordance with SRM 51-48-00.
Refer to FTI tool list No.
DKA340534238-1 Durable Tooling 1
or
Refer to WCI tool list No.
DKA340534238-1 Durable Tooling 1
7
 Clean the drilled area with:
Non Aqueous
Cleaner-General
08BAA9 As required
and
Textile-Lint Free
Cotton
14SBA1 As required
8
 Apply protection to the frame fastener holes with:
Wash Primer 04CMA2 As required
(8) Subtask 534238-831-204-001 - Do the Cold Working Process of the Fastener Holes
at FR69 (Fuselage Frame Only)
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 69
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 30
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 35

@A340
SERVICE BULLETIN
Manpower Resources
Manhours
 3.00
Minimum number of person
 1
Subtask elapsed time
 3.00
Skills
 AIRFRAME
Material necessary to do the job
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Wash Primer
 04CMA2
 As required
Non Aqueous Cleaner-
General
08BAA9
 As required
Textile-Lint Free Cotton
 14SBA1
 As required
Standard tool TOOLD01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA340534238-1
 Durable Tooling
 1
 (1)
EKA340534238-1
 Expendable Tooling
 1
 (2)
FTIA340534238-1
 Capital Tooling
 1
 (3)
NOTE
: Fatigue Technology Incorporated (FTI) has allocated the following tool kit
numbers for cold expansion:
For the definition of capital, durable and expendable tools, refer to ISI
51.48.00001.
NOTE
 (1)
: Durable Tooling: Ref. DKA340534238-1
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to SIL
51-012 (corresponding to ISI 51.48.00001).
NOTE
 (2)
: Expendable Tooli ng: Ref. EKA340534238-1
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
NOTE
 (3)
: Capital Tooling: Ref. FTIA340534238-1
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operators’ stock as a long-
term investment or can be loaned from FTI.
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 31
6
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### Page 36

@A340
SERVICE BULLETIN
Standard tool TOOLD02
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA340534238-1
 Durable Tooling
 1
 (1)
EKA340534238-1
 Expendable Tooling
 1
 (2)
WCIA340534238-1
 Capital Tooling
 1
 (3)
NOTE
: West Coast Industries (WCI) has allocated the following tool kit numbers
for cold expansion:
For the definition of capital, durable and expendable tools, refer to ISI
51.48.00001.
NOTE
 (1)
: Durable Tooling: Ref. DKA340534238-1
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to SIL
51-012 (corresponding to ISI 51.48.00001).
NOTE
 (2)
: Expendable Tooli ng: Ref. EKA340534238-1
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
NOTE
 (3)
: Capital Tooling: Ref. WCIA340534238-1
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operators’ stock as a long
term investment or can be loaned from WCI.
References
Consumable Material List (CML)
Structural Repair Manual (SRM)
 51-48-00
Fig. A-GBAAA
Modification of the Bulk Cargo Door
Frames at FR67 and FR69
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
CAUTION
: MAKE SURE THAT THE FASTENER HOLE EDGE DISTANCE IS
CORRECT BEFORE INSTALLATION OF THE FINAL FASTENERS TO
AVOID EXTENSIVE REPAIRS IN THE FUSELAGE MODIFICATION
AREA.
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 32
6
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### Page 37

@A340
SERVICE BULLETIN
(a) Clean the working area with:
Non Aqueous
Cleaner-General
08BAA9 As required
and
Textile-Lint Free
Cotton
14SBA1 As required
(b) Measure the size of the fastener holes and define the next stage of drill hole
diameter in accordance with SRM 51-48-00 for cold working and as shown on Fig.
A-GBAAA Sheet 06
.
(c) Drill and ream the fastener holes for cold working with the correct start drill/reamer,
refer to Fig. A-GBAAA Sheet 06
 .
(d) Cold expand the fastener holes in accordance with SRM 51-48-00 and Fig. A-
GBAAA Sheet 02
,V i e wBa n dFig. A-GBAAA Sheet 03
 Views C and D:
1
 Refer to FTI tool list No.
DKA340534238-1 Durable Tooling 1
or
Refer to WCI tool list No.
DKA340534238-1 Durable Tooling 1
2
 Clean the working area with:
Non Aqueous
Cleaner-General
08BAA9 As required
and
Textile-Lint Free
Cotton
14SBA1 As required
3
 Install the sleeves in accordance with SRM 51-48-00.
Refer to FTI tool list No.
EKA340534238-1 Expendable Tooling 1
or
Refer to WCI tool list No.
EKA340534238-1 Expendable Tooling 1
4
 Do the cold expansion of the fastener holes in accordance with SRM
51-48-00.
Refer to FTI tool list No.
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 33
6
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### Page 38

@A340
SERVICE BULLETIN
FTIA340534238-1 Capital Tooling 1
or
Refer to WCI tool list No.
WCIA340534238-1 Capital Tooling 1
5
 Remove the sleeves.
6
 Ream and deburr the fastener holes with the correct gage finish reamer refer
to Fig. A-GBAAA Sheet 06
 and in accordance with SRM 51-48-00.
Refer to FTI tool list No.
DKA340534238-1 Durable Tooling 1
or
Refer to WCI tool list No.
DKA340534238-1 Durable Tooling 1
7
 Clean the drilled area with:
Non Aqueous
Cleaner-General
08BAA9 As required
and
Textile-Lint Free
Cotton
14SBA1 As required
8
 Apply protection to the frame fastener holes with:
Wash Primer 04CMA2 As required
(9) Subtask 534238-831-205- 001 - Do the Installation of the Support and Spigot
Assemblies at FR67
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 67
Manpower Resources
Manhours
 3.00
Minimum number of person
 1
Subtask elapsed time
 3.00
Skills
 AIRFRAME
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 34
6
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### Page 39

@A340
SERVICE BULLETIN
Material necessary to do the job
Kit 534238D01R03
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 F5327127020200
 2
 BUSH
3
 NAS1149C0332R
 2
 WASHER
4
 NAS1149C0432R
 2
 WASHER
5
 F5347598420000
 1
 TAPE
6
 NAS1726-3E
 2
 NUT
7
 NAS1726-4E
 22
 NUT
9
 NSA5031-3-10
 2
 BOLT
10
 ABS0114T4-5Y
 10
 BOLT
11
 ABS0114T4-7Y
 10
 BOLT
13
 NSA5031-4-10
 2
 BOLT
14
 DIN65399-2412BF
 2
 RIVET
15
 NSA5075W6
 2
 COLLAR
17
 DAN6-6-6
 2
 PIN
32
 F5327127020800
 2
 BUSH
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Wash Primer
 04CMA2
 As required
Polysulfide Sealant-General
Purpose Interfay
06AAC1
 As required
Non Hardening Jointing
Putty
06LCB1
 As required
Non Aqueous Cleaner-
General
08BAA9
 As required
Textile-Lint Free Cotton
 14SBA1
 As required
References
Aircraft Maintenance Manual (AMM)
 Task 52-33-32-400-801
Consumable Material List (CML)
Structural Repair Manual (SRM)
 51-24-00
51-44-00
Fig. A-GBAAA
Modification of the Bulk Cargo Door
Frames at FR67 and FR69
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
(a) Clean the installation areas with:
Non Aqueous
Cleaner-General
08BAA9 As required
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 35
6
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### Page 40

@A340
SERVICE BULLETIN
and
Textile-Lint Free
Cotton
14SBA1 As required
(b) Oversize to clearance fit the 4 fastener holes in the Support Assembly, Item (19), in
accordance with SRM 51-44-00.
Refer to Fig. A-GBAAA Sheet 04
 , View F, Section D-D.
(c) Apply protection to the support assembly fastener holes with:
Wash Primer 04CMA2 As required
(d) Do the installation of the support assembly on the fuselage Frame 67 between
positions STGR37 and STGR43:
1
 Apply:
Polysulfide Sealant-
General Purpose
Interfay
06AAC1 As required
In accordance with SRM 51-24-00 and refer to Fig. A-GBAAA Sheet 04
 ,V i e w
F, Section D-D.
Install:
5 Support Assy A5397802600400 Item (19) Retained at
removal
10 Bolt ABS0114T4-5Y Item 10
10 Bolt ABS0114T4-7Y Item 11
20 Nut NAS1726-4E Item 7
NOTE
: Wet assemble the Bolts, Items 10 and 11, with:
Non Hardening
Jointing Putty
06LCB1 As required
2
 Do the adjustment/test procedure as specified in the installation of the support
assembly before you apply the torque to the Nuts, Item 7, refer to AMM
52-33-32-400-801.
3
 Torque the Nuts, Item 7, to between 0.70 and 0.80 daNm (62 and 71 lbf in).
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 36
6
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### Page 41

@A340
SERVICE BULLETIN
(e) Do the installation of the spigot assembly on the fuselage Frame 67 at position
STGR42A, refer to Fig. A-GBAAA Sheet 04
 , View F, Section E-E and Fig. A-
GBAAA Sheet 05
,V i e wJ :
1
 Install:
2 Bush F5327127020200 Item 1
2 Bush F5327127020800 Item 32
2
 Final Drill/Ream, refer to Fig. A-GBAAA Sheet 04
 , View F, Section E-E and
Fig. A-GBAAA Sheet 05
 ,V i e wJ .
3
 Apply:
Polysulfide Sealant-
General Purpose
Interfay
06AAC1 As required
In accordance with SRM 51-24-00 and refer to Fig. A-GBAAA Sheet 04
 ,V i e w
F, Section E-E and Fig. A-GBAAA Sheet 05
 ,V i e wJ .
Install:
1 Spigot Assy-Lat ch F5347597600600 Item (23) Retained at
removal
1 Plate-Serrated A5397805220800 Item (25) Retained at
removal
1 Plate-Serrated A5397805221200 Item (26) Retained at
removal
2 Bolt NSA5031-4-10 Item 13
2 Washer NAS1149C0432R Item 4
2 Nut NAS1726-4E Item 7
2 Pin Hi-Lok DAN6-6-6 Item 17
2 Collar NSA5075W6 Item 15
2 Bolt NSA5031-3-10 Item 9
2 Washer NAS1149C0332R Item 3
2 Nut NAS1726-3E Item 6
NOTE
: Wet assemble the Bolts, Items 9 and 13, and the Pins Hi-Lok,
Item 17, with:
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 37
6
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### Page 42

@A340
SERVICE BULLETIN
Non Hardening
Jointing Putty
06LCB1 As required
4
 Do the adjustment/test procedure as specified in the installation of the support
assembly before you apply the torque to the Nuts, Items 6 and 7, refer to
AMM 52-33-32-400-801.
5
 Torque the Nuts, Item 6, to between 0.35 and 0.45 daNm (31 and 39.9 lbf in).
6
 Torque the Nuts, Item 7, to between 0.70 and 0.80 daNm (62 and 71 lbf in).
(f) Install (if necessary):
Refer to Fig. A-GBAAA Sheet 04
 , View F, Section F-F:
1 Tape F5347598420000 Item 5
(g) Apply:
Polysulfide Sealant-
General Purpose
Interfay
06AAC1 As required
In accordance with SRM 51-24-00 and refer to Fig. A-GBAAA Sheet 04
 ,V i e wF .
Install:
1 Nut-Plate MS21059L06 Item (27) Retained at
removal
with
2 Rivet DIN65399-2412BF Item 14
(10) Subtask 534238-831- 206-001 - Do the Installation of the Support and Spigot
Assemblies at FR69
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 69
Manpower Resources
Manhours
 3.00
Minimum number of person
 1
Subtask elapsed time
 3.00
Skills
 AIRFRAME
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 38
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 43

@A340
SERVICE BULLETIN
Material necessary to do the job
Kit 534238D01R03
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 F5327127020200
 2
 BUSH
3
 NAS1149C0332R
 2
 WASHER
4
 NAS1149C0432R
 2
 WASHER
6
 NAS1726-3E
 2
 NUT
7
 NAS1726-4E
 22
 NUT
8
 NSA5031-3-8
 2
 BOLT
10
 ABS0114T4-5Y
 10
 BOLT
11
 ABS0114T4-7Y
 10
 BOLT
12
 NSA5031-4-8
 2
 BOLT
15
 NSA5075W6
 2
 COLLAR
17
 DAN6-6-6
 2
 PIN
32
 F5327127020800
 2
 BUSH
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Wash Primer
 04CMA2
 As required
Polysulfide Sealant-General
Purpose Interfay
06AAC1
 As required
Non Hardening Jointing
Putty
06LCB1
 As required
Non Aqueous Cleaner-
General
08BAA9
 As required
Textile-Lint Free Cotton
 14SBA1
 As required
References
Aircraft Maintenance Manual (AMM)
 Task 52-33-32-400-801
Consumable Material List (CML)
Structural Repair Manual (SRM)
 51-24-00
51-44-00
Fig. A-GBAAA
Modification of the Bulk Cargo Door
Frames at FR67 and FR69
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
(a) Clean the installation areas with:
Non Aqueous
Cleaner-General
08BAA9 As required
and
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 39
6
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### Page 44

@A340
SERVICE BULLETIN
Textile-Lint Free
Cotton
14SBA1 As required
(b) Oversize to clearance fit the 4 fastener holes in the Support Assembly, Item (20), in
accordance with SRM 51-44-00.
Refer to Fig. A-GBAAA Sheet 02
 ,V i e wB ,S e c t i o nB - B .
(c) Apply protection to the support assembly fastener holes with:
Wash Primer 04CMA2 As required
(d) Do the installation of the support assembly on the fuselage Frame 69 between
positions STGR38 and STGR45:
1
 Apply:
Polysulfide Sealant-
General Purpose
Interfay
06AAC1 As required
In accordance with SRM 51-24-00 and refer to Fig. A-GBAAA Sheet 02
 ,V i e w
B, Section B-B.
Install:
5 Support Assy A5397802600600 Item (20) Retained at
removal
10 Bolt ABS0114T4-5Y Item 10
10 Bolt ABS0114T4-7Y Item 11
20 Nut NAS1726-4E Item 7
NOTE
: Wet assemble the Bolts, Items 10 and 11, with:
Non Hardening
Jointing Putty
06LCB1 As required
2
 Do the adjustment/test procedure as specified in the installation of the support
assembly before you apply the torque to the Nuts, Item 7, refer to AMM
52-33-32-400-801.
3
 Torque the Nuts, Item 7, to between 0.70 and 0.80 daNm (62 and 71 lbf in).
(e) Do the installation of the spigot assembly on the fuselage Frame 69 at position
STGR44:
1
 Install:
2 Bush F5327127020200 Item 1
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 40
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SERVICE BULLETIN
2 Bush F5327127020800 Item 32
2
 Final Drill/Ream, refer to Fig. A-GBAAA Sheet 02
 , View B, Section C-C and
Fig. A-GBAAA Sheet 03
 ,V i e wE .
3
 Apply:
Polysulfide Sealant-
General Purpose
Interfay
06AAC1 As required
In accordance with SRM 51-24-00 and refer to Fig. A-GBAAA Sheet 02
 ,V i e w
B, Section C-C and Fig. A-GBAAA Sheet 03
 ,V i e wE .
Install:
1 Spigot Assy-Lat ch F5347598000400 Item (21) Retained at
removal
1 Plate-Serrated A5397805220800 Item (25) Retained at
removal
1 Plate-Serrated A5397805221200 Item (26) Retained at
removal
2 Bolt NSA5031-4-8 Item 12
2 Washer NAS1149C0432R Item 4
2 Nut NAS1726-4E Item 7
2 Pin Hi-Lok DAN6-6-6 Item 17
2 Collar NSA5075W6 Item 15
2 Bolt NSA5031-3-8 Item 8
2 Washer NAS1149C0332R Item 3
2 Nut NAS1726-3E Item 6
NOTE
: Wet assemble the Bolts, Items 8 and 12, and the Pins Hi-Lok,
Item 17, with:
Polysulfide Sealant-
General Purpose
Interfay
06AAC1 As required
4
 Do the adjustment/test procedure as specified in the installation of the support
assembly before you apply the torque to the Nuts, Items 6 and 7, refer to
AMM 52-33-32-400-801.
5
 Torque the Nuts, Item 6, to between 0.35 and 0.45 daNm (31 and 39.9 lbf in).
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 41
6
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SERVICE BULLETIN
6
 Torque the Nuts, Item 7, to between 0.70 and 0.80 daNm (62 and 71 lbf in).
(11) Subtask 534238-930- 201-001 - Re-identify the Support Assembly and Serrated
Plate on FR67
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 67
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 AIRFRAME
Material necessary to do the job
Reidentified part set REIDD01
ITEM
 NEW PART N˚
 KEYWORD
 ITEM
 OLD PART N˚
 SEE
NOTES
19
 A5397802600800
 SUPPORT
 (19)
 A5397802600400
26
 A5397805221600
 PLATE
 (26)
 A5397805221200
References
Process and Material Specification
(PMS)
Process and Material Specification (PMS)
01-06-12
(a) Re-identify the items that follow, refer to Process and Material Specification (PMS)
01-06-12:
1 Support Assy A5397802600400 Item (19)
becomes:
1 Support Assy A5397802600800 Item 19
and
1 Plate-Serrated A5397805221200 Item (26)
becomes:
1 Plate-Serrated A5397805221600 Item 26
(12) Subtask 534238-930- 202-001 - Re-identify the Support Assembly on FR69
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 69
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 42
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Manpower Resources
Manhours
 0.25
Minimum number of person
 1
Subtask elapsed time
 0.25
Skills
 AIRFRAME
Material necessary to do the job
Reidentified part set REIDD02
ITEM
 NEW PART N˚
 KEYWORD
 ITEM
 OLD PART N˚
 SEE
NOTES
20
 A5397802601000
 SUPPORT
 (20)
 A5397802600600
References
Process and Material Specification
(PMS)
Process and Material Specification (PMS)
01-06-12
(a) Re-identify the item that follows, refer to Process and Material Specification (PMS)
01-06-12:
1 Support Assy A5397802600600 Item (20)
becomes:
1 Support Assy A5397802601000 Item 20
(13) Subtask 534238-914-201-001 - Apply the Sealants and Corrosion Preventive
Compounds to the Support and Spigot Assemblies at FR67 and FR69
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 67
Frame 69
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
Coating-Flexible Structure
 04QAB2
 As required
Polysulfide Sealant-General
Purpose Fillet
06AAB1
 As required
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 43
6
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### Page 48

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ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Corrosion Preventive
Compound-Hard
12ABB1
 As required
Corrosion Preventive
Compound-Soft
12ABC1
 As required
References
Consumable Material List (CML)
Structural Repair Manual (SRM)
 51-23-12
51-75-12
Fig. A-GBAAA
Modification of the Bulk Cargo Door
Frames at FR67 and FR69
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
NOTE
: Do this subtask after the adjustment/test procedure as specified in
SUBTASK 534238-700-201 001 Test .
(a) Apply the Sealants and Corrosion Preventive Compounds.
Refer to Fig. A-GBAAA Sheet 02
 , Fig. A-GBAAA Sheet 03
 , Fig. A-GBAAA Sheet 04
and Fig. A-GBAAA Sheet 05
 .
1
 Do a fillet seal around the support assembly with:
Polysulfide Sealant-
General Purpose
Fillet
06AAB1 As required
2
 Renew the protective finish:
Refer to Fig. A-GBAAA Sheet 02
 , Fig. A-GBAAA Sheet 03
 , Fig. A-GBAAA
Sheet 04
 and Fig. A-GBAAA Sheet 05
 and in accordance with SRM 51-75-12:
Coating-Flexible
Structure
04QAB2 As required
3
 Apply corrosion preventive compound to all exposed surfaces:
Refer to Fig. A-GBAAA Sheet 02
 , Fig. A-GBAAA Sheet 03
 , Fig. A-GBAAA
Sheet 04
 and Fig. A-GBAAA Sheet 05
 and in accordance with SRM 51-23-12:
Corrosion
Preventive
Compound-Soft
12ABC1 As required
or
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 44
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SERVICE BULLETIN
Corrosion
Preventive
Compound-Hard
12ABB1 As required
(14) Subtask 534238-410-201-001 - Install the Items Removed for Access at the
Location of the Door Support Fitting-Upper FR67
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 67
Manpower Resources
Manhours
 1.00
Minimum number of person
 1
Subtask elapsed time
 1.00
Skills
 AIRFRAME
Material necessary to do the job
Component COMPD01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
50
 DIN65399-4020BF
 8
 RIVET
52
 NAS1921B05S03U
 3
 RIVET
NOTE
: The above list of components is not an AIRBUS Kit, the required parts
shall be ordered as necessary through the given channel.
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Primer Epoxy Paint-
Corrosion Inhibiting
04DAB2
 As required
Top Coat Polyurethane-
Gray Internal Structure
04JME4
 As required
Polysulfide Sealant-General
Purpose Brushable
06AAA1
 As required
Non Aqueous Cleaner-
General
08BAA9
 As required
Corrosion Preventive
Compound-Hard
12ABB1
 As required
Corrosion Preventive
Compound-Soft
12ABC1
 As required
Textile-Lint Free Cotton
 14SBA1
 As required
References
Aircraft Maintenance Manual (AMM)
 Task 53-43-11-400-801
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 45
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References
Structural Repair Manual (SRM)
 51-24-00
51-42-00
51-75-12
Fig. A-GBBAA
Removal/Installation of the Covers for
Modification of FR67 and FR69 at the
Location of the Door Support Fittings-
Upper
Sheet 01
Sheet 02
Sheet 03
Sheet 04
(a) Install the lower attachment parts of the RH support strut at Frame 67, refer to
AMM Task 53-43-11-400-801.
(b) Install the cover at Frame 67, refer to Fig. A-GBBAA Sheet 01
 ,V i e wAa n d Fig.
A-GBBAA Sheet 02
 , View B and in accordance with SRM 51-24-00 and SRM
51-42-00:
1
 Wet install the rivets in the step below with:
Polysulfide Sealant-
General Purpose
Brushable
06AAA1 As required
2
 Install:
1 Cover Item (51) Retained at
removal
attach with:
8 Rivet DIN65399-4020BF Item 50
3 Rivet NAS1921B05S03U Item 52
3
 Clean the work area with:
Textile-Lint Free
Cotton
14SBA1 As required
made moist with:
Non Aqueous
Cleaner-General
08BAA9 As required
4
 Renew the protective finish of the rivets in accordance with SRM 51-75-12:
Primer Epoxy Paint-
Corrosion Inhibiting
04DAB2 As required
Top Coat
Polyurethane-Gray
Internal Structure
04JME4 As required
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 46
6
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5
 Apply to all exposed surfaces which you touched or moved:
Corrosion
Preventive
Compound-Soft
12ABC1 As required
or
Corrosion
Preventive
Compound-Hard
12ABB1 As required
(15) Subtask 534238-410-202-001 - Install the Items Removed for Access at the
Location of the Door Support Fitting-Upper FR69
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 69
Manpower Resources
Manhours
 1.50
Minimum number of person
 1
Subtask elapsed time
 1.50
Skills
 AIRFRAME
Material necessary to do the job
Component COMPD01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
50
 DIN65399-4020BF
 8
 RIVET
NOTE
: The above list of components is not an AIRBUS Kit, the required parts
shall be ordered as necessary through the given channel.
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Primer Epoxy Paint-
Corrosion Inhibiting
04DAB2
 As required
Top Coat Polyurethane-
Gray Internal Structure
04JME4
 As required
Polysulfide Sealant-General
Purpose Fillet
06AAB1
 As required
Non Aqueous Cleaner-
General
08BAA9
 As required
Corrosion Preventive
Compound-Hard
12ABB1
 As required
Corrosion Preventive
Compound-Soft
12ABC1
 As required
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 47
6
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SERVICE BULLETIN
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Textile-Lint Free Cotton
 14SBA1
 As required
References
Aircraft Maintenance Manual (AMM)
 Task 53-43-11-400-801
Structural Repair Manual (SRM)
 51-24-00
51-42-00
51-75-12
Fig. A-GBBAA
Removal/Installation of the Covers for
Modification of FR67 and FR69 at the
Location of the Door Support Fittings-
Upper
Sheet 01
Sheet 02
Sheet 03
Sheet 04
(a) Install the lower attachment parts of the RH support strut at Frame 69, refer to
AMM Task 53-43-11-400-801.
(b) Install the section between Frame 69 and Frame 71, refer to Fig. A-GBBAA Sheet
01
, View A and Fig. A-GBBAA Sheet 04
 , View D and in accordance with SRM
51-24-00 and SRM 51-42-00:
1
 Apply between the structure at Frame 69 and the Section, item (54):
Polysulfide Sealant-
General Purpose
Fillet
06AAB1 As required
2
 Install:
1 Cover Item (54) Retained at
removal
attach with:
4 Screw NAS1102E3-8 Item (55) Retained at
removal
4 Washer NAS1169-10L Item (56) Retained at
removal
3 Nut NAS1291C3M Item (58) Retained at
removal
3 Washer NAS1149D1165K Item (57) Retained at
removal
1 Screw NAS1102E08-7 Item (59) Retained at
removal
1 Washer NAS1169C8L Item (60) Retained at
removal
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 48
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(c) Install the cover at Frame 69, refer to Fig. A-GBBAA Sheet 01
 ,V i e wAa n d Fig.
A-GBBAA Sheet 03
 , View C and in accordance with SRM 51-24-00 and SRM
51-42-00:
1
 Install:
1 Cover Item (53) Retained at
removal
attach with:
1 Screw NAS1102E3-8 Item (55) Retained at
removal
1 Washer NAS1169-10L Item (56) Retained at
removal
and as per the applicable alternative installation shown on Fig. A-GBBAA
Sheet 03
,V i e wC ,w i t h :
8 Rivet DIN65399-4020BF Item 50
or
7 Rivet DIN65399-4020BF Item 50
2
 Clean the work area with:
Textile-Lint Free
Cotton
14SBA1 As required
made moist with:
Non Aqueous
Cleaner-General
08BAA9 As required
3
 Renew the protective finish of the rivets in accordance with SRM 51-75-12:
Primer Epoxy Paint-
Corrosion Inhibiting
04DAB2 As required
Top Coat
Polyurethane-Gray
Internal Structure
04JME4 As required
4
 Apply to all exposed surfaces which you touched or moved:
Corrosion
Preventive
Compound-Soft
12ABC1 As required
or
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 49
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SERVICE BULLETIN
Corrosion
Preventive
Compound-Hard
12ABB1 As required
D. TEST
(1) Subtask 534238-700-201-001 - Test
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 67
Frame 69
Manpower Resources
Skills
 AIRFRAME
References
Aircraft Maintenance Manual (AMM)
 Task 52-33-32-400-801
Task 52-33-32-400-802
(a) Do the adjustment/test procedure as specified in the installation of the support
assembly, refer to AMM Task 52-33-32-400-801.
(b) Do the operational test procedures as specified in the installation of the latch spigot
assembly, refer to AMM Task 52-33-32-400-802.
E. CLOSE-UP
(1) Subtask 534238-942-201-001 - Close-up
Work Zones and Access Panels
Zone
 Access/Work location
823
 Work location
 Frame 67
Frame 69
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 52-33-32-400-801
Task 52-33-32-400-802
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(b) Do the close-up procedure as specified in the installation of the latch spigot
assembly, refer to AMM Task 52-33-32-400-802.
(c) Do the close-up procedure as specified in the installation of the support assembly,
refer to AMM Task 52-33-32-400-801.
(d) Remove the access platform(s).
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 50
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(e) Put the aircraft back to its initial configuration.
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 51
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**CONF ALL
A
FR69
FR67
A
B
F
STGR43RH
STGR37RH
823
F_SB_534238_6_BAAA_01_01
Figure A-GBAAA - Sheet 01
Modification of the Bulk Cargo Door Frames at FR67 and FR69
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 52
6
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**CONF ALL
E
(10)
(7)
(11)
(20)
10
7
11 x2
x4
x2
10
01
01
02
05
06
04
05
06
B B
TYPICAL
F
W
D
(25)
(21)
4
12
3
8
(26)
6
7
15
17
01
05
06
x2 02
x2 03
x2
x2
04
(7)
(15)
(17)
x2
x2
x2
x2
01
(6)
(9)
(11)
C C
F
W
D
D
C
FR69
STGR38RH
STGR39RH
STGR41RH
STGR43RH
STGR44RH
STGR45RH
B
B
B
B
B
B
B
B
B
B
C
C
B
VIEW LOOKING AFT
FOR NOTES SEE SHEET 05.
FOR FASTENER HOLES, SEE SHEET 06.
NOTE:
12
F_SB_534238_6_BAAA_02_05
Figure A-GBAAA - Sheet 02
Modification of the Bulk Cargo Door Frames at FR67 and FR69
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 53
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SERVICE BULLETIN
**CONF ALL
C
VIEW LOOKING AFT
D
VIEW LOOKING AFT
10.70 mm
(0.421 in)
100.0° TYPICAL
100.0°
12.30 mm
(0.483 in)
9.60 mm
(0.378 in)
4.80 mm
(0.189 in)
2.00 mm
(0.079 in)
1 x2
32 08x2(32)
(1) 07
0.10 mm
(0.004 in) TYPICAL
E
FOR NOTES SEE SHEET 05.
POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION
FOR FASTENER HOLES, SEE SHEET 06.
NOTE:
STGR45RH
STGR43RH
STGR41RH
STGR39RH
STGR38RH
STGR44RH
F_SB_534238_6_BAAA_03_06
Figure A-GBAAA - Sheet 03
Modification of the Bulk Cargo Door Frames at FR67 and FR69
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 54
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**CONF ALL
J 5
FR67
5.00 mm
(0.197 in)
11
F F
15.00 mm
(0.591 in)
D D
05
06
02
H
FR67
VIEW LOOKING
FWD
(27)
(14) 14
04
10
STGR38RH
STGR41RH
STGR43RH
STGR42RH
STGR37RH
D
D
F
G
D
D
D
D
D
D FR67
(23)
(25)
13(11) x2
4 x2
3
9
(26)
6
7
04
05
06
x2
x2
02
03(9)
(7)
x2
x2 (6)
15
17
x2
x2
(15)
(17)
E E
VIEW LOOKING FWD
H
VIEW LOOKING FWD
G
F
F
D
D
STGR42ARH
FOR NOTES SEE SHEET 05.
01
01
(19)
11
7
10
05
06
x2
x4
x2
01
01(11)
(7)
(10)
10
04
F
W
D
F
W
D
F
W
D
I
N
B
D
I
N
B
D
STGR42ARH
STGR43RH
STGR42RH
STGR41RH
STGR38RH
STGR37RH
POSITION OF SPLIT
IN EXPANSION SLEEVE
DURING COLD EXPANSION
FOR FASTENER HOLES, SEE SHEET 06.
NOTE:
E
E
12
F_SB_534238_6_BAAA_04_02
Figure A-GBAAA - Sheet 04
Modification of the Bulk Cargo Door Frames at FR67 and FR69
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 55
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**CONF ALL
NOTE:
TORQUE 0.70 − 0.80 daNm (31 − 39.9 lbf in).
INSTALL WITH JOINT PUTTY MATERIAL No 06LCB1.
02
01
TORQUE 0.35 − 0.45 daNm (62 − 71 lbf in).03
INSTALL WITH INTERFAY SEALANT MATERIAL No 06AAC1.04
AFTER INSTALLATION APPLY FILLET SEALANT MATERIAL No 06AAB1.05
APPLY FLEXIBLE COATING MATERIAL No 04QAB2 AND CORROSION PREVENTATIVE06
6.500 mm (0.2559 in) DRILLING IN BUSH AFTER INSTALLATION.07
5.000 mm (0.1968 in) DRILLING IN BUSH AFTER INSTALLATION.08
AFTER INSTALLATION APPLY CORROSION PREVENTATIVE09
COMPOUND MATERIAL No 12ABC1 TO RIVET HEADS.
COMPOUND MATERIAL No 12ABC1 OR 12ABB1.
REAM HOLES TO 7.130 mm (0.2807 in) MIN TO 7.205 mm (0.2837 in) MAX.10
CHAFING PATCH RENEW IF NECESSARY.11
J
10.70 mm
(0.421 in)
100.0° TYPICAL
0.10 mm
(0.004 in) TYPICAL
100.0°
12.30 mm
(0.484 in)
9.60 mm
(0.378 in)
4.80 mm
(0.189 in)
2.00 mm
(0.079 in)
32 x2
1 x2
08
07
(32)
(1)
F_SB_534238_6_BAAA_05_03
Figure A-GBAAA - Sheet 05
Modification of the Bulk Cargo Door Frames at FR67 and FR69
DATE: Sep 08/17 SERVICE BULLETIN No.: A340-53-4238
REVISION No.: 00 - Sep 08/17 Page: 56
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