# Airbus Service Bulletin A340-57-4138

Copy: No revision named ("A340-57-4138 R01"), 128 pages: PDF https://openairdocs.org/files/sha256/76/2d/762d5e9b028e88f2c5e45f7ff9407cec7c2f8c6dde79337ef13cd08d6bf98e8e; text https://openairdocs.org/service-documents/airbus/a340-57-4138/file/762d5e9b028e.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2018-0113, the docket of AD 2019-16-07. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A340-57-4138
- Page: https://openairdocs.org/service-documents/airbus/a340-57-4138

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a340-57-4138/proposed.md).

## Text (128 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2018-0113, the docket of AD 2019-16-07. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

@A340
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
ATA SYSTEM: 57
TITLE: FUSELAGE - CENTER FUSELAGE - MODIFICATION OF FASTENER
HOLES 12, 14, 260, 261, 262, 263 AT FRAME 40
MODIFICATION No.: 206049S33789
This page transmits Revision No.01 of Service Bulletin No.A340-57-4138
ADDITIONAL WORK
**CONF ALL
REASON
Revision No. 01 issued to:
- Update the EFFECTIVITY paragraph
- Remove the MPD from the PUBLICATION AFFECTED paragraph
- Modify the Service Bulletin structure further to validation on A330 aircraft with Manufacturing Serial
Number (MSN) 0422.
CHANGES
The main changes of this revision are:
- REASON paragr aph has been updated
- GENERAL EVALUATION table has been updated and notes have been added
- PLANNING INFORMATION paragraph has been updated:
. MANPOWER has been updated
. REFERENCES paragraph has been updated.
- MATERIAL INFORMATION paragraph has been updated:
. Update of MATERIAL PRICE AND AVAILABILITY information
. Update of KIT 574138A01R01 and KIT 574138A02R01 to add additional fasteners
. Update of LIST OF MATERIAL - OPERATOR SUPPLIED
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 2

@A340
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
. COMPA01 has been added.
- ACCOMPLISHMENT INSTRUCTIONS paragraph has been updated and modified:
. Warning sentence has been added
. Note has been updated
. Standard Practices paragraph has been updated
. Job Set-up paragraph has been updated
. Removal of additional fasteners for access based on aircraft configurations
. Addition of spotfacing procedure
. Installation of additional fasteners for access based on aircraft configurations
. Test paragraph has been updated to add SUBTASK 574138-790-001-001
. Close up paragraph updated
. Figure A-F BBAA has been updated
. Figures A-FBEAA and A-FBEAB have been updated.
- Manpower Gantt Chart has been updated.
SUMMARY
REASON/DESCRIPTION/OPERATIONAL
CONSEQUENCES
REASON UPDATED
 R
GENERAL EVALUATION
 GENERAL EVALUATION TABLE UPDATED
 R
MATERIAL PRICE INFORMATION
 MATERIAL PRICE INFORMATION TABLE
UPDATED
R
MATERIAL PRICE INFORMATION TABLE
UPDATED
R
MATERIAL PRICE INFORMATION TABLE
UPDATED
R
EFFECTIVITY
 OPERATOR LIST UPDATED
 R
NATURE OF THE WORK
 NATURE OF WORK TABLE UPDATED
 R
MANPOWER
 MANPOWER UPDATED
 R
MANPOWER UPDATED
 R
MANPOWER UPDATED
 R
PLANNING INFORMATION
EFFECTIVITY
 EFFECTIVITY RELATED INFORMATION
UPDATED
R
Configuration definition
CONF 001
 CONFIGURATION DEFINITION UPDATED
 R
CONF 002
 CONFIGURATION DEFINITION UPDATED
 R
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 3

@A340
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Material Effectivity
 MATERIAL EFFECTIVITY UPDATED
MATERIAL SET QUANTITY UPDATED
MATERIAL SET UPDATED
R
MATERIAL EFFECTIVITY UPDATED
MATERIAL SET QUANTITY UPDATED
MATERIAL SET UPDATED
R
MATERIAL EFFECTIVITY UPDATED
MATERIAL SET QUANTITY UPDATED
MATERIAL SET UPDATED
R
REASON
Operational/Maintenance
Consequences
OPERATIONAL/MAINTENANCE CONSEQUENCES
UPDATED
R
MANPOWER
 MANPOWER UPDATED
 R
MANPOWER UPDATED
 R
MANPOWER UPDATED
 R
REFERENCES
 REFERENCED DOCUMENTATION UPDATED
 R
REFERENCED DOCUMENTATION UPDATED
 R
REFERENCED DOCUMENTATION UPDATED
 R
PUBLICATION AFFECTED
 PUBLICATIONS AFFECTED UPDATED
 R
MATERIAL INFORMATION
MATERIAL - PRICE AND AVAILABILITY
Procurement Addresses
 PROCUREMENT ADDRESSES UPDATED
MATERIAL SET UPDATED
R
Price and Availability
 PRICE AND AVAILABILITY UPDATED
MATERIAL AVAILABILITY UPDATED
MATERIAL SET UPDATED
MATERIAL PRICE UPDATED
R
INDUSTRY SUPPORT INFORMATION
 INDUSTRY SUPPORT INFORMATION UPDATED
 R
LIST OF COMPONENTS
Kit 574138A01R01
 PART MATERIAL SET UPDATED
MATERIAL SET LABEL UPDATED
PART NUMBER UPDATED
R
Kit 574138A02R01
 PART MATERIAL SET UPDATED
MATERIAL SET LABEL UPDATED
PART NUMBER UPDATED
R
LIST OF MATERIALS - OPERATOR
SUPPLIED
Consumable Materials
Consumable CMLA01
 CONSUMABLE MATERIAL SET UPDATED
CONSUMABLE UPDATED
QUANTITY UPDATED
R
Components
 COMPONENTS UPDATED
 R
Component COMPA01
 PART MATERIAL SET ADDED
 N
ACCOMPLISHMENT INSTRUCTIONS
TASK 574138- 831-801-001-Modification
 TASK SOLUTION UPDATED
WARNING UPDATED
NOTE UPDATED
CAUTION UPDATED
R
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 3
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 4

@A340
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Task associated data - 001
 ZONE UPDATED
MAN HOURS UPDATED
ELAPSED TIME UPDATED
R
Task associated data - 002
 ZONE UPDATED
MAN HOURS UPDATED
ELAPSED TIME UPDATED
R
Task associated data - 003
 ZONE UPDATED
MAN HOURS UPDATED
ELAPSED TIME UPDATED
R
Subtask 574138-910-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
REFERENCES UPDATED
R
Subtask 574138-910-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
REFERENCES UPDATED
R
Subtask 574138-910-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
REFERENCES UPDATED
R
Subtask 574138-941-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
PANEL UPDATED
REFERENCES UPDATED
NOTE UPDATED
R
Subtask 574138-941-002-001
 SUBTASK SOLUTION DELETED FOR
APPLICABLE MSN
D
Subtask 574138-010-004-001
 SUBTASK SOLUTION DELETED FOR
APPLICABLE MSN
D
Subtask 574138-010-005-001
 SUBTASK SOLUTION DELETED FOR
APPLICABLE MSN
D
Subtask 574138-010-003-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
CONFIGURATION UPDATED
FIGURE REFERENCE UPDATED
FIN UPDATED
ITEM NUMBER UPDATED
PART NUMBER DESCRIPTION UPDATED
QUANTITY UPDATED
REFERENCES UPDATED
R
Subtask 574138-941-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
PANEL UPDATED
REFERENCES UPDATED
NOTE UPDATED
R
Subtask 574138-941-002-001
 SUBTASK SOLUTION DELETED FOR
APPLICABLE MSN
D
Subtask 574138-010-004-001
 SUBTASK SOLUTION DELETED FOR
APPLICABLE MSN
D
Subtask 574138-010-005-001
 SUBTASK SOLUTION DELETED FOR
APPLICABLE MSN
D
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 4
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 5

@A340
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Subtask 574138-010-003-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
CONFIGURATION UPDATED
FIGURE REFERENCE UPDATED
FIN UPDATED
ITEM NUMBER UPDATED
PART NUMBER DESCRIPTION UPDATED
QUANTITY UPDATED
REFERENCES UPDATED
R
Subtask 574138-941-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
PANEL UPDATED
REFERENCES UPDATED
NOTE UPDATED
R
Subtask 574138-941-002-001
 SUBTASK SOLUTION DELETED FOR
APPLICABLE MSN
D
Subtask 574138-010-004-001
 SUBTASK SOLUTION DELETED FOR
APPLICABLE MSN
D
Subtask 574138-010-005-001
 SUBTASK SOLUTION DELETED FOR
APPLICABLE MSN
D
Subtask 574138-010-003-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
CONFIGURATION UPDATED
FIGURE REFERENCE UPDATED
FIN UPDATED
ITEM NUMBER UPDATED
PART NUMBER DESCRIPTION UPDATED
QUANTITY UPDATED
REFERENCES UPDATED
R
Subtask 574138-831-001-001
 SUBTASK SOLUTION UPDATED
CONFIGURATION UPDATED
NOTE UPDATED
ITEM NUMBER UPDATED
PART NUMBER DESCRIPTION UPDATED
QUANTITY UPDATED
FIGURE REFERENCE UPDATED
MANPOWER RESSOURCE UPDATED
R
Subtask 574138-832-001-001
 SUBTASK SOLUTION UPDATED
MANPOWER RESSOURCE UPDATED
R
Subtask 574138-831-002-001
 SUBTASK SOLUTION UPDATED
CONSUMABLE UPDATED
QUANTITY UPDATED
REFERENCED DOCUMENTATION UPDATED
MANPOWER RESSOURCE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 5
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 6

@A340
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Subtask 574138-831-003-001
 SUBTASK SOLUTION UPDATED
PART NUMBER UPDATED
KEYWORD UPDATED
ITEM NUMBER UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
CONFIGURATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
PART NUMBER DESCRIPTION UPDATED
MANPOWER RESSOURCE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 574138-831-004-001
 SUBTASK SOLUTION UPDATED
CONFIGURATION UPDATED
NOTE UPDATED
ITEM NUMBER UPDATED
PART NUMBER DESCRIPTION UPDATED
QUANTITY UPDATED
FIGURE REFERENCE UPDATED
MANPOWER RESSOURCE UPDATED
R
Subtask 574138-832-002-001
 SUBTASK SOLUTION UPDATED
MANPOWER RESSOURCE UPDATED
R
Subtask 574138-831-005-001
 SUBTASK SOLUTION UPDATED
CONSUMABLE UPDATED
QUANTITY UPDATED
REFERENCED DOCUMENTATION UPDATED
MANPOWER RESSOURCE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 574138-831-006-001
 SUBTASK SOLUTION UPDATED
PART NUMBER UPDATED
KEYWORD UPDATED
ITEM NUMBER UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
PART NUMBER DESCRIPTION UPDATED
CONFIGURATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
MANPOWER RESSOURCE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 6
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 7

@A340
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Subtask 574138-831-001-002
 SUBTASK SOLUTION UPDATED
CONFIGURATION UPDATED
NOTE UPDATED
ITEM NUMBER UPDATED
PART NUMBER DESCRIPTION UPDATED
QUANTITY UPDATED
FIGURE REFERENCE UPDATED
MANPOWER RESSOURCE UPDATED
R
Subtask 574138-832-001-002
 SUBTASK SOLUTION UPDATED
MANPOWER RESSOURCE UPDATED
R
Subtask 574138-831-002-002
 SUBTASK SOLUTION UPDATED
CONSUMABLE UPDATED
QUANTITY UPDATED
REFERENCED DOCUMENTATION UPDATED
MANPOWER RESSOURCE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 574138-831-003-002
 SUBTASK SOLUTION UPDATED
PART NUMBER UPDATED
KEYWORD UPDATED
ITEM NUMBER UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
CONFIGURATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
PART NUMBER DESCRIPTION UPDATED
MANPOWER RESSOURCE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 574138-831-004-002
 SUBTASK SOLUTION UPDATED
CONFIGURATION UPDATED
NOTE UPDATED
ITEM NUMBER UPDATED
PART NUMBER DESCRIPTION UPDATED
QUANTITY UPDATED
FIGURE REFERENCE UPDATED
MANPOWER RESSOURCE UPDATED
R
Subtask 574138-832-002-002
 SUBTASK SOLUTION UPDATED
MANPOWER RESSOURCE UPDATED
R
Subtask 574138-831-005-002
 SUBTASK SOLUTION UPDATED
CONSUMABLE UPDATED
QUANTITY UPDATED
REFERENCED DOCUMENTATION UPDATED
MANPOWER RESSOURCE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 7
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 8

@A340
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Subtask 574138-831-006-002
 SUBTASK SOLUTION UPDATED
PART NUMBER UPDATED
KEYWORD UPDATED
ITEM NUMBER UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
PART NUMBER DESCRIPTION UPDATED
CONFIGURATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
MANPOWER RESSOURCE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 574138-831-001-001
 SUBTASK SOLUTION UPDATED
CONFIGURATION UPDATED
NOTE UPDATED
ITEM NUMBER UPDATED
PART NUMBER DESCRIPTION UPDATED
QUANTITY UPDATED
FIGURE REFERENCE UPDATED
MANPOWER RESSOURCE UPDATED
R
Subtask 574138-832-001-001
 SUBTASK SOLUTION UPDATED
MANPOWER RESSOURCE UPDATED
R
Subtask 574138-831-002-001
 SUBTASK SOLUTION UPDATED
CONSUMABLE UPDATED
QUANTITY UPDATED
REFERENCED DOCUMENTATION UPDATED
MANPOWER RESSOURCE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 574138-831-003-001
 SUBTASK SOLUTION UPDATED
PART NUMBER UPDATED
KEYWORD UPDATED
ITEM NUMBER UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
CONFIGURATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
PART NUMBER DESCRIPTION UPDATED
MANPOWER RESSOURCE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 8
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 9

@A340
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Subtask 574138-831-004-001
 SUBTASK SOLUTION UPDATED
CONFIGURATION UPDATED
NOTE UPDATED
ITEM NUMBER UPDATED
PART NUMBER DESCRIPTION UPDATED
QUANTITY UPDATED
FIGURE REFERENCE UPDATED
MANPOWER RESSOURCE UPDATED
R
Subtask 574138-832-002-001
 SUBTASK SOLUTION UPDATED
MANPOWER RESSOURCE UPDATED
R
Subtask 574138-831-005-001
 SUBTASK SOLUTION UPDATED
CONSUMABLE UPDATED
QUANTITY UPDATED
REFERENCED DOCUMENTATION UPDATED
MANPOWER RESSOURCE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 574138-831-006-001
 SUBTASK SOLUTION UPDATED
PART NUMBER UPDATED
KEYWORD UPDATED
ITEM NUMBER UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
PART NUMBER DESCRIPTION UPDATED
CONFIGURATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
MANPOWER RESSOURCE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 574138-700-001-001
 SUBTASK SOLUTION UPDATED
CONFIGURATION UPDATED
R
Subtask 574138-790-001-001
 SUBTASK SOLUTION ADDED
 N
Subtask 574138-700-001-001
 SUBTASK SOLUTION UPDATED
CONFIGURATION UPDATED
R
Subtask 574138-790-001-001
 SUBTASK SOLUTION ADDED
 N
Subtask 574138-700-001-001
 SUBTASK SOLUTION UPDATED
CONFIGURATION UPDATED
R
Subtask 574138-790-001-001
 SUBTASK SOLUTION ADDED
 N
Subtask 574138-410-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
CONFIGURATION UPDATED
FIGURE REFERENCE UPDATED
ITEM NUMBER UPDATED
PART NUMBER DESCRIPTION UPDATED
QUANTITY UPDATED
FIN UPDATED
REFERENCES UPDATED
R
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 9
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 10

@A340
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Subtask 574138-410-004-001
 SUBTASK SOLUTION DELETED FOR
APPLICABLE MSN
D
Subtask 574138-410-005-001
 SUBTASK SOLUTION DELETED FOR
APPLICABLE MSN
D
Subtask 574138-942-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
PANEL UPDATED
REFERENCES UPDATED
R
Subtask 574138-410-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
CONFIGURATION UPDATED
FIGURE REFERENCE UPDATED
ITEM NUMBER UPDATED
PART NUMBER DESCRIPTION UPDATED
QUANTITY UPDATED
FIN UPDATED
REFERENCES UPDATED
R
Subtask 574138-410-004-001
 SUBTASK SOLUTION DELETED FOR
APPLICABLE MSN
D
Subtask 574138-410-005-001
 SUBTASK SOLUTION DELETED FOR
APPLICABLE MSN
D
Subtask 574138-942-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
PANEL UPDATED
REFERENCES UPDATED
R
Subtask 574138-410-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
CONFIGURATION UPDATED
FIGURE REFERENCE UPDATED
ITEM NUMBER UPDATED
PART NUMBER DESCRIPTION UPDATED
QUANTITY UPDATED
FIN UPDATED
REFERENCES UPDATED
R
Subtask 574138-410-004-001
 SUBTASK SOLUTION DELETED FOR
APPLICABLE MSN
D
Subtask 574138-410-005-001
 SUBTASK SOLUTION DELETED FOR
APPLICABLE MSN
D
Subtask 574138-942-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
PANEL UPDATED
REFERENCES UPDATED
R
Fig. A-FBBAA
 FIGURE SOLUTION ADDED
 N
Fig. A-FBBAA Sheet 01
 SHEET ADDED
 N
Fig. A-FBEAA
 FIGURE SOLUTION UPDATED
 R
Fig. A-FBEAA Sheet 01
 SHEET UPDATED
 R
Fig. A-FBEAA Sheet 02
 SHEET UPDATED
 R
Fig. A-FBEAA Sheet 03
 SHEET ADDED
 N
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 10
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 11

@A340
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Fig. A-FBEAB
 FIGURE SOLUTION UPDATED
 R
Fig. A-FBEAB Sheet 01
 SHEET UPDATED
 R
Fig. A-FBEAB Sheet 02
 SHEET UPDATED
 R
Fig. A-FBEAB Sheet 03
 SHEET ADDED
 N
Appendix 01 - Manpower Gantt Chart
Fig. A-FAAAA
Fig. A-FAAAA Sheet 01
 SHEET UPDATED
 R
FILING INSTRUCTIONS
This Service Bulletin has been generated electronically and is reissued as a complete document.
Replace the complete document.
Put this Revision Transmittal Sheet in front of the Service Bulletin.
HISTORY OF PREVIOUS REVISIONS
No previous revision
REVISION SEQUENCE
ORIGINAL: Nov 23/16
REVISION No. : 01 - Feb 13/18
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 11
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 12

@A340
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
This Page Intentionally Left Blank
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 12
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 13

@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: 57
TITLE: FUSELAGE - CENTER FUSELAGE - MODIFICATION OF FASTENER
HOLES 12, 14, 260, 261, 262, 263 AT FRAME 40
**CONF ALL
MODIFICATIONS
MODIFICATION CLASSIFICATION
MAJOR
 206049S33789
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
The area at Frame 40 is subjected to a specific maintenance program. A new campaign of modification
has been launched to improve the maintenance program, decrease the number of maintenance actions
and to improve the structural potential of the aircraft to meet the Design Service Goal (DSG) /
Evaluated Service Goal (ESG).
This Service Bulletin recommends the expansion of holes at Frame 40 to improve the fatigue behaviour.
Depending on the configurations, this reinforcement consists in doing a first or second cold expansion
of fastener holes 12, 14, 260, 261, 262, 263 and installing oversized fasteners with high interference.
Accomplishment of this Service Bulletin will prevent cracks and will increase the fatigue life on the area
of Frame 40.
Accomplishment of this Service Bulletin cancels the inspection requirement of Service Bulletin No.
A340-57-4124 for fastener holes 12, 14, 260, 261, 262, 263 except for hole 260 PRE MOD No.
49202S16307 where the hole must be inspected again by Service Bulletin No.
 A340-57-4124. Then,
accomplishment of Service Bulletin No. A340-57-4137 will become the terminative action of Service
Bulletin No. A340-57-4124 for hole 260.
GENERAL EVALUATION
EVALUATION TABLE
COMPLIANCE
 RECOMMENDED (1)
 CANCELS INSPECTION SB
 NO
POTENTIAL AD
 NO
 A/C OPERATION AFFECTED
 NO
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 14

@A340
SERVICE BULLETIN
SUMMARY
EVALUATION TABLE
RELIABILITY AFFECTED
 NO
 PAX COMFORT AFFECTED
 NO
COST SAVING
 NO
 LROPS AFFECTED
 NO
STRUCTURAL LIFE EXTN
 NO
 VENDOR SB INVOLVED
 NO
DE-FUELLING/VENTILATION
 YES
 VALIDATION ON AIRCRAFT
 YES
BOOKLET AVAILABLE
 YES
NOTE
 (1)
: Service Bulletin recommended to be accomplished to prevent significant operational
disruptions.
NOTE
: Depending on aircraft configuration, de-fuelling of the center fuel tank may be required
before performing the cold working procedure.
NOTE
: The equivalent of this Service Bulletin has been validated on A330 aircraft with MSN
0422.
MATERIAL PRICE INFORMATION
**CONF 001
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit
 574138A01R01
 1
 325.00
 Bolts, nuts, pins
Component
 COMPA01
 1
 See SB
 Bolt and nut
Standard tool TOOLA01
 1
 See SB
 FTI cold working tools
Standard tool TOOLA02
 1
 See SB
 WCI cold working tools
**CONF 002
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit
 574138A02R01
 1
 415.00
 Bolts, nuts, pin
Component
 COMPA01
 1
 See SB
 Bolt and nut
Standard tool TOOLA01
 1
 See SB
 FTI cold working tools
Standard tool TOOLA02
 1
 See SB
 WCI cold working tools
**CONF 003
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit
 574138A01R01
 1
 325.00
 Bolts, nuts, pins
Component
 COMPA01
 1
 See SB
 Bolt and nut
Standard tool TOOLA01
 1
 See SB
 FTI cold working tools
Standard tool TOOLA02
 1
 See SB
 WCI cold working tools
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 2
5
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SERVICE BULLETIN
SUMMARY
EFFECTIVITY
**CONF ALL
This Service Bulletin is applicable to this (these) operator(s) :
09M 78U
 83V 85Z
 ABD AFR AIB ALD ARG AXY BOE CAL CPA
DLH EDW F2I GAF HFM HFY IBE IRM KMF
 MAU MDG MRJ PAL
PUE QQE
 ROI S3R SAA SAS SLM SWR SYR
 THT THY
CONCURRENT REQUIREMENTS
None
REFERENCES / REPERCUSSIONS
TFU
 57.11.00.007
OEB
 None
AOT
 None
SIL
 None
ISI
 None
LINE MAINTENANCE AFFECTED
 No
LIFE LIMIT
 None
OTHER
 None
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
MANPOWER
**CONF 001
Task 574138-831-801-001: Modification
TOTAL MANHOURS
 67.00
ELAPSED TIME (HOURS)
 28.50
**CONF 002
Task 574138-831-801-001: Modification
TOTAL MANHOURS
 67.00
ELAPSED TIME (HOURS)
 28.50
**CONF 003
Task 574138-831-801-001: Modification
TOTAL MANHOURS
 67.00
ELAPSED TIME (HOURS)
 28.50
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 3
5
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SERVICE BULLETIN
SUMMARY
APPENDICES
**CONF ALL
Appendix 01 - Manpower Gantt Chart
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 4
5
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SERVICE BULLETIN
SUMMARY
**CONF ALL
A
Z140
A
STGR38
STGR39
STGR40
CENTER WING BOX
LOWER PANEL REFERENCE
B
VIEW LOOKING AFT
LH SHOWN
RH SYMMETRICAL
COLD WORKING OF
6 FASTENER HOLES
FR40
U
P
INBD
STGR37
C
B
H260
H14 H263
H262H12
H261
FR40
FR47
F_SB_574138_5_SAAA_01_03
Figure A-FSAAA - Sheet 01
Cold Working of the Fastener Holes 12, 14, 260, 261, 262 and 263 at FR40 on the Left Hand (LH) and
the Right Hand (RH) Side
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 5
5
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SERVICE BULLETIN
SUMMARY
**CONF ALL
DATUMFR40
STGR1
LH SHOWN
RH SYMMETRICAL
Y1959
C
COLD WORKING OF
6 FASTENER HOLES
H260
H14
H263
H262
H12
H261
F_SB_574138_5_SAAA_02_00
Figure A-FSAAA - Sheet 02
Cold Working of the Fastener Holes 12, 14, 260, 261, 262 and 263 at FR40 on the Left Hand (LH) and
the Right Hand (RH) Side
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 6
5
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### Page 19

@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: 57
TITLE: FUSELAGE - CENTER FUSELAGE - MODIFICATION OF FASTENER
HOLES 12, 14, 260, 261, 262, 263 AT FRAME 40
MODIFICATION No.: 206049S33789
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.
NOTE
: This Service Bulletin is only applicable for aircraft on which MOD No.
44360S13013 or MOD No. 44360S13482 is embodied and on which MOD No.
55306S18660 is not embodied.
(1) Models
340-212 340-213 340-312 340-313
(2) Effectivity by MSN
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
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 1
5
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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
09M
 0483
78U
 0179
83V
 0280 0292
85Z
 0263
ABD
 0210
AFR
 0186 0207 0237 0245 0246 0260 0307 0310 0377
AIB
 0192 0243 0264
ALD
 0178
ARG
 0193 0373
AXY
 0374
BOE
 0554
CAL
 0402 0406 0411 0415 0433 0541
CPA
 0208 0218 0227
DLH
 0213 0233 0252 0297 0304 0321 0325 0327 0335 0347 0352 0354
0379 0390 0434 0447
EDW
 0562
F2I
 0214
GAF
 0274 0355
HFM
 0185
 0236
 0367
HFY
 0190 0202
IBE
 0217 0221 0329
IRM
 0282
KMF
 0278
MAU
 0194 0268 0793 0800
MDG
 0319
MRJ
 0257
PAL
 0302 0318 0332 0387 0459 0474
PUE
 0212 0215 0399
QQE
 0528
ROI
 0199 0201
S3R
 0204
SAA
 0197 0378 0544 0582 0590 0643 0646 0651
SAS
 0413 0424 0430 0435 0450 0467 0470
SLM
 0242
SWR
 0538 0545 0546 0556 0559 0561 0585 0598
SYR
 0381
THT
 0385 0395 0438 0446 0668
THY
 0180 0270 0331
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 2
5
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SERVICE BULLETIN
(4) Configuration by MSN
MSN
 CONFIGURATION
0178 0180 0185 0190 0192 0199 0201 0202 0204 0212 0214
0215 0236 0242 0243 0257 0264 0270 0278 0280 0282 0292
0318 0319 0331 0373 0378 0385 0395 0413 0424 0430 0435
0438 0446 0450 0467 0470
001 002
0179 0186 0193 0194 0197 0207 0208 0210 0213 0217 0218
0221 0227 0233 0237 0245 0246 0252 0260 0263 0268 0274
0297 0302 0304 0307 0310 0321 0325 0327 0329 0332 0335
0347 0352 0354 0355 0367 0374 0377 0379 0381 0387 0390
0399 0402 0406 0411 0415 0433 0434 0447 0459 0474 0483
002
0528 0538 0541 0544 0545 0546 0554 0556 0559 0561 0562
0582 0585 0590 0598 0643 0646 0651 0668 0793 0800
003
(5) Configuration definition
**CONF 001
Config 001 is valid for aircraft on which:
- MOD No. 44360S13482 and MOD No. 44360S13013 are embodied
- MOD No. 49202S16307 is not embodied
and on which
- Service Bulletin No. A340-57-4090 is not accomplished.
**CONF 002
Config 002 is valid for aircraft on which:
- MOD No. 44360S13482 and MOD No. 44360S13013 are embodied
- MOD No. 49202S16307 is not embodied
and on which
- Service Bulletin No. A340-57-4090 is accomplished.
**CONF 003
Config 003 is valid for aircraft on which:
- MOD No. 49202S16307 is embodied
and on which
- MOD No. 55306S18660 is not embodied
(6) Material Effectivity
**CONF 001
MATERIAL
 QTY PER A/C
 SEE NOTES
Kit
 574138A01R01
 1
Component
 COMPA01
 1
Consumable CMLA01
 1
Standard tool TOOLA01
 1
 (1)
Standard tool TOOLA02
 1
 (1)
NOTE
 (1)
: Only one tool kit is necessary to perform cold working, either TOOLA01
or TOOLA02 depending on supplier chosen.
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 3
5
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SERVICE BULLETIN
**CONF 002
MATERIAL
 QTY PER A/C
 SEE NOTES
Kit
 574138A02R01
 1
Component
 COMPA01
 1
Consumable CMLA01
 1
Standard tool TOOLA01
 1
 (1)
Standard tool TOOLA02
 1
 (1)
NOTE
 (1)
: Only one tool kit is necessary to perform cold working, either TOOLA01
or TOOLA02 depending on supplier chosen.
**CONF 003
MATERIAL
 QTY PER A/C
 SEE NOTES
Kit
 574138A01R01
 1
Component
 COMPA01
 1
Consumable CMLA01
 1
Standard tool TOOLA01
 1
 (1)
Standard tool TOOLA02
 1
 (1)
NOTE
 (1)
: Only one tool kit is necessary to perform cold working, either TOOLA01
or TOOLA02 depending on supplier chosen.
**CONF ALL
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
The area at Frame 40 is subjected to a specific maintenance program. A new campaign
of modification has been launched to improve the maintenance program, decrease the
number of maintenance actions and to improve the structural potential of the aircraft to
meet the Design Service Goal (DSG) / Evaluated Service Goal (ESG).
(2) Objective/Action
This Service Bulletin recommends the expansion of holes at Frame 40 to improve the
fatigue behaviour. Depending on the configurations, this reinforcement consists in doing
a first or second cold expansion of fastener holes 12, 14, 260, 261, 262, 263 and
installing oversized fasteners with high interference.
(3) Advantages
Accomplishment of this Service Bulletin will prevent cracks and will increase the fatigue
life on the area of Frame 40.
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 4
5
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### Page 23

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SERVICE BULLETIN
(4) Operational/Maintenance Consequences
Accomplishment of this Service Bulletin cancels the inspection requirement of Service
Bulletin No.
 A340-57-4124 for fastener holes 12, 14, 260, 261, 262, 263 except for hole
260 PRE MOD No. 49202S16307 where the hole must be inspected again by Service
Bulletin No.
 A340-57-4124. Then, accomplishment of Service Bulletin No. A340-57-4137
will become the terminative action of Service Bulletin No. A340-57-4124 for hole 260.
D. DESCRIPTION
To accomplish this Service Bulletin it is necessary to :
**CONF 001
Task 574138-831-801-001: Modification
(1) Remove the Fastener from the Holes 12, 14, 260, 261, 262 and 263 between
STGR37 and STGR38 at FR40, LH Side
(2) Do an Inspection of Fastener Holes 12, 14, 260, 261, 262 and 263 between STGR37
and STGR38 at FR40, LH Side
(3) Do a Cold Working of Fastener Holes 12, 14, 260, 261, 262 and 263 between
STGR37 and STGR38 at FR40, LH Side
(4) Install the Fastener in the Holes 12, 14, 260, 261, 262 and 263 between STGR37
and STGR38 at FR40, LH Side
(5) Remove the Fastener from the Holes 12, 14, 260, 261, 262 and 263 between
STGR37 and STGR38 at FR40, RH Side
(6) Do an Inspection of Fastener Holes 12, 14, 260, 261, 262 and 263 between STGR37
and STGR38 at FR40, RH Side
(7) Do a Cold Working of Fastener Holes 12, 14, 260, 261, 262 and 263 between
STGR37 and STGR38 at FR40, RH Side
(8) Install the Fastener in the Holes 12, 14, 260, 261, 262 and 263 between STGR37
and STGR38 at FR40, RH Side
**CONF 002
Task 574138-831-801-001: Modification
(1) Remove the Fastener from the Holes 12, 14, 260, 261, 262 and 263 between
STGR37 and STGR38 at FR40, LH Side
(2) Do an Inspection of Fastener Holes 12, 14, 260, 261, 262 and 263 between STGR37
and STGR38 at FR40, LH Side
(3) Do a Cold Working of Fastener Holes 12, 14, 260, 261, 262 and 263 between
STGR37 and STGR38 at FR40, LH Side
(4) Install the Fastener in the Holes 12, 14, 260, 261, 262 and 263 between STGR37
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 5
5
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SERVICE BULLETIN
and STGR38 at FR40, LH Side
(5) Remove the Fastener from the Holes 12, 14, 260, 261, 262 and 263 between
STGR37 and STGR38 at FR40, RH Side
(6) Do an Inspection of Fastener Holes 12, 14, 260, 261, 262 and 263 between STGR37
and STGR38 at FR40, RH Side
(7) Do a Cold Working of Fastener Holes 12, 14, 260, 261, 262 and 263 between
STGR37 and STGR38 at FR40, RH Side
(8) Install the Fastener in the Holes 12, 14, 260, 261, 262 and 263 between STGR37
and STGR38 at FR40, on the RH Side
**CONF 003
Task 574138-831-801-001: Modification
(1) Remove the Fastener from the Holes 12, 14, 260, 261, 262 and 263 between
STGR37 and STGR38 at FR40, LH Side
(2) Do an Inspection of Fastener Holes 12, 14, 260, 261, 262 and 263 between STGR37
and STGR38 at FR40, LH Side
(3) Do a Cold Working of Fastener Holes 12, 14, 260, 261, 262 and 263 between
STGR37 and STGR38 at FR40, LH Side
(4) Install the Fastener in the Holes 12, 14, 260, 261, 262 and 263 between STGR37
and STGR38 at FR40, LH Side
(5) Remove the Fastener from the Holes 12, 14, 260, 261, 262 and 263 between
STGR37 and STGR38 at FR40, RH Side
(6) Do an Inspection of Fastener Holes 12, 14, 260, 261, 262 and 263 between STGR37
and STGR38 at FR40, RH Side
(7) Do a Cold Working of Fastener Holes 12, 14, 260, 261, 262 and 263 between
STGR37 and STGR38 at FR40, RH Side
(8) Install the Fastener in the Holes 12, 14, 260, 261, 262 and 263 between STGR37
and STGR38 at FR40, RH Side
**CONF ALL
E. COMPLIANCE
(1) Classification
RECOMMENDED: Service Bulletin recommended to be accomplished to prevent
significant operational disruptions.
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 6
5
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SERVICE BULLETIN
(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 574138-831-801-001: Modification
Get Access
 21.50
On Aircraft
Remove the Fastener from the Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
LH Side
2.00
Do an Inspection of Fastener Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
LH Side
1.00
Do a Cold Working of Fastener Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
LH Side
5.50
Install the Fastener in the Holes 12, 14, 260, 261, 262
and 263 between STGR37 and STGR38 at FR40, LH
Side
2.50
Remove the Fastener from the Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
RH Side
2.00
Do an Inspection of Fastener Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
RH Side
1.00
Do a Cold Working of Fastener Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
RH Side
5.50
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 7
5
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SERVICE BULLETIN
Task 574138-831-801-001: Modification
Install the Fastener in the Holes 12, 14, 260, 261, 262
and 263 between STGR37 and STGR38 at FR40, RH
Side
2.50
Tests
 2.00
Close-Up
 21.50
TOTAL MANHOURS
 67.00
ELAPSED TIME (HOURS)
 28.50
NOTE
: For an explanation of the man-hours and elapsed time, refer to the Gantt
Chart,
 Fig. A-FAAAA
 given in Appendix 01 - Manpower Gantt Chart .
**CONF 002
Task 574138-831-801-001: Modification
Get Access
 21.50
On Aircraft
Remove the Fastener from the Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
LH Side
2.00
Do an Inspection of Fastener Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
LH Side
1.00
Do a Cold Working of Fastener Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
LH Side
5.50
Install the Fastener in the Holes 12, 14, 260, 261, 262
and 263 between STGR37 and STGR38 at FR40, LH
Side
2.50
Remove the Fastener from the Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
RH Side
2.00
Do an Inspection of Fastener Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
RH Side
1.00
Do a Cold Working of Fastener Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
RH Side
5.50
Install the Fastener in the Holes 12, 14, 260, 261, 262
and 263 between STGR37 and STGR38 at FR40, on
the RH Side
2.50
Tests
 2.00
Close-Up
 21.50
TOTAL MANHOURS
 67.00
ELAPSED TIME (HOURS)
 28.50
NOTE
: For an explanation of the man-hours and elapsed time, refer to the Gantt
Chart,
 Fig. A-FAAAA
 given in Appendix 01 - Manpower Gantt Chart .
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 8
5
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SERVICE BULLETIN
**CONF 003
Task 574138-831-801-001: Modification
Get Access
 21.50
On Aircraft
Remove the Fastener from the Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
LH Side
2.00
Do an Inspection of Fastener Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
LH Side
1.00
Do a Cold Working of Fastener Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
LH Side
5.50
Install the Fastener in the Holes 12, 14, 260, 261, 262
and 263 between STGR37 and STGR38 at FR40, LH
Side
2.50
Remove the Fastener from the Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
RH Side
2.00
Do an Inspection of Fastener Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
RH Side
1.00
Do a Cold Working of Fastener Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40,
RH Side
5.50
Install the Fastener in the Holes 12, 14, 260, 261, 262
and 263 between STGR37 and STGR38 at FR40, RH
Side
2.50
Tests
 2.00
Close-Up
 21.50
TOTAL MANHOURS
 67.00
ELAPSED TIME (HOURS)
 28.50
NOTE
: For an explanation of the man-hours and elapsed time, refer to the Gantt
Chart,
 Fig. A-FAAAA
 given in Appendix 01 - Manpower Gantt Chart .
**CONF ALL
H. WEIGHT AND BALANCE
Not Changed
I. ELECTRICAL LOAD DATA
Not Changed
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 9
5
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SERVICE BULLETIN
J. REFERENCES
**CONF 001
Aircraft Maintenance Manual (AMM)
 06-20-00 06-31-53 06-41-53
12-34-24 20-21-11 21-20-00
21-21-41
 21-21-51 25-52-00
25-80-00 28-00-00 28-10-00
28-11-00
 28-25-00 32-12-00
38-41-00
 52-30-00 53-35-13
57-17-11
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
In Service Information (ISI)
 51.48.00001
Non Destructive Test Manual (NTM)
 51-10-01
Service Bulletin (SB)
 A340-57-4090
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-24-00 51-40-00 51-42-00
51-43-00 51-44-00 51-48-00
51-70-20
 51-75-12 51-76-12
**CONF 002
Aircraft Maintenance Manual (AMM)
 06-20-00 06-31-53 06-41-53
12-34-24 20-21-11 21-20-00
21-21-41
 21-21-51 25-52-00
25-80-00 28-00-00 28-10-00
28-11-00
 28-25-00 32-12-00
38-41-00
 52-30-00 53-35-13
57-17-11
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
In Service Information (ISI)
 51.48.00001
Non Destructive Test Manual (NTM)
 51-10-01
Service Bulletin (SB)
 A340-57-4090
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-24-00 51-40-00 51-42-00
51-43-00 51-44-00 51-48-00
51-70-20
 51-75-12 51-76-12
**CONF 003
Aircraft Maintenance Manual (AMM)
 06-20-00 06-31-53 06-41-53
12-34-24 20-21-11 21-20-00
21-21-41
 21-21-51 25-52-00
25-80-00 28-00-00 28-10-00
28-11-00
 28-25-00 32-12-00
38-41-00
 52-30-00 53-35-13
57-17-11
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
In Service Information (ISI)
 51.48.00001
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 10
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SERVICE BULLETIN
Non Destructive Test Manual (NTM)
 51-10-01
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-24-00 51-40-00 51-42-00
51-43-00 51-44-00 51-48-00
51-70-20
 51-75-12 51-76-12
**CONF ALL
K. PUBLICATION AFFECTED
None
L. INTERCHANGEABILITY/MIXABILITY
Not Applicable
M. SPARES
None
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 11
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This Page Intentionally Left Blank
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 12
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SERVICE BULLETIN
2. MATERIAL INFORMATION
**CONF ALL
A. MATERIAL - PRICE AND AVAILABILITY
(1) Procurement Addresses
Customers with aircraft shown in effectivity of this Service Bulletin should send a
purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:
Kit
 574138A01R01
Kit
 574138A02R01
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 Hotlines:
A330/340: +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
 COMPA01
 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
 574138A01R01
Cost
 325.00
 USD
Availability
 240 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.
Kit
 574138A02R01
Cost
 415.00
 USD
Availability
 240 calendar days from receipt of order
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 13
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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
 COMPA01
Operator supplied standard hardware parts, required to accomplish this Service Bulletin,
are to be supplied from the operator’s stock.
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 574138A01R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
20
 EN6115K7-16
 6
 BOLT
21
 ASNA2531-7
 10
 NUT
22
 EN6115K6-20
 2
 BOLT
23
 ASNA2531-6
 2
 NUT
24
 EN6115K7-22
 2
 BOLT
25
 EN6115K7-18
 2
 BOLT
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 574138A02R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
20
 EN6115K7-16
 4
 BOLT
21
 ASNA2531-7
 8
 NUT
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 14
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ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
22
 EN6115K6-20
 2
 BOLT
23
 ASNA2531-6
 2
 NUT
24
 EN6115K7-22
 2
 BOLT
25
 EN6115K7-18
 2
 BOLT
29
 EN6115K8-16
 2
 BOLT
30
 ASNA2531-8
 2
 NUT
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.
D. LIST OF MATERIALS - OPERATOR SUPPLIED
(1) Consumable Materials
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
Wash Primer - Structure
 04CMA2
 As required
Primer Polyurethane Paint -
Corrosion Inhibiting
04EAC2
 As required
Polyurethane Coating - Fuel Vapour
Barrier Structure
04PAG2
 0
Polysulfide Sealant - Fuel Tank
Brushable
06ABA1
 0
Coating Sealant - Fuel Tank
Brushable
06HAA1
 0
Adhesion Promoter - For Polysulfide
Sealant
06PAG1
 As required
Non Aqueous Cleaner - General
 08BAA9
 As required
Corrosion Preventive Compound -
Water Displacing
12ADB1
 0
Textile - Lint Free Cotton
 14SBA1
 As required
(2) Components
Component COMPA01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
35
 EN6115V4X11
 2
 BOLT
36
 ASNA2531-4
 2
 NUT
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: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 15
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NOTE
: The components listed above are only necessary if the fasteners are to
be removed for access, depending on the aircraft configuration. The
quantity of these items are to be ordered as required.
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
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
F. TOOLING
(1) Tooling - Price and Availability
(a) Procurement Addresses
Operators interested in obtaining the FTI tool kit should contact:
Standard tool TOOLA01
 Fatigue Technology Inc.
401 Andover Park East
SEATTLE, WA 98188-7605
USA
Internet: www.fatiguetech.com
Phone: (206) 2462010
Fax: (206) 2449886
Operators interested in obtaining the WCI tool kit should contact:
Standard tool TOOLA02
 West Coast Industries Inc.
14900 Whitman Ave. N
Seattle, Washington 98133
Tel: (206) 365-7513
Fax: (206) 365-7483
Email: info@coldwork.com
Europe, Middle-East, Africa, India and
Russia: customer@capaero.com /+33 5 61
92 04 91 (France)
(b) Price and Availability
Standard tool TOOLA01
Procurement to be negotiated directly with FTI.
Standard tool TOOLA02
Procurement to be negotiated directly with WCI.
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 16
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(2) Tools
Standard tool TOOLA01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA340574138-1
 Durable Tooling
 1
 (1)
EKA340574138-1
 Expendable Tooling
 1
 (2)
FTIA340574138-1
 Capital Tooling
 1
 (3)
NOTE
: 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. DK-A340-57-4138-1
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 ISI
51.48.00001.
NOTE
 (2)
: Expendable tooling: Ref. EK-A340-57-4138-1
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. FTI-A340-57-4138-1
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 TOOLA02
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA340574138-1
 Durable Tooling
 1
 (1)
EKA340574138-1
 Expendable Tooling
 1
 (2)
WCIA340574138-1
 Capital Tooling
 1
 (3)
NOTE
: 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. DK-A340-57-4138-1
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 17
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SERVICE BULLETIN
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 ISI
51.48.00001.
NOTE
 (2)
: Expendable tooling: Ref. EK-A340-57-4138-1
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. WCI-A340-57-4138-1
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: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 18
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3. ACCOMPLISHMENT INSTRUCTIONS
Task 574138-831-801-001 - Modification
WARNING
: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
WARNING
: THIS PROCEDURE USES A FUEL SYSTEM ITEM THAT IS IN A CATEGORY
KNOWN AS A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION
(CDCCL). CDCCL IDENTIFIES AN ITEM THAT CAN BE THE SOURCE OF A
POSSIBLE FUEL TANK IGNITION. YOU MUST KEEP ALL CDCCL ITEMS IN
THE APPROVED CONFIGURATION. DAMAGE, WEAR OR CHANGES TO A
CDCCL ITEM CAN CAUSE A POSSIBLE TANK EXPLOSION.
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.
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 19
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NOTE
: Discarded parts must be managed at the operator’s discretion.
Task Associated Data
**CONF 001
Zone
130 131 132
Manpower
TOTAL MANHOURS
 67.00
ELAPSED TIME (HOURS)
 28.50
**CONF 002
Zone
130 131 132
Manpower
TOTAL MANHOURS
 67.00
ELAPSED TIME (HOURS)
 28.50
**CONF 003
Zone
130 131 132
Manpower
TOTAL MANHOURS
 67.00
ELAPSED TIME (HOURS)
 28.50
**CONF ALL
A. GENERAL
**CONF 001
(1) Subtask 574138-910-001-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-20-00, Page Block 001
06-31-53, Page Block 001
06-41-53, Page Block 001
Task 20-21-11-911-801
Task 21-20-00-010-801
Task 21-20-00-410-801
Consumable Material List (CML)
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 20
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References
Structural Repair Manual (SRM)
 51-24-00
51-40-00
51-42-00
51-43-00
51-44-00
51-48-00
51-70-20
51-75-12
(a) For the specification of Material Numbers (Mat. No.) given in this Service Bulletin,
refer to the
 Consumable Materials List (CML).
(b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.
(c) For the identification of zones, refer to AMM 06-20-00, Page Block 001.
(d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.
(e) If alternative and substitute fasteners have to be used, you must make sure that the
associated nut/collar are compatible in accordance with SRM 51-40-00 ’Mating Part’
column.
(f) 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.
(g) Get alternative and substitute fastener data in accordance with
 SRM 51-43-00.
(h) Remove and install fasteners in accordance with SRM 51-42-00.
(i) Get fastener hole diameters and drill data in accordance with
 SRM 51-44-00.
(j) Perform spotfacing in accordance with SRM 51-70-20.
(k) To torque tighten the standard threaded fasteners, refer to AMM Task
20-21-11-911-801.
(l) For the general removal of air-conditioning distribution ducts, refer to AMM Task
21-20-00-010-801.
(m) For the general installation of air-conditioning distribution ducts, refer to AMM Task
21-20-00-410-801.
(n) Do the cold working of the fastener holes in accordance with SRM 51-48-00.
(o) Apply sealant in accordance with SRM 51-24-00.
(p) Renew the protective finish in accordance with SRM 51-75-12.
(q) Tag all the parts you must remove and retain to make the subsequent installation
easier.
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 21
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(r) Put all the retained hardware in identified plastic bags and attach the bags to the
related unit.
(2) Subtask 574138-839-001-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
**CONF 002
(1) Subtask 574138-910-001-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-20-00, Page Block 001
06-31-53, Page Block 001
06-41-53, Page Block 001
Task 20-21-11-911-801
Task 21-20-00-010-801
Task 21-20-00-410-801
Consumable Material List (CML)
Structural Repair Manual (SRM)
 51-24-00
51-40-00
51-42-00
51-43-00
51-44-00
51-48-00
51-70-20
51-75-12
(a) For the specification of Material Numbers (Mat. No.) given in this Service Bulletin,
refer to the
 Consumable Materials List (CML).
(b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.
(c) For the identification of zones, refer to AMM 06-20-00, Page Block 001.
(d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.
(e) If alternative and substitute fasteners have to be used, you must make sure that the
associated nut/collar are compatible in accordance with SRM 51-40-00 ’Mating Part’
column.
(f) 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.
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 22
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(g) Get alternative and substitute fastener data in accordance with
 SRM 51-43-00.
(h) Remove and install fasteners in accordance with SRM 51-42-00.
(i) Get fastener hole diameters and drill data in accordance with
 SRM 51-44-00.
(j) Perform spotfacing in accordance with SRM 51-70-20.
(k) To torque tighten the standard threaded fasteners, refer to AMM Task
20-21-11-911-801.
(l) For the general removal of air-conditioning distribution ducts, refer to AMM Task
21-20-00-010-801.
(m) For the general installation of air-conditioning distribution ducts, refer to AMM Task
21-20-00-410-801.
(n) Do the cold working of the fastener holes in accordance with SRM 51-48-00.
(o) Apply sealant in accordance with SRM 51-24-00.
(p) Renew the protective finish in accordance with SRM 51-75-12.
(q) Tag all the parts you must remove and retain to make the subsequent installation
easier.
(r) Put all the retained hardware in identified plastic bags and attach the bags to the
related unit.
(2) Subtask 574138-839-001-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
**CONF 003
(1) Subtask 574138-910-001-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-20-00, Page Block 001
06-31-53, Page Block 001
06-41-53, Page Block 001
Task 20-21-11-911-801
Task 21-20-00-010-801
Task 21-20-00-410-801
Consumable Material List (CML)
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 23
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References
Structural Repair Manual (SRM)
 51-24-00
51-40-00
51-42-00
51-43-00
51-44-00
51-48-00
51-70-20
51-75-12
(a) For the specification of Material Numbers (Mat. No.) given in this Service Bulletin,
refer to the
 Consumable Materials List (CML).
(b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.
(c) For the identification of zones, refer to AMM 06-20-00, Page Block 001.
(d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.
(e) If alternative and substitute fasteners have to be used, you must make sure that the
associated nut/collar are compatible in accordance with SRM 51-40-00 ’Mating Part’
column.
(f) 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.
(g) Get alternative and substitute fastener data in accordance with
 SRM 51-43-00.
(h) Remove and install fasteners in accordance with SRM 51-42-00.
(i) Get fastener hole diameters and drill data in accordance with
 SRM 51-44-00.
(j) Perform spotfacing in accordance with SRM 51-70-20.
(k) To torque tighten the standard threaded fasteners, refer to AMM Task
20-21-11-911-801.
(l) For the general removal of air-conditioning distribution ducts, refer to AMM Task
21-20-00-010-801.
(m) For the general installation of air-conditioning distribution ducts, refer to AMM Task
21-20-00-410-801.
(n) Do the cold working of the fastener holes in accordance with SRM 51-48-00.
(o) Apply sealant in accordance with SRM 51-24-00.
(p) Renew the protective finish in accordance with SRM 51-75-12.
(q) Tag all the parts you must remove and retain to make the subsequent installation
easier.
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 24
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(r) Put all the retained hardware in identified plastic bags and attach the bags to the
related unit.
(2) Subtask 574138-839-001-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
**CONF ALL
B. PREPARATION
**CONF 001
(1) Subtask 574138-941-001-001 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 12-34-24-860-802
Task 21-20-00-010-801
Task 25-80-00-000-801
Task 28-00-00-610-801
Task 28-10-00-910-805
Task 28-25-00-650-803
Task 32-12-00-010-801
Task 52-30-00-010-801
Task 53-35-13-000-802
Task 57-17-11-000-801
NOTE
: For the basic Aircraft configuration, refer to AMM Chapter "Introduction -
Aircraft status for maintenance" in Manual Front Matter section.
(a) Make sure that the aircraft is electrically grounded, refer to AMM Task
12-34-24-860-802.
(b) Put an access platform in position at 821 Forward (FWD) Cargo-Compartment Door
(CCD) and Main Landing Gear (MLG) doors.
(c) Open the 821 FWD CCD, refer to AMM Task 52-30-00-010-801.
(d) Defuel the center fuel tank, refer to AMM Task 28-25-00-650-803.
(e) Purge and vent the center fuel tanks for maintenance, refer to AMM Task
28-00-00-610-801 and AMM Task 28-10-00-910-805.
(f) Open the Main Landing Gear (MLG) doors, refer to AMM Task 32-12-00-010-801.
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 25
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(g) Remove the covers 147AZ and 148AZ for access, refer to AMM Task
57-17-11-000-801.
(h) Remove the access panels 191FB, 192GB and 192JB, refer to AMM Task
53-35-13-000-802
.
(2) Subtask 574138-010-003-001 - Remove/Open for Access in the FWD Cargo-
Compartment
Work Zones and Access Panels
Zone
 Access/Work location
130
 Work location
 from Frame 39.1 to Frame 40
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 21-20-00-010-801
Task 21-21-41-000-801
Task 21-21-51-000-801
Task 25-52-00-000-801
Task 25-80-00-000-801
Fig. A-FBAAA
Removal/Installation of the Air
Conditioning Ducts between FR39.1 and
FR40, FWD Cargo-Compartment
Sheet 01
Fig. A-FBBAA
Removal/Installation of the Air Supply
Pipe Assy
Sheet
 01
WARNING
: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR
CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A
GROUND SOURCE.
HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL
CAUTION
: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.
(a) Remove the ceiling panels, partition panels and sidewall panels in the FWD cargo
compartment 131CX, 131DX, 132CX, 132DX and 131BX, refer to AMM Task
25-52-00-000-801.
(b) Remove between Frame 39.1 and Frame 40 on the LH and RH sides, as shown on
Fig. A-FBAAA
:
Refer to AMM Task 21-20-00-010-801.
2 Duct Item (1) Retain
2 Duct Item (2) Retain
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 26
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SERVICE BULLETIN
(c) Remove, as shown on Fig. A-FBAAA
:
Refer to AMM Task 21-21-51-000-801 and AMM Task 21-21-41-000-801.
2 Recirculation Fan Item (3) Retain
2 Recirculation Filter Item (4) Retain
(d) Remove, as shown on Fig. A-FBBAA
:
3
 Bolt
 Item (31
) Retain
3
 Washer
 Item (32
) Retain
1
 Strip - Bonding
 Item (37
) Retain
3
 Clamp
 Item (33
) Retain
1
 Air Supply Pipe Assy
 Item (34
) Retain
(e) Remove the necessary insulation blankets to access work area, refer to AMM Task
25-80-00-000-801.
**CONF 002
(1) Subtask 574138-941-001-001 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 12-34-24-860-802
Task 21-20-00-010-801
Task 25-80-00-000-801
Task 28-00-00-610-801
Task 28-10-00-910-805
Task 28-25-00-650-803
Task 32-12-00-010-801
Task 52-30-00-010-801
Task 53-35-13-000-802
Task 57-17-11-000-801
NOTE
: For the basic Aircraft configuration, refer to AMM Chapter "Introduction -
Aircraft status for maintenance" in Manual Front Matter section.
(a) Make sure that the aircraft is electrically grounded, refer to AMM Task
12-34-24-860-802.
(b) Put an access platform in position at 821 Forward (FWD) Cargo-Compartment Door
(CCD) and Main Landing Gear (MLG) doors.
(c) Open the 821 FWD CCD, refer to AMM Task 52-30-00-010-801.
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 27
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(d) Defuel the center fuel tank, refer to AMM Task 28-25-00-650-803.
(e) Purge and vent the center fuel tanks for maintenance, refer to AMM Task
28-00-00-610-801 and AMM Task 28-10-00-910-805.
(f) Open the Main Landing Gear (MLG) doors, refer to AMM Task 32-12-00-010-801.
(g) Remove the covers 147AZ and 148AZ for access, refer to AMM Task
57-17-11-000-801.
(h) Remove the access panels 191FB, 192GB and 192JB, refer to AMM Task
53-35-13-000-802
.
(2) Subtask 574138-010-003-001 - Remove/Open for Access in the FWD Cargo-
Compartment
Work Zones and Access Panels
Zone
 Access/Work location
130
 Work location
 from Frame 39.1 to Frame 40
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 21-20-00-010-801
Task 21-21-41-000-801
Task 21-21-51-000-801
Task 25-52-00-000-801
Task 25-80-00-000-801
Fig. A-FBAAA
Removal/Installation of the Air
Conditioning Ducts between FR39.1 and
FR40, FWD Cargo-Compartment
Sheet 01
Fig. A-FBBAA
Removal/Installation of the Air Supply
Pipe Assy
Sheet
 01
WARNING
: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR
CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A
GROUND SOURCE.
HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL
CAUTION
: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.
(a) Remove the ceiling panels, partition panels and sidewall panels in the FWD cargo
compartment 131CX, 131DX, 132CX, 132DX and 131BX, refer to AMM Task
25-52-00-000-801.
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 28
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(b) Remove between Frame 39.1 and Frame 40 on the LH and RH sides, as shown on
Fig. A-FBAAA
:
Refer to AMM Task 21-20-00-010-801.
2 Duct Item (1) Retain
2 Duct Item (2) Retain
(c) Remove, as shown on Fig. A-FBAAA
:
Refer to AMM Task 21-21-51-000-801 and AMM Task 21-21-41-000-801.
2 Recirculation Fan Item (3) Retain
2 Recirculation Filter Item (4) Retain
(d) Remove, as shown on Fig. A-FBBAA
:
3
 Bolt
 Item (31
) Retain
3
 Washer
 Item (32
) Retain
1
 Strip - Bonding
 Item (37
) Retain
3
 Clamp
 Item (33
) Retain
1
 Air Supply Pipe Assy
 Item (34
) Retain
(e) Remove the necessary insulation blankets to access work area, refer to AMM Task
25-80-00-000-801.
**CONF 003
(1) Subtask 574138-941-001-001 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 12-34-24-860-802
Task 21-20-00-010-801
Task 25-80-00-000-801
Task 28-00-00-610-801
Task 28-10-00-910-805
Task 28-25-00-650-803
Task 32-12-00-010-801
Task 52-30-00-010-801
Task 53-35-13-000-802
Task 57-17-11-000-801
NOTE
: For the basic Aircraft configuration, refer to AMM Chapter "Introduction -
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 29
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Aircraft status for maintenance" in Manual Front Matter section.
(a) Make sure that the aircraft is electrically grounded, refer to AMM Task
12-34-24-860-802.
(b) Put an access platform in position at 821 Forward (FWD) Cargo-Compartment Door
(CCD) and Main Landing Gear (MLG) doors.
(c) Open the 821 FWD CCD, refer to AMM Task 52-30-00-010-801.
(d) Defuel the center fuel tank, refer to AMM Task 28-25-00-650-803.
(e) Purge and vent the center fuel tanks for maintenance, refer to AMM Task
28-00-00-610-801 and AMM Task 28-10-00-910-805.
(f) Open the Main Landing Gear (MLG) doors, refer to AMM Task 32-12-00-010-801.
(g) Remove the covers 147AZ and 148AZ for access, refer to AMM Task
57-17-11-000-801.
(h) Remove the access panels 191FB, 192GB and 192JB, refer to AMM Task
53-35-13-000-802
.
(2) Subtask 574138-010-003-001 - Remove/Open for Access in the FWD Cargo-
Compartment
Work Zones and Access Panels
Zone
 Access/Work location
130
 Work location
 from Frame 39.1 to Frame 40
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 21-20-00-010-801
Task 21-21-41-000-801
Task 21-21-51-000-801
Task 25-52-00-000-801
Task 25-80-00-000-801
Fig. A-FBAAA
Removal/Installation of the Air
Conditioning Ducts between FR39.1 and
FR40, FWD Cargo-Compartment
Sheet 01
Fig. A-FBBAA
Removal/Installation of the Air Supply
Pipe Assy
Sheet
 01
WARNING
: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR
CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A
GROUND SOURCE.
HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 30
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CAUTION
: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.
(a) Remove the ceiling panels, partition panels and sidewall panels in the FWD cargo
compartment 131CX, 131DX, 132CX, 132DX and 131BX, refer to AMM Task
25-52-00-000-801.
(b) Remove between Frame 39.1 and Frame 40 on the LH and RH sides, as shown on
Fig. A-FBAAA
:
Refer to AMM Task 21-20-00-010-801.
2 Duct Item (1) Retain
2 Duct Item (2) Retain
(c) Remove, as shown on Fig. A-FBAAA
:
Refer to AMM Task 21-21-51-000-801 and AMM Task 21-21-41-000-801.
2 Recirculation Fan Item (3) Retain
2 Recirculation Filter Item (4) Retain
(d) Remove, as shown on Fig. A-FBBAA
:
3
 Bolt
 Item (31
) Retain
3
 Washer
 Item (32
) Retain
1
 Strip - Bonding
 Item (37
) Retain
3
 Clamp
 Item (33
) Retain
1
 Air Supply Pipe Assy
 Item (34
) Retain
(e) Remove the necessary insulation blankets to access work area, refer to AMM Task
25-80-00-000-801.
**CONF ALL
C. PROCEDURE
**CONF 001
(1) Subtask 574138-831-001-001 - Remove the Fastener from the Holes 12, 14, 260,
261, 262 and 263 between STGR37 and STGR38 at FR40, LH Side
Work Zones and Access Panels
Zone
 Access/Work location
131
 Work location
 Frame 40
from Stringer 37 LH to Stringer 38 LH
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 31
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Manpower Resources
Manhours
 2.00
Minimum number of person
 2
Subtask elapsed time
 1.00
Skills
 AIRFRAME
Material necessary to do the job
Consumable CMLA01
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
Structural Repair Manual (SRM)
 51-42-00
Fig. A-FBEAA
Removal/Installation of the Fasteners
between STGR37 and STGR38 at FR40
on the LH and RH Sides
Sheet 01
Sheet 02
Sheet 03
(a) Remove, as shown on Fig. A-FBEAA Sheet 01
 view B and Fig. A-FBEAA Sheet 02
view D:
1
 Bolt
 Item (35
) Discard
1
 Nut
 Item (36
) Discard
NOTE
: Remove the bolt and nut only if necessary for access.
(b) Remove, as shown on Fig. A-FBEAA
 and in accordance with SRM 51-42-00:
3 Bolt Item (12) Discard
1 Bolt Item (14) Discard
1 Bolt Item (16) Discard
1 Bolt Item (17) Discard
4 Nut Item (13) Discard
1 Nut Item (15) Discard
1 Nut Item (18) Discard
1 Washer Item (19) Discard
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 32
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SERVICE BULLETIN
(c) Remove the old sealant with a non metallic spatula.
(d) Clean the work area with:
Textile - Lint Free
Cotton
14SBA1 As required
and
Non Aqueous
Cleaner - General
08BAA9 As required
(2) Subtask 574138-832-001-001 - Do an Inspection of Fastener Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40, LH Side
Work Zones and Access Panels
Zone
 Access/Work location
131
 Work location
 Frame 40
from Stringer 37 LH to Stringer 38 LH
Manpower Resources
Manhours
 1.00
Minimum number of person
 2
Subtask elapsed time
 0.50
Skills
 NON DESTRUCTIVE
TESTING
References
Non Destructive Test Manual (NTM)
 51-10-01
(a) Do a rotating probe test of fastener holes in accordance with NTM 51-10-01.
1
 In case of crack finding in the fasteners holes, contact AIRBUS before next
flight and follow their instructions.
2
 In case of no crack findings, do a cold working of the fastener holes in
accordance with SUBTASK 574138-831-002 001 Do a Cold Working of
Fastener Holes 12, 14, 260, 261, 262 and 263 between STGR37 and STGR38
at FR40, LH Side
(3) Subtask 574138-831-002-001 - Do a Cold Working of Fastener Holes 12, 14, 260,
261, 262 and 263 between STGR37 and STGR38 at FR40, LH Side
Work Zones and Access Panels
Zone
 Access/Work location
131
 Work location
 Frame 40
from Stringer 37 LH to Stringer 38 LH
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 33
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Manpower Resources
Manhours
 5.50
Minimum number of person
 2
Subtask elapsed time
 2.75
Skills
 AIRFRAME
Material necessary to do the job
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Wash Primer - Structure
 04CMA2
 As required
Primer Polyurethane Paint -
Corrosion Inhibiting
04EAC2
 As required
Non Aqueous Cleaner -
General
08BAA9
 As required
Textile - Lint Free Cotton
 14SBA1
 As required
Standard tool TOOLA01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA340574138-1
 Durable Tooling
 1
 (1)
EKA340574138-1
 Expendable Tooling
 1
 (2)
FTIA340574138-1
 Capital Tooling
 1
 (3)
NOTE
: 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. DK-A340-57-4138-1
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 ISI
51.48.00001.
NOTE
 (2)
: Expendable tooling: Ref. EK-A340-57-4138-1
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. FTI-A340-57-4138-1
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: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 34
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Standard tool TOOLA02
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA340574138-1
 Durable Tooling
 1
 (1)
EKA340574138-1
 Expendable Tooling
 1
 (2)
WCIA340574138-1
 Capital Tooling
 1
 (3)
NOTE
: 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. DK-A340-57-4138-1
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 ISI
51.48.00001.
NOTE
 (2)
: Expendable tooling: Ref. EK-A340-57-4138-1
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. WCI-A340-57-4138-1
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
Structural Repair Manual (SRM)
 51-44-00
51-48-00
51-70-20
51-75-12
Fig. A-FBEAA
Removal/Installation of the Fasteners
between STGR37 and STGR38 at FR40
on the LH and RH Sides
Sheet 01
Sheet 02
Sheet 03
(a) Do a check of the existing hole diameters and compare with values as shown on
Fig. A-FBEAA
.
1
 In case the existing hole diameter is more than or equal to the minimum
starting hole diameter, please contact AIRBUS for further instructions before
next flight.
2
 In case the hole diameter is less than the minimum starting hole diameter, do
the next step.
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 35
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(b) Drill and ream the fastener holes to the correct starting hole diameter as shown
onFig. A-FBEAA
 and in accordance with SRM 51-44-00 and SRM 51-48-00.
Refer to FTI Tool list No.:
DKA340574138-1 Durable Tooling 1
or
Refer to WCI Tool list No.:
DKA340574138-1 Durable Tooling 1
(c) Clean the drilled holes with:
Textile - Lint Free
Cotton
14SBA1
 As required
and
Non Aqueous
Cleaner - General
08BAA9
 As required
(d) If necessary, perform spotfacing to the related fastener head depth, refer to SRM
51-70-20.
(e) Renew the protective finish in accordance with SRM 51-75-12:
Wash Primer -
Structure
04CMA2
 As required
and
Primer
Polyurethane Paint
- Corrosion
Inhibiting
04EAC2
 As required
(f) Do a cold working of the fastener holes.
1
 Install split sleeves as shown on Fig. A-FBEAA
Refer to FTI Tool list No.:
EKA340574138-1 Expendable Tooling 1
or
Refer to WCI Tool list No.:
EKA340574138-1 Expendable Tooling 1
2
 Do a cold working of the fastener holes in accordance with SRM 51-48-00.
Refer to FTI Tool list No.:
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 36
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FTIA340574138-1 Capital Tooling 1
or
Refer to WCI Tool list No.:
WCIA340574138-1 Capital Tooling 1
3
 Remove the split sleeves.
(g) Ream the fastener holes to the final hole diameter, as shown on Fig. A-FBEAA
 and
in accordance with SRM 51-44-00 and SRM 51-48-00.
Refer to FTI Tool list No.:
DKA340574138-1 Durable Tooling 1
or
Refer to WCI Tool list No.:
DKA340574138-1 Durable Tooling 1
(h) Clean the drilled holes with:
Textile - Lint Free
Cotton
14SBA1
 As required
and
Non Aqueous
Cleaner - General
08BAA9
 As required
(4) Subtask 574138-831-003-001 - Install the Fastener in the Holes 12, 14, 260, 261, 262
and 263 between STGR37 and STGR38 at FR40, LH Side
Work Zones and Access Panels
Zone
 Access/Work location
131
 Work location
 Frame 40
from Stringer 37 LH to Stringer 38 LH
Manpower Resources
Manhours
 2.50
Minimum number of person
 2
Subtask elapsed time
 1.25
Skills
 AIRFRAME
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 37
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Material necessary to do the job
Kit 574138A01R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
20
 EN6115K7-16
 3
 BOLT
21
 ASNA2531-7
 5
 NUT
22
 EN6115K6-20
 1
 BOLT
23
 ASNA2531-6
 1
 NUT
24
 EN6115K7-22
 1
 BOLT
25
 EN6115K7-18
 1
 BOLT
Component COMPA01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
35
 EN6115V4X11
 1
 BOLT
36
 ASNA2531-4
 1
 NUT
NOTE
: The components listed above are only necessary if the fasteners are to
be removed for access, depending on the aircraft configuration. The
quantity of these items are to be ordered as required.
NOTE
: The above list of components is not an AIRBUS Kit, the required parts
shall be ordered as necessary through the given channel.
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Primer Polyurethane Paint -
Corrosion Inhibiting
04EAC2
 As required
Polyurethane Coating - Fuel
Vapour Barrier Structure
04PAG2
 As required
Polysulfide Sealant - Fuel
Tank Brushable
06ABA1
 As required
Coating Sealant - Fuel Tank
Brushable
06HAA1
 As required
Adhesion Promoter - For
Polysulfide Sealant
06PAG1
 As required
Non Aqueous Cleaner -
General
08BAA9
 As required
Corrosion Preventive
Compound - Water
Displacing
12ADB1
 As required
Textile - Lint Free Cotton
 14SBA1
 As required
References
Aircraft Maintenance Manual (AMM)
 Task 20-21-11-911-801
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 38
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References
Structural Repair Manual (SRM)
 51-42-00
51-75-12
51-76-12
Fig. A-FBEAA
Removal/Installation of the Fasteners
between STGR37 and STGR38 at FR40
on the LH and RH Sides
Sheet 01
Sheet 02
Sheet 03
(a) Install the fasteners to the aircraft structure.
1
 Wet install in accordance with SRM 51-42-00, refer to Fig. A-FBEAA
 and AMM
Task 20-21-11-911-801.
3 Bolt EN6115K7-16 Item 20
1 Bolt EN6115K6-20
 Item 22
1 Bolt EN6115K7-22 Item 24
1 Bolt EN6115K7-18 Item 25
5 Nut ASNA2531-7 Item 21
1 Nut ASNA2531-6 Item 23
with
Polysulfide Sealant
- Fuel Tank
Brushable
06ABA1
 As required
2
 Install, as shown on Fig. A-FBEAA Sheet 01
 view C and Fig. A-FBEAA Sheet
02
 view E:
Refer to AMM Task 20-21-11-911-801.
1
 Bolt
 EN6115V4X11
 Item 35
1
 Nut
 ASNA2531-4
 Item 36
NOTE
: Install the bolt and nut only if removed.
3
 Clean the work area with:
Textile - Lint Free
Cotton
14SBA1
 As required
and
Non Aqueous
Cleaner - General
08BAA9
 As required
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 39
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 58

@A340
SERVICE BULLETIN
(b) Apply protective finish on the fasteners, refer to Fig. A-FBEAA
.
1
 Apply to the bolt head of hole H12 inside the center fuel tank, in accordance
with SRM 51-76-12:
Adhesion Promoter
- For Polysulfide
Sealant
06PAG1
 As required
Polysulfide Sealant
- Fuel Tank
Brushable
06ABA1
 As required
Coating Sealant -
Fuel Tank
Brushable
06HAA1
 As required
2
 Apply to the bolt heads of holes H14, H260, H261, H262 and H263 outside
the center fuel tank, in accordance with
 SRM 51-75-12:
Primer
Polyurethane Paint
- Corrosion
Inhibiting
04EAC2
 As required
Polyurethane
Coating - Fuel
Vapour Barrier
Structure
04PAG2
 As required
Corrosion
Preventive
Compound - Water
Displacing
12ADB1
 As required
3
 Apply to the nut of hole H12 outside the center fuel tank, in accordance with
SRM 51-75-12:
Primer
Polyurethane Paint
- Corrosion
Inhibiting
04EAC2
 As required
Polyurethane
Coating - Fuel
Vapour Barrier
Structure
04PAG2
 As required
Corrosion
Preventive
Compound - Water
Displacing
12ADB1
 As required
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 40
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 59

@A340
SERVICE BULLETIN
4
 Apply to the nuts of holes H14, H260, H261, H262 and H263 inside the center
fuel tank, in accordance with SRM 51-76-12:
Adhesion Promoter
- For Polysulfide
Sealant
06PAG1 As required
Polysulfide Sealant
- Fuel Tank
Brushable
06ABA1
 As required
Coating Sealant -
Fuel Tank
Brushable
06HAA1
 As required
(5) Subtask 574138-831-004-001 - Remove the Fastener from the Holes 12, 14, 260,
261, 262 and 263 between STGR37 and STGR38 at FR40, RH Side
Work Zones and Access Panels
Zone
 Access/Work location
132
 Work location
 Frame 40
from Stringer 37 RH to Stringer 38 RH
Manpower Resources
Manhours
 2.00
Minimum number of person
 2
Subtask elapsed time
 1.00
Skills
 AIRFRAME
Material necessary to do the job
Consumable CMLA01
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
Structural Repair Manual (SRM)
 51-42-00
Fig. A-FBEAA
Removal/Installation of the Fasteners
between STGR37 and STGR38 at FR40
on the LH and RH Sides
Sheet 01
Sheet 02
Sheet 03
(a) Remove, as shown on Fig. A-FBEAA Sheet 01
 view B and Fig. A-FBEAA Sheet 02
view D:
1
 Bolt
 Item (35
) Discard
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 41
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 60

@A340
SERVICE BULLETIN
1
 Nut
 Item (36
) Discard
NOTE
: Remove the bolt and nut only if necessary for access.
(b) Remove as shown on Fig. A-FBEAA
 and in accordance with SRM 51-42-00:
3 Screw Item (12) Discard
1 Bolt Item (14) Discard
1 Bolt Item (16) Discard
1 Bolt Item (17) Discard
4 Nut Item (13) Discard
1 Nut Item (15) Discard
1 Nut Item (18) Discard
1 Washer Item (19) Discard
(c) Remove the old sealant with a non metallic spatula.
(d) Clean the work area with:
Textile - Lint Free
Cotton
14SBA1 As required
and
Non Aqueous
Cleaner - General
08BAA9 As required
(6) Subtask 574138-832-002-001 - Do an Inspection of Fastener Holes 12, 14, 260, 261,
262 and 263 between STGR37 and STGR38 at FR40, RH Side
Work Zones and Access Panels
Zone
 Access/Work location
132
 Work location
 Frame 40
from Stringer 37 RH to Stringer 38 RH
Manpower Resources
Manhours
 1.00
Minimum number of person
 2
Subtask elapsed time
 0.50
Skills
 NON DESTRUCTIVE
TESTING
DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4138
REVISION No.: 01 - Feb 13/18 Page: 42
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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