# Airbus Service Bulletin A330-57-3114

## Copies (2)

Copies the FAA filed in AD dockets on regulations.gov, newest revision first. A newer revision may exist.

- Revision 01 ("A330-57-3114 R01"), 144 pages: PDF https://openairdocs.org/files/sha256/cb/24/cb24c0ef5a227da0b8be1b0295886960d40edf2ecb9c358817abecfcfe63274f; text https://openairdocs.org/service-documents/airbus/a330-57-3114/file/cb24c0ef5a22.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.
- FAA-2016-6899 SB A330-57-3114 R00 ("FAA-2016-6899 SB A330-57-3114 R00"), 105 pages: PDF https://openairdocs.org/files/sha256/42/b9/42b9e17d2fb9def8c54b569cc26f7c33134a201cd0f7a416409acf8d0171bfeb; text https://openairdocs.org/service-documents/airbus/a330-57-3114/file/42b9e17d2fb9.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-6899; AD 2016-12-09 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A330-57-3114
- Latest revision known: A330-57-3114, Revision 01, dated January 13, 2017 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a330-57-3114

## ADs that cite it (2) (OpenAirDocs)

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

- [AD 2016-12-09](https://openairdocs.org/ad/2016-12-09.md), effective Jun 29, 2016: No revision named
- [AD 2016-09-11](https://openairdocs.org/ad/2016-09-11.md), effective Jun 13, 2016: No revision named

Also cited in [2 proposed ADs](https://openairdocs.org/service-documents/airbus/a330-57-3114/proposed.md).

## Text (144 pages)

Revision 01, the newest copy. 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

@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 57
TITLE: WINGS - CENTER WING BOX - I NSPECTION OF FASTENER HOLES AT
FRAME 40 VERTICAL WEB BELOW INTRADOS
MODIFICATION No.: None
This page transmits Revision No.01 of Service Bulletin No.A330-57-3114
ADDITIONAL WORK
**CONF ALL
No additional work is required by this revision for aircraft modified by any previous issue.
REASON
Revision No. 01 issued to split kit A01 in order to facilitate the Service Bulletin embodiment.
CHANGES
The main changes of this revision are:
- Kit 573114A01 revised
- Kits 573114A02 and 573114A03 created
- CML references updated
- PREPARATION and CL OSE-UP paragraphs updated
- Illustrations updated
- Appendix 01 - Inspection Report created
- Minors changes applied.
Some revision bars are produced due to a text amendment to change ’(Refer to...)’ into ’in accordance
with’.
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 2

@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
SUMMARY
REASON/DESCRIPTION/OPERATIONAL
CONSEQUENCES
REASON UPDATED
 R
GENERAL EVALUATION
 GENERAL EVALUATION TABLE UPDATED
 R
MATERIAL PRICE INFORMATION
 MATERIAL PRICE INFORMATION TABLE
UPDATED
R
EFFECTIVITY
 OPERATOR LIST UPDATED
 R
REFERENCES / REPERCUSSIONS
 REFERENCES/REPERCUSSIONS TABLE
UPDATED
R
MANPOWER
 MANPOWER UPDATED
 R
APPENDICES
 APPENDICES UPDATED
 R
Fig. A-FSAAA
Fig. A-FSAAA Sheet 01
 SHEET UPDATED
 R
PLANNING INFORMATION
EFFECTIVITY
 EFFECTIVITY RELATED INFORMATION
UPDATED
R
Configuration definition
CONF 001
 CONFIGURATION DEFINITION UPDATED
 R
Material Effectivity
 MATERIAL EFFECTIVITY UPDATED
MATERIAL SET QUANTITY UPDATED
MATERIAL SET UPDATED
R
REASON
History
 HISTORY UPDATED
 R
Objective/Action
 OBJECTIVE/ACTION UPDATED
 R
Advantages
 ADVANTAGES UPDATED
 R
Operational/Maintenance
Consequences
OPERATIONAL/MAINTENANCE CONSEQUENCES
UPDATED
R
COMPLIANCE
Accomplishment Timescale
 ACCOMPLISHMENT TIMESCALE UPDATED
 R
MANPOWER
 MANPOWER UPDATED
 R
REFERENCES
 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 PRICE UPDATED
MATERIAL SET UPDATED
R
INDUSTRY SUPPORT INFORMATION
 INDUSTRY SUPPORT INFORMATION UPDATED
 R
LIST OF COMPONENTS
 LIST OF COMPONENTS UPDATED
 R
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 3

@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Kit 573114A01R05
 PART MATERIAL SET UPDATED
MATERIAL SET LABEL UPDATED
QUANTITY UPDATED
ITEM NUMBER UPDATED
PART NUMBER UPDATED
KEYWORD UPDATED
R
Kit 573114A02R00
 PART MATERIAL SET ADDED
 N
Kit 573114A03R00
 PART MATERIAL SET ADDED
 N
LIST OF MATERIALS - OPERATOR
SUPPLIED
Consumable Materials
 CONSUMABLE MATERIALS UPDATED
 R
Consumable CMLA01
 CONSUMABLE MATERIAL SET UPDATED
CONSUMABLE UPDATED
QUANTITY UPDATED
R
Components
 COMPONENTS UPDATED
 R
TOOLING
Tools
 TOOLS UPDATED
 R
ACCOMPLISHMENT INSTRUCTIONS
TASK 573114- 832-801-001-Inspection
 TASK SOLUTION UPDATED
NOTE UPDATED
CAUTION UPDATED
R
Task associated data - 001
 MAN HOURS UPDATED
ELAPSED TIME UPDATED
R
Subtask 573114-910-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
REFERENCES UPDATED
R
Subtask 573114-941-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
NOTE UPDATED
R
Subtask 573114-010-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
FIN UPDATED
REFERENCES UPDATED
R
Subtask 573114-010-002-001
 SUBTASK SOLUTION UPDATED
 R
Subtask 573114-941-006-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
R
Subtask 573114-110-001-001
 SUBTASK SOLUTION UPDATED
CONSUMABLE UPDATED
QUANTITY UPDATED
MATERIAL LIST UPDATED
R
Subtask 573114-210-001-001
 SUBTASK SOLUTION UPDATED
 R
Subtask 573114-832-001-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
R
Subtask 573114-832-006-001
 SUBTASK SOLUTION UPDATED
 R
Subtask 573114-832-002-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
R
Subtask 573114-832-007-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
R
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 3
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 4

@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Subtask 573114-832-003-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
REFERENCES UPDATED
R
Subtask 573114-832-008-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
REFERENCES UPDATED
R
Subtask 573114-832-004-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
REFERENCES UPDATED
R
Subtask 573114-832-009-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
REFERENCES UPDATED
R
Subtask 573114-832-005-001
 SUBTASK SOLUTION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
REFERENCES UPDATED
R
Subtask 573114-832-010-001
 SUBTASK SOLUTION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
REFERENCES UPDATED
R
Subtask 573114-700-003-001
 SUBTASK SOLUTION UPDATED
CONFIGURATION UPDATED
PANEL UPDATED
NOTE UPDATED
R
Subtask 573114-410-001-001
 SUBTASK SOLUTION UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
NOTE UPDATED
CONFIGURATION UPDATED
FIN UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 573114-410-002-001
 SUBTASK SOLUTION UPDATED
CONFIGURATION UPDATED
NOTE UPDATED
R
Subtask 573114-942-006-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
NOTE UPDATED
CONFIGURATION UPDATED
ZONE UPDATED
R
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 4
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 5

@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Subtask 573114-942-001-001
 SUBTASK SOLUTION UPDATED
REFERENCES UPDATED
REFERENCED DOCUMENTATION UPDATED
PANEL UPDATED
R
TASK 573114- 833-801-001-Repair
 TASK SOLUTION UPDATED
CAUTION UPDATED
NOTE UPDATED
R
Task associated data - 001
 MAN HOURS UPDATED
ELAPSED TIME UPDATED
R
Subtask 573114-910-002-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
REFERENCES UPDATED
R
Subtask 573114-941-003-001
 SUBTASK SOLUTION UPDATED
NOTE UPDATED
R
Subtask 573114-010-003-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
FIN UPDATED
REFERENCES UPDATED
R
Subtask 573114-010-004-001
 SUBTASK SOLUTION UPDATED
 R
Subtask 573114-941-005-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
R
Subtask 573114-110-002-001
 SUBTASK SOLUTION UPDATED
CONSUMABLE UPDATED
MATERIAL LIST UPDATED
R
Subtask 573114-210-002-001
 SUBTASK SOLUTION UPDATED
 R
Subtask 573114-833-001-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 573114-833-012-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 573114-833-007-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 5
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 6

@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Subtask 573114-833-013-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 573114-833-002-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 573114-833-014-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
NOTE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 573114-833-003-001
 SUBTASK SOLUTION UPDATED
FIGURE REFERENCE UPDATED
REFERENCES UPDATED
R
Subtask 573114-833-015-001
 SUBTASK SOLUTION UPDATED
FIGURE REFERENCE UPDATED
REFERENCES UPDATED
R
Subtask 573114-833-011-001
 SUBTASK SOLUTION UPDATED
FIGURE REFERENCE UPDATED
REFERENCES UPDATED
R
Subtask 573114-833-016-001
 SUBTASK SOLUTION UPDATED
FIGURE REFERENCE UPDATED
REFERENCES UPDATED
R
Subtask 573114-833-010-001
 SUBTASK SOLUTION UPDATED
FIGURE REFERENCE UPDATED
REFERENCES UPDATED
R
Subtask 573114-833-017-001
 SUBTASK SOLUTION UPDATED
FIGURE REFERENCE UPDATED
REFERENCES UPDATED
R
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 6
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 7

@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Subtask 573114-833-005-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
CONFIGURATION UPDATED
NOTE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 573114-833-018-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
CONFIGURATION UPDATED
NOTE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 573114-833-009-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
CONFIGURATION UPDATED
NOTE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 573114-833-019-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
CONFIGURATION UPDATED
NOTE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 573114-833-006-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
CONFIGURATION UPDATED
NOTE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 7
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 8

@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Subtask 573114-833-020-001
 SUBTASK SOLUTION UPDATED
QUANTITY UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
FIGURE REFERENCE UPDATED
CONFIGURATION UPDATED
NOTE UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 573114-700-002-001
 SUBTASK SOLUTION UPDATED
CONFIGURATION UPDATED
PANEL UPDATED
NOTE UPDATED
R
Subtask 573114-942-002-001
 SUBTASK SOLUTION UPDATED
CONSUMABLE UPDATED
REFERENCED DOCUMENTATION UPDATED
NOTE UPDATED
CONFIGURATION UPDATED
FIN UPDATED
MATERIAL LIST UPDATED
REFERENCES UPDATED
R
Subtask 573114-942-003-001
 SUBTASK SOLUTION UPDATED
CONFIGURATION UPDATED
NOTE UPDATED
R
Subtask 573114-942-004-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
NOTE UPDATED
CONFIGURATION UPDATED
ZONE UPDATED
R
Subtask 573114-942-005-001
 SUBTASK SOLUTION UPDATED
REFERENCES UPDATED
REFERENCED DOCUMENTATION UPDATED
PANEL UPDATED
R
Fig. A-FCBAA
 FIGURE SOLUTION UPDATED
 R
Fig. A-FCBAA Sheet 01
 SHEET UPDATED
 R
Fig. A-FCBAA Sheet 02
 SHEET UPDATED
 R
Fig. A-FCBAA Sheet 03
 SHEET ADDED
 N
Fig. A-FDAAA
 FIGURE SOLUTION UPDATED
 R
Fig. A-FDBAA
 FIGURE SOLUTION UPDATED
 R
Fig. A-FDCAA
 FIGURE SOLUTION UPDATED
 R
Fig. A-FBAAA
 FIGURE SOLUTION UPDATED
 R
Fig. A-FBAAA Sheet 02
 SHEET UPDATED
 R
Fig. A-FCAAA
 FIGURE SOLUTION UPDATED
 R
Fig. A-FCAAA Sheet 01
 SHEET UPDATED
 R
Fig. A-FCAAA Sheet 02
 SHEET UPDATED
 R
Fig. A-FCAAA Sheet 03
 SHEET ADDED
 N
Fig. A-FCAAA Sheet 04
 SHEET ADDED
 N
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 8
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 9

@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Fig. A-FCCAA
 FIGURE SOLUTION UPDATED
 R
Fig. A-FCCAA Sheet 01
 SHEET UPDATED
 R
Fig. A-FCCAA Sheet 02
 SHEET UPDATED
 R
Fig. A-FCCAA Sheet 03
 SHEET ADDED
 N
Fig. A-FCCAA Sheet 04
 SHEET ADDED
 N
Fig. A-FEAAA
 FIGURE SOLUTION ADDED
 N
Fig. A-FEAAA Sheet 01
 SHEET ADDED
 N
Fig. A-FEAAA Sheet 02
 SHEET ADDED
 N
Fig. A-FEAAA Sheet 03
 SHEET ADDED
 N
Fig. A-FEAAA Sheet 04
 SHEET ADDED
 N
Fig. A-FFAAA
Fig. A-FFAAA Sheet 01
 SHEET UPDATED
 R
Fig. A-FFAAA Sheet 02
 SHEET UPDATED
 R
Fig. A-FFAAA Sheet 03
 SHEET UPDATED
 R
Fig. A-FFAAA Sheet 04
 SHEET UPDATED
 R
Appendix 01 - Inspection Report
APPENDIX CONTENT
 APPENDIX CONTENT ADDED
 N
Fig. A-FAAAA
 FIGURE SOLUTION ADDED
 N
Fig. A-FAAAA Sheet 01
 SHEET ADDED
 N
Fig. A-FAAAA Sheet 02
 SHEET ADDED
 N
Fig. A-FAAAA Sheet 03
 SHEET ADDED
 N
Fig. A-FAAAA Sheet 04
 SHEET ADDED
 N
APPENDIX
 APPENDIX DELETED
 D
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: Mar 12/13
REVISION No. : 01 - Jan 13/17
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 9
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 10

@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
This Page Intentionally Left Blank
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 10
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 11

@A330
SERVICE BULLETIN
SUMMARY
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
This summary is for information only and is not approved for modification of the aircraft.
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 57
TITLE: WINGS - CENTER WING BOX - I NSPECTION OF FASTENER HOLES AT
FRAME 40 VERTICAL WEB BELOW INTRADOS
**CONF ALL
MODIFICATIONS
None
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
During Airworthiness Limitation Items (ALI) 57-11-04 inspections tasks on the rear fitting of the
 Frame
40 between stringer 38 and 39 LH/RH sides, cracks have been found on the fasteners next to the one
to be inspected.
After reaming at second oversize of the subjected hole, the crack is still present.
This Service Bulletin mandates the Inspection of the fasteners holes at
 Frame 40 Vertical Web between
stringer 38 and 39 - below Intrados, left and right sides for all A330 aircraft pre-modification No.
44360S13013 and 44360S13482 embodiment.
The aim of this Inspection Service Bulletin (ISB) is to implement the corrective inspection necessary to
the in-service aircraft.
For aircraft on which
 Frame 40 web is already repaired on one side or on both sides as per Repair
Instruction R57115092, Inspection task of this ISB is not necessary for the repaired side(s); dedicated
Repair Design Approval Sheet (RDAS) instructions have to be followed.
For aircraft previously inspected as per Technical Disposition Ref. LR57D11029171 or
LR57D11030741, next inspection is due based on interval value given in this ISB.
The procedure as described in this Service Bulletin is to be performed if no Airbus repair and/or repair
improvement has been previously performed in the same area. In case of repairs performed previously,
please contact AIRBUS Repair Support department for further instructions.
Accomplishment of this ISB will permit early detection of cracks on the
 Frame 40 Vertical Web between
stringer 38 and 39 - below Intrados, left and right sides and will ensure that the structural integrity of the
area is maintained.
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 12

@A330
SERVICE BULLETIN
SUMMARY
The Task ALI 57-11-04 applicable to aircraft pre-modification No. 44360S13013 and 44360S13482 will
be superseded by accomplishment of this Service Bulletin No. A330-57-3114
 .
GENERAL EVALUATION
EVALUATION TABLE
COMPLIANCE
 MANDATORY (1)
 CANCELS INSPECTION SB
 NO
POTENTIAL AD
 YES
 A/C OPERATION AFFECTED
 NO
RELIABILITY AFFECTED
 NO
 PAX COMFORT AFFECTED
 NO
COST SAVING
 NO
 ETOPS AFFECTED
 NO
STRUCTURAL LIFE EXTN
 NO
 VENDOR SB INVOLVED
 NO
NOTE
 (1)
: Service Bulletin must be accomplished.
MATERIAL PRICE INFORMATION
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit
 573114A01R05
 2
 10,040.00
 Screws, Nuts
Kit
 573114A02R00
 2
 7,480.00
 Screws, Nuts
Kit
 573114A03R00
 2
 6,040.00
 Screws, Nuts
TOTAL
 23,560.00
EFFECTIVITY
This Service Bulletin is applicable to this (these) operator(s) :
56O
 83V
 98W
 BEL CPA F2I
 GIA HDA HFY KAL OHY RSY SAI
THA TSC U6A
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
 OIT Ref. 999.0082/12
OTHER
 OIT Ref. 999.0086/11
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 13

@A330
SERVICE BULLETIN
SUMMARY
HARD
 NO
SOFT
 NO
OBRM
 NO
MANPOWER
Task 573114-832-801-001: Inspection
TOTAL MANHOURS
 51.25
ELAPSED TIME (HOURS)
 51.25
Task 573114-833-801-001: Repair
TOTAL MANHOURS
 63.25
ELAPSED TIME (HOURS)
 63.25
APPENDICES
Appendix 01 - Inspection Report
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 3
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SERVICE BULLETIN
SUMMARY
**CONF ALL
HOLES OF AREA A TO BE INSPECTED.
A
B
NOTE:
FASTENER NOT AFFECTED.
 − Z141 Z142
FR40
VIEW LOOKING AFT
LH SHOWN
RH SYMMETRICAL
A
FR40
FR47
B
STGR38
STGR39
STGR40
CENTER WING BOX LOWER PANEL REFERENCE
HOLE OF AREA B TO BE INSPECTED. G_SB_573114_5_SAAA_01_07
Figure A-FSAAA - Sheet 01
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 4
5
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SERVICE BULLETIN
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 57
TITLE: WINGS - CENTER WING BOX - I NSPECTION OF FASTENER HOLES AT
FRAME 40 VERTICAL WEB BELOW INTRADOS
MODIFICATION No.: None
This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the
property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with
any information contained in it. It is delivered on the express condition that said document and the
information contained in it shall be treated as confidential, shall not be used for any purpose other than
that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall
not be duplicated in any manner (except for the purposes of performing the tasks described hereunder
and provided that any recipient of such document shall comply with the conditions herein), without
AIRBUS prior written consent.
1. PLANNING INFORMATION
**CONF ALL
A. EFFECTIVITY
NOTE
: This Service Bulletin is only applicable to aircraft on which Modification No.
44360S13013 and 44360S13482 are not embodied.
(1) Models
330-301 330-321 330-322 330-341 330-342
(2) Effectivity by MSN
0012 0017 0030 0037 0045 0050 0054-0055 0060 0062 0064-0065
 0070-0072
0082-0083 0086-0087 0095-0096 0098-0099
 0102 0106
 0109
 0111-0113
 0116 0118
0120-0122
 0127 0132 0138 0140 0143-0144 0148 0153 0155 0162 0165 0171-0172
(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.
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 1
5
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SERVICE BULLETIN
OPERATOR
 MSN
56O
 0116
83V
 0171
98W
 0054
BEL
 0030 0037 0045 0082 0095
CPA
 0102 0113 0121
F2I
 0070
 0087
GIA
 0138 0140 0144 0148 0153 0165
HDA
 0012
 0017
 0071 0083 0099 0106 0109 0118
 0155
HFY
 0127
KAL
 0162 0172
OHY
 0072 0098 0143
RSY
 0096
 0120
SAI
 0055 0086
THA
 0050 0060 0062 0065 0112 0122
TSC
 0111 0132
U6A
 0064
(4) Configuration by MSN
MSN
 CONFIGURATION
0012 0017 0030 0037 0045 0050 0054 0055 0060 0062 0064
0065 0070 0071 0072 0082 0083 0086 0087 0095 0096 0098
0099 0102 0106 0109 0111 0112 0113 0116 0118 0120 0121
0122 0127 0132 0138 0140 0143 0144 0148 0153 0155 0162
0165 0171 0172
001
(5) Configuration definition
**CONF 001
Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a
standard configuration.
(6) Material Effectivity
MATERIAL
 QTY PER A/C
 SEE NOTES
Kit
 573114A01R05
 2
Kit
 573114A02R00
 2
Kit
 573114A03R00
 2
Consumable CMLA01
 1
B. CONCURRENT REQUIREMENTS
None
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 2
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SERVICE BULLETIN
C. REASON
(1) History
During Airworthiness Limitation Items (ALI) 57-11-04 inspections tasks on the rear fitting
of the
 Frame 40 between stringer 38 and 39 LH/RH sides, cracks have been found on
the fasteners next to the one to be inspected.
After reaming at second oversize of the subjected hole, the crack is still present.
(2) Objective/Action
This Service Bulletin mandates the Inspection of the fasteners holes at
 Frame 40
Vertical Web between stringer 38 and 39 - below Intrados, left and right sides for all
A330 aircraft pre-modification No. 44360S13013 and 44360S13482 embodiment.
The aim of this Inspection Service Bulletin (ISB) is to implement the corrective inspection
necessary to the in-service aircraft.
For aircraft on which
 Frame 40 web is already repaired on one side or on both sides as
per Repair Instruction R57115092
 , Inspection task of this ISB is not necessary for the
repaired side(s); dedicated Repair Design Approval Sheet (RDAS) instructions have to
be followed.
For aircraft previously inspected as per Technical Disposition Ref. LR57D11029171 or
LR57D11030741, next inspection is due based on interval value given in this ISB.
The procedure as described in this Service Bulletin is to be performed if no Airbus repair
and/or repair improvement has been previously performed in the same area. In case of
repairs performed previously, please contact AIRBUS Repair Support department for
further instructions.
(3) Advantages
Accomplishment of this ISB will permit early detection of cracks on the
 Frame 40 Vertical
Web between stringer 38 and 39 - below Intrados, left and right sides and will ensure
that the structural integrity of the area is maintained.
(4) Operational/Maintenance Consequences
The Task ALI 57-11-04 applicable to aircraft pre-modification No. 44360S13013 and
44360S13482 will be superseded by accomplishment of this Service Bulletin No.
A330-57-3114
.
D. DESCRIPTION
To accomplish this Service Bulletin it is necessary to :
Task 573114-832-801-001: Inspection
(1) Do a Special Detailed Inspection of the Fasteners Holes of the Area A at FR40, LH
side
(2) Do a Special Detailed Inspection of the Fasteners Holes of the Area A at FR40, RH
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 3
5
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SERVICE BULLETIN
side
(3) Do a Special Detailed Inspection of the Fastener Hole of the Area B at FR40, LH
side
(4) Do a Special Detailed Inspection of the Fastener Hole of the Area B at FR40, RH
side
(5) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the
Area A of the Frame 40, LH side
(6) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Holes of the
Area A of the Frame 40, RH side
(7) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the
Area A of the Frame 40, LH side
(8) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Holes of the
Area A of the Frame 40, RH side
(9) Do a Rototest Inspection of the Hole of the Area B of the frame 40, LH side
(10) Do a Rototest Inspection of the Hole of the Area B of the frame 40, RH side
Task 573114-833-801-001: Repair
(1) Install new same fasteners pre Service Bulletin No. A330-57-3083 of the Area A in
transition fit, LH side
(2) Install new same fasteners pre Service Bulletin No. A330-57-3083 of the Area A in
transition fit, RH side
(3) Install new same fasteners post Service Bulletin No. A330-57-3083 of the area A in
transition fit, LH side
(4) Install new same fasteners post Service Bulletin No. A330-57-3083 of the area A in
transition fit, RH side
(5) Install new same fastener of the Area B in transition fit, LH side
(6) Install new same fastener of the Area B in transition fit, RH side
(7) Oversize the holes to the first Oversize in comparison with the current hole diameter
of the Area A pre Service Bulletin No. A330-57-3083, LH side
(8) Oversize the holes to the first Oversize in comparison with the current hole diameter
of the Area A pre Service Bulletin No. A330-57-3083, RH side
(9) Oversize the holes to the first Oversize in comparison with the current hole diameter
of the Area A post Service Bulletin No. A330-57-3083, LH side
(10) Oversize the holes to the first Oversize in comparison with the current hole diameter
of the Area A post Service Bulletin No. A330-57-3083, RH side
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 4
5
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SERVICE BULLETIN
(11) Oversize the hole to the first Oversize in comparison with the current hole diameter
o ft h eA r e aB ,L Hs i d e
(12) Oversize the hole to the first Oversize in comparison with the current hole diameter
o ft h eA r e aB ,R Hs i d e
(13) Install new fasteners pre Service Bulletin No. A330-57-3083 of the Area A in
transition fit, LH side
(14) Install new fasteners pre Service Bulletin No. A330-57-3083 of the Area A in
transition fit, RH side
(15) Install new fasteners post Service Bulletin No. A330-57-3083 of the Area A in
transition fit, LH side
(16) Install new fasteners post Service Bulletin No. A330-57-3083 of the Area A in
transition fit, RH side
(17) Install new fastener of the Area B in transition fit, LH side
(18) Install new fastener of the Area B in transition fit, RH side
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
This Service Bulletin has been classified Mandatory by the issue of an Airworthiness
Directive (AD) published by the European Av iation Safety Agenc y (EASA). The AD must
be used as the reference document for the mandated accomplishment timescale.
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 5
5
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SERVICE BULLETIN
Table 1, Config 001 - Special Detailed Inspection of the Fasteners Holes of the Area A of the
 Frame
40, LH and RH sides
Compliance Time
Condition
 Action
Threshold
(whichever
occurs first)
Grace
period
(whichever
occurs
first)
Repetitive
Interval
ALI 57-11-04
accomplished
Do a Rototest Inspection
Pre Service Bulletin No.
A330-57-3083 on LH
and RH Sides in
accordance with
SUBTASK
573114-832-003-001 for
LH Side and SUBTASK
573114-832-008-001 for
RH Side
Refer to table 3
OR
Apply Service Bulletin
No. A330-57-3083
and
Before next flight
ALI 57-11-04 not
accomplished
Pre Service
Bulletin No.
A330-57-3083
Do a Rototest Inspection
Post Service Bulletin No.
A330-57-3083 on LH
and RH Sides in
accordance with
SUBTASK
573114-832-004-001 for
LH Side and SUBTASK
573114-832-009-001 for
RH Side
Refer to table 4
Perform this rototest at the Threshold
from Service Bulletin No.
A330-57-3083 embodiment
ALI 57-11-04
accomplished
ALI 57-11-04 not
accomplished
Post Service
Bulletin No.
A330-57-3083
Do a Rototest Inspection
Post Service Bulletin No.
A330-57-3083 on LH
and RH Sides in
accordance with
SUBTASK
573114-832-004-001 for
LH Side and SUBTASK
573114-832-009-001 for
RH Side
Refer to table 4
Perform this rototest at the Threshold
from Service Bulletin No.
A330-57-3083 embodiment
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 6
5
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SERVICE BULLETIN
Table 2, Config 001 - Special Detailed Inspection of the Fastener Hole of the Area B of the
 Frame 40,
LH and RH sides
Compliance Time
Condition
 Action
Threshold
(whichever
occurs first)
Grace period
(whichever
occurs first)
Repetitive Interval
Config. 001
 Do a Rototest Inspection
on LH and RH Sides in
accordance with
SUBTASK
573114-832-005-001 for
LH Side and SUBTASK
573114-832-010-001 for
RH Side
Refer to table 5
Table 3, Config 001 - Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fasteners
Holes of the Area A of the
 Frame 40, LH and RH sides
Compliance Time
Condition
 Action
Threshold
from first
flight
(whichever
occurs first)
Grace
period
(whichever
occurs first)
Repetitive
Interval
ALI 57-11-04
accomplished
None
 None
 FC optimized
set: 7400 FC /
24300 FH from
ALI
embodiment
or
FH optimized
set: 5950 FC /
40400 FH from
ALI
embodiment
See NOTE (*)
Pre Service
Bulletin No.
A330-57-3083
ALI 57-11-04
not
accomplished
Do a Rototest Inspection
Pre Service Bulletin No.
A330-57-3083 on LH and
RH Sides in accordance
with SUBTASK
573114-832-003-001 for
LH Side and SUBTASK
573114-832-008-001 for
RH Side
FC optimized
set: 17400
FC / 57000
FH
or
FH optimized
set: 13500
FC / 91500
FH
See NOTE (*)
2400 FC or
24 months
from
Service
Bulletin
issuance
date
None
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 7
5
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@A330
SERVICE BULLETIN
Table 3, Config 001 - Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fasteners
Holes of the Area A of the
 Frame 40, LH and RH sides
Compliance Time
Condition
 Action
Threshold
from first
flight
(whichever
occurs first)
Grace
period
(whichever
occurs first)
Repetitive
Interval
Install New same
fasteners in transition fit
Pre Service Bulletin No.
A330-57-3083 on LH
and/or RH Sides in
accordance with
SUBTASK
573114-833-001-001 for
LH Side and/or
SUBTASK
573114-833-012-001 for
RH Side
and
Before next
flight
None
 None
Repeat the Rototest
Inspection of the holes
Pre Service Bulletin No.
A330-57-3083 on LH
and/or RH Sides in
accordance with
SUBTASK
573114-832-003-001 for
LH Side and/or
SUBTASK
573114-832-008-001 for
RH Side
None
 None
 FC optimized
set: 7400 FC /
24300 FH
or
FH optimized
set: 5950 FC /
40400 FH
See NOTE (*)
No Crack found
OR
Apply Service Service
Bulletin No.
A330-57-3083
and
Before next
flight
None
 None
No Crack found
Do a Rototest Inspection
Post Service Bulletin No.
A330-57-3083 on LH and
RH Sides in accordance
with SUBTASK
573114-832-004-001 for
LH Side and SUBTASK
573114-832-009-001 for
RH Side
Refer to table 4
Perform this rototest at the Threshold from
Service Bulletin No. A330-57-3083
embodiment
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 8
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SERVICE BULLETIN
Table 3, Config 001 - Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fasteners
Holes of the Area A of the
 Frame 40, LH and RH sides
Compliance Time
Condition
 Action
Threshold
from first
flight
(whichever
occurs first)
Grace
period
(whichever
occurs first)
Repetitive
Interval
Crack found
 Oversize the holes to first
oversize in comparison
with the current hole
diameter Pre Service
Bulletin No.
A330-57-3083 on LH
and/or RH Sides in
accordance with
SUBTASK
573114-833-003-001 for
LH Side and/or
SUBTASK
573114-833-015-001 for
RH Side
and
Do a Rototest Inspection
Before next
flight
None
 None
Crack found after Rototest
Inspection
Contact Airbus
 Before next
flight
None
 None
Install new fasteners in
transition fit Pre Service
Bulletin No.
A330-57-3083 on LH
and/or RH Sides in
accordance with
SUBTASK
573114-833-005-001 for
LH Side and/or
SUBTASK
573114-833-018-001 for
RH Side
and
Before next
flight
None
 None
No Crack found after Rototest
Inspection
Repeat the Rototest
Inspection of the holes
Pre Service Bulletin No.
A330-57-3083 on LH
and/or RH Sides in
accordance with
SUBTASK
573114-832-003-001 for
LH Side and/or
SUBTASK
573114-832-008-001 for
RH Side
None
 None
 FC optimized
set: 7400 FC /
24300 FH
or
FH optimized
set: 5950 FC /
40400 FH
See NOTE (*)
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 9
5
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@A330
SERVICE BULLETIN
Table 3, Config 001 - Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fasteners
Holes of the Area A of the
 Frame 40, LH and RH sides
Compliance Time
Condition
 Action
Threshold
from first
flight
(whichever
occurs first)
Grace
period
(whichever
occurs first)
Repetitive
Interval
NOTE (*): For FH and FC optimization on A330/A340 aircraft, operators shall select the set that better
suits aircraft operation and utilization, refer to OIT 999.0086/11.
Table 4, Config 001 - Rototest Inspection Post Service Bulletin No. A330-57-3083 of the fasteners
holes of the Area A of the
 Frame 40, LH and RH Sides
Compliance Time
Condition
 Action
Threshold from
Service Bulletin
No.
A330-57-3083
embodiment
(whichever
occurs first)
Grace period
(whichever
occurs first)
Repetitive
Interval
Post Service Bulletin No.
A330-57-3083
ALI 57-11-04 accomplished or
not
Do a Rototest
Inspection Post
Service Bulletin No.
A330-57-3083 on LH
and RH Sides in
accordance with
SUBTASK
573114-832-004-001
for LH Side and
SUBTASK
573114-832-009-001
for RH Side
FC optimized
set: 30900 FC /
100900 FH
or
FH optimized
set: 23900 FC /
162000 FH
See NOTE (*)
2400 FC or
24 months
from SB
issuance
date
None
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 10
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@A330
SERVICE BULLETIN
Table 4, Config 001 - Rototest Inspection Post Service Bulletin No. A330-57-3083 of the fasteners
holes of the Area A of the
 Frame 40, LH and RH Sides
Compliance Time
Condition
 Action
Threshold from
Service Bulletin
No.
A330-57-3083
embodiment
(whichever
occurs first)
Grace period
(whichever
occurs first)
Repetitive
Interval
Install new same
fasteners in
transition fit Post
Service Bulletin No.
A330-57-3083 on LH
and/or RH Sides in
accordance with
SUBTASK
573114-833-007-001
for LH Side and/or
SUBTASK
573114-833-013-001
for RH Side
and
Before next
flight
None
 None
No crack found
Repeat the Rototest
Inspection of the
holes Post Service
Bulletin No.
A330-57-3083 on LH
and/or RH Sides in
accordance with
SUBTASK
573114-832-004-001
for LH Side and/or
SUBTASK
573114-832-009-001
for RH Side
None
 None
 FC optimized
set: 7400 FC
/ 24300 FH
or
FH optimized
set: 5950 FC
/ 40400 FH
See NOTE (*)
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 11
5
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@A330
SERVICE BULLETIN
Table 4, Config 001 - Rototest Inspection Post Service Bulletin No. A330-57-3083 of the fasteners
holes of the Area A of the
 Frame 40, LH and RH Sides
Compliance Time
Condition
 Action
Threshold from
Service Bulletin
No.
A330-57-3083
embodiment
(whichever
occurs first)
Grace period
(whichever
occurs first)
Repetitive
Interval
Crack found
 Oversize the holes
to first oversize in
comparison with the
current hole
diameter on LH
and/or RH Sides in
accordance with
SUBTASK
573114-833-011-001
for LH Side and/or
SUBTASK
573114-833-016-001
for RH Side
and
Do a Rototest
Inspection
Before next
flight
None
 None
Crack found after Rototest
Inspection
Contact Airbus
 Before next
flight
None
 None
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 12
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### Page 27

@A330
SERVICE BULLETIN
Table 4, Config 001 - Rototest Inspection Post Service Bulletin No. A330-57-3083 of the fasteners
holes of the Area A of the
 Frame 40, LH and RH Sides
Compliance Time
Condition
 Action
Threshold from
Service Bulletin
No.
A330-57-3083
embodiment
(whichever
occurs first)
Grace period
(whichever
occurs first)
Repetitive
Interval
Install new fasteners
in transition fit Post
Service Bulletin No.
A330-57-3083 on LH
and/or RH Sides in
accordance with
SUBTASK
573114-833-009-001
for LH Side and/or
SUBTASK
573114-833-019-001
for RH Side
and
Before next
flight
None
 None
No Crack found after Rototest
Inspection
Repeat the Rototest
Inspection of the
holes Post Service
Bulletin No.
A330-57-3083 on LH
and/or RH Sides in
accordance with
SUBTASK
573114-832-004-001
for LH Side and/or
SUBTASK
573114-832-009-001
for RH Side
None
 None
 FC optimized
set: 7400 FC
/ 24300 FH
or
FH optimized
set: 5950 FC
/ 40400 FH
See NOTE (*)
NOTE (*): For FH and FC optimization on A330/A340 aircraft, operators shall select the set that better
suits aircraft operation and utilization, refer to OIT 999.0086/11.
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 13
5
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### Page 28

@A330
SERVICE BULLETIN
Table 5, Config 001 - Rototest Inspection of the fastener hole of the Area B of the
 Frame 40, LH and
RH Sides
Compliance Time
Condition
 Action
Threshold from
first flight
(whichever
occurs first)
Grace period
(whichever
occurs first)
Repetitive
Interval
Config. 001
 Do a Rototest Inspection on
LH and RH Sides in
accordance with SUBTASK
573114-832-005-001 for LH
Side and SUBTASK
573114-832-010-001 for RH
Side
FC optimized set:
17400 FC /
57000 FH
or
FH optimized set:
13500 FC /
91500 FH
See NOTE (*)
2400 FC or
24 months
from SB
issuance date
None
Install new same fastener in
transition fit on LH and/or
RH Sides in accordance
with SUBTASK
573114-833-002-001 for LH
Side and/or SUBTASK
573114-833-014-001 for RH
Side
and
Before next flight
 None
 None
No Crack found
Repeat the Rototest
Inspection on LH and/or RH
Sides in accordance with
SUBTASK
573114-832-005-001 for LH
Side and/or SUBTASK
573114-832-010-001 for RH
Side
None
 None
 FC optimized
set: 7400 FC /
24300 FH
or
FH optimized
set: 5950 FC /
40400 FH
See NOTE (*)
Crack found
 Oversize the hole to first
oversize in comparison with
the current hole diameter on
LH and/or RH Sides in
accordance with SUBTASK
573114-833-010-001 for LH
Side and/or SUBTASK
573114-833-017-001 for RH
Side
and
Do a Rototest Inspection
Before next flight
 None
 None
Crack found after
Rototest Inspection
Contact Airbus
 Before next flight
 None
 None
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 14
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Table 5, Config 001 - Rototest Inspection of the fastener hole of the Area B of the
 Frame 40, LH and
RH Sides
Compliance Time
Condition
 Action
Threshold from
first flight
(whichever
occurs first)
Grace period
(whichever
occurs first)
Repetitive
Interval
Install new fastener in
transition fit on LH and/or
RH Sides in accordance
with SUBTASK
573114-833-006-001 for LH
Side and/or SUBTASK
573114-833-020-001 for RH
Side
and
Before next flight
 None
 None
No Crack found
after Rototest
Inspection
Repeat the Rototest
Inspection of the holes on
LH and/or RH Sides in
accordance with SUBTASK
573114-832-005-001 for LH
Side and/or SUBTASK
573114-832-010-001 for RH
Side
None
 None
 FC optimized
set: 7400 FC /
24300 FH
or
FH optimized
set: 5950 FC /
40400 FH
See NOTE (*)
NOTE (*): For FH and FC optimization on A330/A340 aircraft, operators shall select the set that better
suits aircraft operation and utilization, refer to OIT 999.0086/11.
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.
Task 573114-832-801-001: Inspection
Get Access
 20.00
On Aircraft
Do a Special Detailed Inspection of the Fasteners
Holes of the Area A at FR40, LH side
0.25
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 15
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Task 573114-832-801-001: Inspection
Do a Special Detailed Inspection of the Fasteners
Holes of the Area A at FR40, RH side
0.25
Do a Special Detailed Inspection of the Fastener Hole
of the Area B at FR40, LH side
0.25
Do a Special Detailed Inspection of the Fastener Hole
of the Area B at FR40, RH side
0.25
Do a Rototest Inspection Pre Service Bulletin No.
A330-57-3083 of the Holes of the Area A of the Frame
40, LH side
2.25
Do a Rototest Inspection Pre Service Bulletin No.
A330-57-3083 of the Holes of the Area A of the Frame
40, RH side
2.25
Do a Rototest Inspection Post Service Bulletin No.
A330-57-3083 of the Holes of the Area A of the Frame
40, LH side
2.25
Do a Rototest Inspection Post Service Bulletin No.
A330-57-3083 of the Holes of the Area A of the Frame
40, RH side
2.25
Do a Rototest Inspection of the Hole of the Area B of
the frame 40, LH side
0.25
Do a Rototest Inspection of the Hole of the Area B of
the frame 40, RH side
0.25
Close-Up
 20.75
TOTAL MANHOURS
 51.25
ELAPSED TIME (HOURS)
 51.25
Task 573114-833-801-001: Repair
Get Access
 20.00
On Aircraft
Install new same fasteners pre Service Bulletin No.
A330-57-3083 of the Area A in transition fit, LH side
1.75
Install new same fasteners pre Service Bulletin No.
A330-57-3083 of the Area A in transition fit, RH side
1.75
Install new same fasteners post Service Bulletin No.
A330-57-3083 of the area A in transition fit, LH side
1.75
Install new same fasteners post Service Bulletin No.
A330-57-3083 of the area A in transition fit, RH side
1.75
Install new same fastener of the Area B in transition fit,
LH side
0.25
Install new same fastener of the Area B in transition fit,
RH side
0.25
Oversize the holes to the first Oversize in comparison
with the current hole diameter of the Area A pre
Service Bulletin No. A330-57-3083, LH side
1.75
Oversize the holes to the first Oversize in comparison
with the current hole diameter of the Area A pre
Service Bulletin No. A330-57-3083, RH side
1.75
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 16
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Task 573114-833-801-001: Repair
Oversize the holes to the first Oversize in comparison
with the current hole diameter of the Area A post
Service Bulletin No. A330-57-3083, LH side
1.75
Oversize the holes to the first Oversize in comparison
with the current hole diameter of the Area A post
Service Bulletin No. A330-57-3083, RH side
1.75
Oversize the hole to the first Oversize in comparison
with the current hole diameter of the Area B, LH side
0.25
Oversize the hole to the first Oversize in comparison
with the current hole diameter of the Area B, RH side
0.25
Install new fasteners pre Service Bulletin No.
A330-57-3083 of the Area A in transition fit, LH side
1.75
Install new fasteners pre Service Bulletin No.
A330-57-3083 of the Area A in transition fit, RH side
1.75
Install new fasteners post Service Bulletin No.
A330-57-3083 of the Area A in transition fit, LH side
1.75
Install new fasteners post Service Bulletin No.
A330-57-3083 of the Area A in transition fit, RH side
1.75
Install new fastener of the Area B in transition fit, LH
side
0.25
Install new fastener of the Area B in transition fit, RH
side
0.25
Close-Up
 20.75
TOTAL MANHOURS
 63.25
ELAPSED TIME (HOURS)
 63.25
NOTE
: For Area A, if SB No.A330-57-3083 is accomplished, only the manhours
stating post SB No.A330-57-3083 apply.
For Area A, if SB No.A330-57-3083 is not accomplished, only the manhours
stating pre SB No.A330-57-3083 apply.
NOTE
: The minimum manhours necessary to accomplish this Service Bulletin are
those for the Inspection. Depending on the inspection result, additional
manhours can apply.
H. WEIGHT AND BALANCE
Not Changed
I. ELECTRICAL LOAD DATA
Not Changed
J. REFERENCES
LR57D11029171
Airworthiness Limitation Item (ALI)
 ALI 57-11-04
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 17
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Aircraft Maintenance Manual (AMM)
 06-20-00
 06-31-53 06-41-53
12-34-24 20-21-11 21-20-00
21-52-41 25-52-00 25-80-00
36-22-19 52-30-00 53-35-13
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
Non Destructive Test Manual (NTM)
 51-10-01
Repair Instruction
 Repair Instruction R57115092
Service Bulletin (SB)
 A330-57-3083
A330-57-3114
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-11-00 51-22-00 51-24-00
51-40-00
 51-42-00 51-43-00
51-44-00 51-75-12
K. PUBLICATION AFFECTED
Airworthiness Limitation Section (ALS)
 Airworthiness Limitation Section
(ALS) PART 2
Maintenance Planning Document (MPD)
 571104-01-6
L. INTERCHANGEABILITY/MIXABILITY
Not Applicable
M. SPARES
None
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 18
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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
 573114A01R05
Kit
 573114A02R00
Kit
 573114A03R00
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
(2) Price and Availability
Kit
 573114A01R05
Cost
 5,020.00
 USD
Availability
 180 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
AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.
Kit
 573114A02R00
Cost
 3,740.00
 USD
Availability
 180 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
AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.
Kit
 573114A03R00
Cost
 3,020.00
 USD
Availability
 180 calendar days from receipt of order
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 19
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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
AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.
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 organisation of this retrofit, you are kindly requested to contact AIRBUS retrofit
management department.
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
France
E-mail: monitored.retrofit@airbus.com
This Service Bulletin is subject in case of findings to a specific support provided by AIRBUS.
For more details regarding the applicable commercial policy, please contact your Customer
Support Director.
C. LIST OF COMPONENTS
Kit 573114A01R05
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
1
 EN6115V5-12
 1
 SCREW
2
 ASNA2529-5
 1
 NUT
5
 EN6115V4-6
 4
 SCREW
6
 EN6115V4-10
 2
 SCREW
7
 ASNA2529-4
 6
 NUT
10
 EN6115V5X12
 1
 SCREW
12
 EN6115V4X6
 4
 SCREW
13
 EN6115V4X10
 2
 SCREW
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
: Kit 573114A01 is used only for the Area A pre Service Bulletin No.
A330-57-3083.
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 20
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Kit 573114A02R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
2
 ASNA2529-5
 6
 NUT
16
 EN6115V6-12
 1
 SCREW
17
 ASNA2529-6
 1
 NUT
18
 EN6115V5-6
 4
 SCREW
19
 EN6115V5-10
 2
 SCREW
21
 EN6115V6X12
 1
 BOLT
22
 EN6115V5X6
 4
 SCREW
23
 EN6115V5X10
 2
 SCREW
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
: Kit 573114A02 is used only for the Area A post Service Bulletin No.
A330-57-3083.
Kit 573114A03R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
3
 EN6115T7-18
 1
 SCREW
4
 ASNA2531-7
 1
 NUT
11
 EN6115T7X18
 1
 SCREW
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
: Kit 573114A03 is used only for the Area B.
D. LIST OF MATERIALS - OPERATOR SUPPLIED
(1) Consumable Materials
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
Primer Polyurethane Paint -
Corrosion Inhibiting
04EAC2
 As required
Top Coat Polyurethane - Grey
Internal Structure
04JME4
 As required
Polysulfide Sealant-General
Purpose Brushable
06AAA1
 As required
Polysulfide Sealant-Fuel
Contaminated Area Brusha
06ADA1
 As required
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 21
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ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
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
(2) Components
NOTE
: To accomplish this Service Bulletin it is necessary to use the expendable
parts listed in the subsequent referenced task:
- AMM Task 21-52-41-400-801
(3) Equipment
None
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
F. TOOLING
(1) Tooling - Price and Availability
None
(2) Tools
NOTE
: To accomplish this Service Bulletin it is necessary to use the tools listed
in the subsequent re ferenced tasks:
- AMM Task 21-52-41-000-801
- AMM Task 21-52-41-400-801
(3) Special Tools
None
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
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3. ACCOMPLISHMENT INSTRUCTIONS
Task 573114-832-801-001 - Inspection
WARNING
: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
WARNING
: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE
IN POSITION BEFORE YOU START A TASK ON OR NEAR:
- THE FLIGHT CONTROLS
- THE FLIGHT CONTROL SURFACES
- THE LANDING GEAR AND THE RELATED DOORS
- COMPONENTS THAT MOVE.
MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS.
WARNING
: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY
INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED
MOVEMENT OF THE LANDING GEAR.
CAUTION
: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP
ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY
AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE
WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,
COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO
THIS:
- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC. AS
NECESSARY ON WIRING AND COMPONENTS.
- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND
OTHER CONTAMINATION.
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION
AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.
IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.
CAUTION
: TO ACCOMPLISH THIS SERVICE BULLETIN IT IS NOT NECESSARY
TO PUT THE AIRCRAFT UNDER ZERO STRESS JACKING. NO ZERO
STRESS JACKING IS REQUIRED ALSO IN CASE OF CONCURRENT
ACCOMPLISHMENT OF MAINTENANCE TASKS OR SBS IN FRAME 40 AREA.
HOWEVER THIS IS APPLICABLE ONLY FOR THE ACCOMPLISHMENT OF
THESE TASKS/SBS WITH OUT DEVIATION. INDEED, IN CASE OF HEAVY
REPAIR, A TEMPORARY RE-INSTALLATION OF FASTENERS AND/OR ZERO
STRESS JACKING PROCEDURE COULD BE ANTICIPATED.
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
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
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’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 is classified mandatory or expected to be classified mandatory
by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these
accomplishment instructions are Required for Compliance (RC) and must be done
to comply with the AD. Other paragraphs are recommended and may be deviated
from, done as part of other actions or done with accepted methods different from
those given in the Service Bulletin, as long as the RC paragraphs can be done and
the aircraft can be put back into a serviceable condition.
NOTE
: 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
: The purpose of flowcharts is to supplement the information given in the Procedure
and Compliance paragraphs and not to serve as the primary source for tasks or
compliance times given in this Service Bulletin.
Task Associated Data
Zone
137 138
Manpower
TOTAL MANHOURS
 51.25
ELAPSED TIME (HOURS)
 51.25
A. GENERAL
(1) Subtask 573114-910-001-001 - 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
Consumable Material List (CML)
Structural Repair Manual (SRM)
 51-42-00
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
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(a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.
(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.
(c) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001.
(d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to
Consumable Material List (CML).
(e) Remove and install fasteners in accordance with SRM 51-42-00.
(f) Use a non-metallic spatula to remove the sealant.
(g) Tag all the parts you must remove and retain to make the subsequent installation
easier.
(h) Put all the retained hardware in identified plastic bags and attach the bags to the
related unit.
(2) Subtask 573114-839-001-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
B. PREPARATION
(1) Subtask 573114-941-001-001 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 12-34-24-860-802
NOTE
: The items given in this note shall be considered as the basic Aircraft
configuration before you start a maintenance task:
- Aircraft on the ground resting on landing gear (the ground safety
locks and the wheel chocks are in position on the landing gear)
- Engine shut down, thrust reversers closed and locked
- Aircraft in clean configuration
- Parking brake applied
- Aircraft electrical network de-energized
- Hydraulic system s depressurized
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 25
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- Access to the cockpit and cabin is available
- All circuit breakers are in closed position
- All controls in NORM, AUTO or OFF position.
(a) Make sure that the aircraft is electrically grounded , refer to AMM Task
12-34-24-860-802.
(b) Put the access platform(s) in position at door 821.
(2) Subtask 573114-941-002-001 - Safety Precautions
Manpower Resources
Skills
 NON SPECIFIC
(a) On the AIR control panel 225VU:
1
 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2)
pushbutton switches are released.
2
 Put a WARNING NOTICE in position to tell persons not to operate these
pushbotton switches.
(b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons
not to supply the ground air source.
(3) Subtask 573114-010-001-001 - Remove/Open for Access in the Belly Fairing Area
RH side
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 21-20-00-010-801
Task 21-52-41-000-801
Task 36-22-19-000-801
Task 53-35-13-000-802
Fig. A-FBAAA
Removal/Installation of the Heat Shield
Sheet 01
Sheet 02
Fig. A-FDBAA
Removal/Installation of the Air
Conditioning Ducts between FR39.1 and
FR40 (Belly Fairing Area)
Sheet 01
Fig. A-FDCAA
Removal/Installation of the Air
Conditioning Ducts between FR39.1 and
FR40 (Belly Fairing Area)
Sheet 01
(a) Remove the Belly Fairing Access-Panels 193DB, refer to
 AMM Task
53-35-13-000-802.
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(b) If necessary, on the RH side, remove and retain the air-conditioning pack outlet
duct:
Refer to Fig. A-FDBAA Sheet 01
Refer to AMM Task 21-20-00-010-801
1 Duct Item (26) Retain
(c) On the RH side, remove and retain the air ventilation duct:
Refer to Fig. A-FDCAA Sheet 01
Refer to AMM Task 21-20-00-010-801
1 Duct Item (41) Retain
(d) If necessary, remove the Wing Bleed-Air Duct Sensing Elements
 120HF,
 131HF,
135HF,
 124HF,
 133HF and
 122HF, refer to
 AMM Task 36-22-19-000-801.
(e) Remove the Air Conditioning Pack
 522HH, refer to AMM Task 21-52-41-000-801.
(f) Remove the Heat Shield of the RH Conditioning Pack:
Refer to
 Fig. A-FBAAA Sheet 01
 and Fig. A-FBAAA Sheet 02
1 Heat Shield Item (8) Retain
12 Screw Item (9) Retain
(4) Subtask 573114-010-002-001 - Remove/Open for Access in the Belly Fairing Area
LH side
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 53-35-13-000-802
(a) Remove the Belly Fairing Access-Panels 192PB, refer to
 AMM Task
53-35-13-000-802.
(5) Subtask 573114-941-006-001 - Remove/Open for Access in the FWD Cargo-
Compartment
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 21-20-00-010-801
Task 25-52-00-000-801
Task 25-80-00-000-801
Task 52-30-00-010-801
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 27
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References
Fig. A-FDAAA
Removal/Installation of the Air
Conditioning Ducts between FR39.1 and
FR40 (FWD Cargo-Compartment)
Sheet 01
CAUTION
: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.
(a) Open the FWD cargo-compartment door 821, refer to
 AMM Task
52-30-00-010-801.
(b) Remove the Ceiling Panels, the Partition Panels and the Sidewall Panels in the
Forward Cargo Compartment
 131CX, 131DX, 132CX and 132DX, refer to
 AMM
Task 25-52-00-000-801.
(c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1
and Frame 40:
Refer to Fig. A-FDAAA Sheet 01
Refer to AMM Task 21-20-00-010-801
2 Duct Item (11) Retain
2 Duct Item (12) Retain
2 Recirculation filter-
housing
Item (13) Retain
2 Recirculation fan Item (14) Retain
(d) Move Insulation Blankets as necessary, refer to
 AMM Task 25-80-00-000-801.
(6) Subtask 573114-110-001-001 - Cleaning of the structure
Manpower Resources
Skills
 NON SPECIFIC
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
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 28
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SERVICE BULLETIN
WARNING
: USE SOLVENTS/CLEANING AG ENTS, SEALANTS AND OTHER
SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH
T H EW O R KA R E A .
THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN
IRRITANTS.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.
WARNING
: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE
THIS/THESE MATERIAL/S.
USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A
MASK.
(a) Clean the inspection area with:
Non Aqueous
Cleaner-General
08BAA9
 As required
and (if necessary)
Textile-Lint Free
Cotton
14SBA1
 As required
(7) Subtask 573114-210-001-001 - Preparation of the inspection Area
Manpower Resources
Skills
 NON SPECIFIC
References
Structural Repair Manual (SRM)
 51-11-00
51-22-00
(a) Use a FLASHLIGHT to do this inspection if necessary.
(b) Make sure that the surface of the inspection area is clean and smooth.
(c) Do a visual check of the inspection area for damages or discontinuities.
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 29
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SERVICE BULLETIN
(d) Make sure that there is no:
1
 Corrosion damage:
- If you find corrosion damage, refer to the Structural Repair Manual for
Types, inspection, removal and corrosion protection in accordance with
SRM 51-22-00.
2
 Other damage (cracks, scratches, str ess, marks, dents, bumps, ...):
- If you find this type of damage, refer to the Structural Repair Manual
for damage classification and corrective action in accordance with
 SRM
51-11-00.
C. PROCEDURE
(1) Subtask 573114-832-001-001 - Do a Special Detailed Inspection of the Fasteners
Holes of the Area A at FR40, LH side
Work Zones and Access Panels
Zone
 Access/Work location
137
 Work location
 Frame 40
Manpower Resources
Manhours
 0.25
Minimum number of person
 1
Subtask elapsed time
 0.25
Skills
 NON DESTRUCTIVE
TESTING
AIRFRAME
References
Service Bulletin (SB)
 A330-57-3083
Fig. A-FFAAA
Flow Chart
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Refer to Fig. A-FFAAA
(a) If Service Bulletin No.A330-57-3083 is accomplished:
1
 Do SUBTASK 573114-832-004 001 Do a Rototest Inspection Post Service
Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40,
LH side at the threshold given in the table 4 of the Planning Information
Paragraph E.(2).
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 30
5
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SERVICE BULLETIN
(b) If Service Bulletin No. A330-57-3083 is not accomplished:
1
 Do SUBTASK 573114-832-003 001 Do a Rototest Inspection Pre Service
Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40,
LH side at the threshold given in the table 3 of the Planning Information
Paragraph E.(2).
or
Apply Service Bulletin No. A330-57-3083 before next flight.
And do the SUBTASK 573114-832-004 001 Do a Rototest Inspection Post
Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame
40, LH side at the threshold given in the table 4 of the Planning Information
Paragraph E.(2).
(2) Subtask 573114-832-006-001 - Do a Special Detailed Inspection of the Fasteners
Holes of the Area A at FR40, RH side
Work Zones and Access Panels
Zone
 Access/Work location
138
 Work location
 Frame 40
Manpower Resources
Manhours
 0.25
Minimum number of person
 1
Subtask elapsed time
 0.25
Skills
 NON DESTRUCTIVE
TESTING
AIRFRAME
References
Service Bulletin (SB)
 A330-57-3083
Fig. A-FFAAA
Flow Chart
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Refer to Fig. A-FFAAA
(a) If Service Bulletin No.A330-57-3083 is accomplished:
1
 Do SUBTASK 573114-832-009 001 Do a Rototest Inspection Post Service
Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40,
RH side at the threshold given in the table 4 of the Planning Information
Paragraph E.(2).
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 31
5
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SERVICE BULLETIN
(b) If Service Bulletin No. A330-57-3083 is not accomplished:
1
 Do SUBTASK 573114-832-008 001 Do a Rototest Inspection Pre Service
Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame 40,
RH side at the threshold given in the table 3 of the Planning Information
Paragraph E.(2).
or
Apply Service Bulletin No. A330-57-3083 before next flight.
And do the SUBTASK 573114-832-009 001 Do a Rototest Inspection Post
Service Bulletin No. A330-57-3083 of the Holes of the Area A of the Frame
40, RH side at the threshold given in the table 4 of the Planning Information
Paragraph E.(2).
(3) Subtask 573114-832-002-001 - Do a Special Detailed Inspection of the Fastener
Hole of the Area B at FR40, LH side
Work Zones and Access Panels
Zone
 Access/Work location
137
 Work location
 Frame 40
Manpower Resources
Manhours
 0.25
Minimum number of person
 1
Subtask elapsed time
 0.25
Skills
 NON SPECIFIC
References
Fig. A-FFAAA
Flow Chart
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Refer to Fig. A-FFAAA
(a) Do SUBTASK 573114-832-005 001 Do a Rototest Inspection of the Hole of the
Area B of the frame 40, LH side at the threshold given in the table 5 of the
Planning Information Paragraph E.(2).
(4) Subtask 573114-832-007-001 - Do a Special Detailed Inspection of the Fastener
Hole of the Area B at FR40, RH side
Work Zones and Access Panels
Zone
 Access/Work location
138
 Work location
 Frame 40
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 32
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SERVICE BULLETIN
Manpower Resources
Manhours
 0.25
Minimum number of person
 1
Subtask elapsed time
 0.25
Skills
 NON SPECIFIC
References
Fig. A-FFAAA
Flow Chart
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Refer to Fig. A-FFAAA
(a) Do SUBTASK 573114-832-010 001 Do a Rototest Inspection of the Hole of the
Area B of the frame 40, RH side at the threshold given in the table 5 of the
Planning Information Paragraph E.(2).
(5) Subtask 573114-832-003-001 - Do a Rototest Inspection Pre Service Bulletin No.
A330-57-3083 of the Holes of the Area A of the Frame 40, LH side
Work Zones and Access Panels
Zone
 Access/Work location
137
 Work location
 Frame 40
Manpower Resources
Manhours
 2.25
Minimum number of person
 1
Subtask elapsed time
 2.25
Skills
 NON SPECIFIC
References
Airworthiness Limitation Item (ALI)
 Airworthiness Limitation Items (ALI)
57-11-04
Non Destructive Test Manual (NTM)
 51-10-01
Service Bulletin (SB)
 A330-57-3083
Fig. A-FCBAA
Inspection Area
Sheet
 01
Sheet
 02
Sheet
 03
Fig. A-FCCAA
Removal/Installation of the fasteners pre
Service Bulletin No. A330-57-3083 of the
Area A
Sheet
 01
Sheet
 02
Sheet
 03
Sheet
 04
At the Threshold/Interval given in the Planning Information Paragraph E.(2):
NOTE
: If ALI 57-11-04 is accomplished, the Interval is to be applied.
If ALI 57-11-04 is not accomplished, the Threshold is to be applied.
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 33
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SERVICE BULLETIN
(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the area A of the
Frame 40, LH side.
- Remove the fasteners from holes H41, H42, H44, and H46, LH side:
Refer to Fig. A-FCCAA
4 Screw Item (5) Discard
4 Nut Item (7) Discard
- Remove the fasteners from holes H45 and H259, LH side:
Refer to Fig. A-FCCAA
2 Screw Item (6) Discard
2 Nut Item (7) Discard
- Remove the fastener from hole H25, LH side:
Refer to Fig. A-FCCAA
1 Screw Item (1) Discard
1 Nut Item (2) Discard
- Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and
H259, LH side.
Refer to Fig. A-FCBAA
Refer to NTM 51-10-01
1
 If no crack is found:
a
 Do SUBTASK 573114-833-001 001 Install new same fasteners pre
Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH side
before next flight
and
Repeat the rototest inspection as described in SUBTASK
573114-832-003 001 Do a Rototest Inspection Pre Service Bulletin No.
A330-57-3083 of the Holes of the Area A of the Frame 40, LH side at the
interval given in the table 3 of the Planning Information Paragraph E.(2).
or
b
 Apply Service Bulletin No. A330-57-3083 before next flight.
And do the SUBTASK 573114-832-004 001 Do a Rototest Inspection
Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the
Frame 40, LH side at the threshold given in the table 4 of the Planning
Information Paragraph E.(2).
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 34
5
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SERVICE BULLETIN
2
 If crack is found:
a
 Do SUBTASK 573114-833-003 001 Oversize the holes to the first
Oversize in comparison with the current hole diameter of the Area A pre
Service Bulletin No. A330-57-3083, LH side and check if crack is found
with a rototest inspection before next flight.
<1> If crack is found after the rototest inspection:
<a> Contact Airbus before next flight.
<2> If no crack is found after the rototest inspection:
<a> Do SUBTASK 573114-833-005 001 Install new fasteners pre
Service Bulletin No. A330-57-3083 of the Area A in transition
fit, LH side before next flight
and
Repeat the rototest inspection as described in SUBTASK
573114-832-003 001 Do a Rototest Inspection Pre Service
Bulletin No. A330-57-3083 of the Holes of the Area A of the
Frame 40, LH side at the interval given in the table 3 of the
Planning Information Paragraph E.(2).
(b) Upload the inspection report in AirbusWorld, refer to Appendix 01 - Inspection
Report
 .
NOTE
: Complete the inspection report sheets with detailed damage report
and pictures.
(6) Subtask 573114-832-008-001 - Do a Rototest Inspection Pre Service Bulletin No.
A330-57-3083 of the Holes of the Area A of the Frame 40, RH side
Work Zones and Access Panels
Zone
 Access/Work location
138
 Work location
 Frame 40
Manpower Resources
Manhours
 2.25
Minimum number of person
 1
Subtask elapsed time
 2.25
Skills
 NON SPECIFIC
References
Airworthiness Limitation Item (ALI)
 Airworthiness Limitation Items (ALI)
57-11-04
Non Destructive Test Manual (NTM)
 51-10-01
Service Bulletin (SB)
 A330-57-3083
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 35
5
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SERVICE BULLETIN
References
Fig. A-FCBAA
Inspection Area
Sheet
 01
Sheet
 02
Sheet
 03
Fig. A-FCCAA
Removal/Installation of the fasteners pre
Service Bulletin No. A330-57-3083 of the
Area A
Sheet
 01
Sheet
 02
Sheet
 03
Sheet
 04
At the Threshold/Interval given in the Planning Information Paragraph E.(2):
NOTE
: If ALI 57-11-04 is accomplished, the Interval is to be applied.
If ALI 57-11-04 is not accomplished, the Threshold is to be applied.
(a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the area A of the
Frame 40, RH side.
- Remove the fasteners from holes H41, H42, H44, and H46, RH side:
Refer to Fig. A-FCCAA
4 Screw Item (5) Discard
4 Nut Item (7) Discard
- Remove the fasteners from holes H45 and H259, RH side:
Refer to Fig. A-FCCAA
2 Screw Item (6) Discard
2 Nut Item (7) Discard
- Remove the fastener from hole H25, RH side:
Refer to Fig. A-FCCAA
1 Screw Item (1) Discard
1 Nut Item (2) Discard
- Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and
H259, RH side.
Refer to Fig. A-FCBAA
Refer to NTM 51-10-01
1
 If no crack is found:
a
 Do SUBTASK 573114-833-012 001 Install new same fasteners pre
Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH side
before next flight
and
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 36
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SERVICE BULLETIN
Repeat the rototest inspection as described in SUBTASK
573114-832-008 001 Do a Rototest Inspection Pre Service Bulletin No.
A330-57-3083 of the Holes of the Area A of the Frame 40, RH side at the
interval given in the table 3 of the Planning Information Paragraph E.(2).
or
b
 Apply Service Bulletin No. A330-57-3083 before next flight.
And do the SUBTASK 573114-832-009 001 Do a Rototest Inspection
Post Service Bulletin No. A330-57-3083 of the Holes of the Area A of the
Frame 40, RH side at the threshold given in the table 4 of the Planning
Information Paragraph E.(2).
2
 If crack is found:
a
 Do SUBTASK 573114-833-015 001 Oversize the holes to the first
Oversize in comparison with the current hole diameter of the Area A pre
Service Bulletin No. A330-57-3083, RH side and check if crack is found
with a rototest inspection before next flight.
<1> If crack is found after the rototest inspection:
<a> Contact Airbus before next flight.
<2> If no crack is found after the rototest inspection:
<a> Do SUBTASK 573114-833-018 001 Install new fasteners pre
Service Bulletin No. A330-57-3083 of the Area A in transition
fit, RH side before next flight
and
Repeat the rototest inspection as described in SUBTASK
573114-832-008 001 Do a Rototest Inspection Pre Service
Bulletin No. A330-57-3083 of the Holes of the Area A of the
Frame 40, RH side at the interval given in the table 3 of the
Planning Information Paragraph E.(2).
(b) Upload the inspection report in AirbusWorld, refer to Appendix 01 - Inspection
Report
 .
NOTE
: Complete the inspection report sheets with detailed damage report
and pictures.
(7) Subtask 573114-832-004-001 - Do a Rototest Inspection Post Service Bulletin No.
A330-57-3083 of the Holes of the Area A of the Frame 40, LH side
Work Zones and Access Panels
Zone
 Access/Work location
137
 Work location
 Frame 40
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 37
5
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SERVICE BULLETIN
Manpower Resources
Manhours
 2.25
Minimum number of person
 1
Subtask elapsed time
 2.25
Skills
 NON SPECIFIC
References
Airworthiness Limitation Item (ALI)
 Airworthiness Limitation Items (ALI)
57-11-04
Non Destructive Test Manual (NTM)
 51-10-01
Service Bulletin (SB)
 A330-57-3083
Fig. A-FCBAA
Inspection Area
Sheet 01
Sheet 02
Sheet 03
Fig. A-FCAAA
Removal/Installation of the fasteners
post Service Bulletin No. A330-57-3083
o ft h eA r e aA
Sheet
 01
Sheet
 02
Sheet
 03
Sheet
 04
At the threshold given in the Planning Information Paragraph E.(2):
NOTE
: As Service Bulletin No. A330-57-3083 is applied even if ALI 57-11-04 is
accomplished or not, the Threshold is to be applied.
(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the area A of
the
 Frame 40, LH side.
- In the area A, remove the fasteners from holes H41, H42, H44, and H46, LH
side:
Refer to Fig. A-FCAAA
4 Bolt Item (18) Discard
4 Nut Item (2) Discard
- In the area A, remove the fasteners from holes H45 and H259, LH side:
Refer to Fig. A-FCAAA
2 Bolt Item (19) Discard
2 Nut Item (2) Discard
- In the area A, remove the fastener from hole H25, LH side:
Refer to Fig. A-FCAAA
1 Bolt Item (16) Discard
1 Nut Item (17) Discard
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 38
5
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SERVICE BULLETIN
- Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and
H259, LH side.
Refer to Fig. A-FCBAA
Refer to NTM 51-10-01
1
 If no crack is found:
a
 Do SUBTASK 573114-833-007 001 Install new same fasteners post
Service Bulletin No. A330-57-3083 of the area A in transition fit, LH side
before next flight
and
Repeat the rototest inspection as described in SUBTASK
573114-832-004 001 Do a Rototest Inspection Post Service Bulletin No.
A330-57-3083 of the Holes of the Area A of the Frame 40, LH side at the
interval given in the table 4 of the Planning Information Paragraph E.(2).
2
 If crack is found:
a
 Do SUBTASK 573114-833-011 001 Oversize the holes to the first
Oversize in comparison with the current hole diameter of the Area A post
Service Bulletin No. A330-57-3083, LH side and check if crack is found
with a rototest inspection before next flight.
<1> If crack is found after the rototest inspection:
<a> Contact Airbus before next flight.
<2> If no crack is found after the rototest inspection:
<a> Do SUBTASK 573114-833-009 001 Install new fasteners post
Service Bulletin No. A330-57-3083 of the Area A in transition
fit, LH side before next flight
and
Repeat the rototest inspection as described in SUBTASK
573114-832-004 001 Do a Rototest Inspection Post Service
Bulletin No. A330-57-3083 of the Holes of the Area A of the
Frame 40, LH side at the interval given in the table 4 of the
Planning Information Paragraph E.(2).
(b) Upload the inspection report in AirbusWorld, refer to Appendix 01 - Inspection
Report
 .
NOTE
: Complete the inspection report sheets with detailed damage report
and pictures.
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 39
5
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SERVICE BULLETIN
(8) Subtask 573114-832-009-001 - Do a Rototest Inspection Post Service Bulletin No.
A330-57-3083 of the Holes of the Area A of the Frame 40, RH side
Work Zones and Access Panels
Zone
 Access/Work location
138
 Work location
 Frame 40
Manpower Resources
Manhours
 2.25
Minimum number of person
 1
Subtask elapsed time
 2.25
Skills
 NON SPECIFIC
References
Airworthiness Limitation Item (ALI)
 Airworthiness Limitation Items (ALI)
57-11-04
Non Destructive Test Manual (NTM)
 51-10-01
Service Bulletin (SB)
 A330-57-3083
Fig. A-FCBAA
Inspection Area
Sheet 01
Sheet 02
Sheet 03
Fig. A-FCAAA
Removal/Installation of the fasteners
post Service Bulletin No. A330-57-3083
o ft h eA r e aA
Sheet
 01
Sheet
 02
Sheet
 03
Sheet
 04
At the threshold given in the Planning Information Paragraph E.(2):
NOTE
: As Service Bulletin No. A330-57-3083 is applied even if ALI 57-11-04 is
accomplished or not, the Threshold is to be applied.
(a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the area A of
the
 Frame 40, RH side.
- In the area A, remove the fasteners from holes H41, H42, H44, and H46, RH
side:
Refer to Fig. A-FCAAA
4 Bolt Item (18) Discard
4 Nut Item (2) Discard
- In the area A, remove the fasteners from holes H45 and H259, RH side:
Refer to Fig. A-FCAAA
2 Bolt Item (19) Discard
2 Nut Item (2) Discard
- In the area A, remove the fastener from hole H25, RH side:
Refer to Fig. A-FCAAA
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 40
5
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SERVICE BULLETIN
1 Bolt Item (16) Discard
1 Nut Item (17) Discard
- Do a rototest inspection at the holes H25, H41, H42, H44, H45, H46, and
H259, RH side.
Refer to Fig. A-FCBAA
Refer to NTM 51-10-01
1
 If no crack is found:
a
 Do SUBTASK 573114-833-013 001 Install new same fasteners post
Service Bulletin No. A330-57-3083 of the area A in transition fit, RH side
before next flight
and
Repeat the rototest inspection as described in SUBTASK
573114-832-009 001 Do a Rototest Inspection Post Service Bulletin No.
A330-57-3083 of the Holes of the Area A of the Frame 40, RH side at the
interval given in the table 4 of the Planning Information Paragraph E.(2).
2
 If crack is found:
a
 Do SUBTASK 573114-833-016 001 Oversize the holes to the first
Oversize in comparison with the current hole diameter of the Area A post
Service Bulletin No. A330-57-3083, RH side and check if crack is found
with a rototest inspection before next flight.
<1> If crack is found after the rototest inspection:
<a> Contact Airbus before next flight.
<2> If no crack is found after the rototest inspection:
<a> Do SUBTASK 573114-833-019 001 Install new fasteners post
Service Bulletin No. A330-57-3083 of the Area A in transition
fit, RH side before next flight
and
Repeat the rototest inspection as described in SUBTASK
573114-832-009 001 Do a Rototest Inspection Post Service
Bulletin No. A330-57-3083 of the Holes of the Area A of the
Frame 40, RH side at the interval given in the table 4 of the
Planning Information Paragraph E.(2).
(b) Upload the inspection report in AirbusWorld, refer to Appendix 01 - Inspection
Report
 .
NOTE
: Complete the inspection report sheets with detailed damage report
and pictures.
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 41
5
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SERVICE BULLETIN
(9) Subtask 573114-832-005-001 - Do a Rototest Inspection of the Hole of the Area B
of the frame 40, LH side
Work Zones and Access Panels
Zone
 Access/Work location
137
 Work location
 Frame 40
Manpower Resources
Manhours
 0.25
Minimum number of person
 1
Subtask elapsed time
 0.25
Skills
 NON SPECIFIC
References
Non Destructive Test Manual (NTM)
 51-10-01
Fig. A-FCBAA
Inspection Area
Sheet
 01
Sheet
 02
Sheet
 03
Fig. A-FEAAA
Removal/Installation of the fasteners of
the Area B
Sheet
 01
Sheet
 02
Sheet
 03
Sheet
 04
Refer to Fig. A-FEAAA
At the threshold given in the Planning Information Paragraph E.(2):
(a) Do a rototest inspection of the area B of the
 Frame 40, LH side.
- Remove fastener from hole H39, LH side, refer to Fig. A-FEAAA Sheet 02
 :
1 Bolt Item (3) Discard
1 Nut Item (4) Discard
- Do a rototest inspection at hole H39, LH side.
Refer to Fig. A-FCBAA
Refer to NTM 51-10-01
1
 If no crack is found:
a
 Do SUBTASK 573114-833-002 001 Install new same fastener of the Area
B in transition fit, LH side before next flight
and
Repeat the rototest inspection as described in SUBTASK
573114-832-005 001 Do a Rototest Inspection of the Hole of the Area B
of the frame 40, LH side at the interval given in the table 5 of the
Planning Information Paragraph E.(2).
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 42
5
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SERVICE BULLETIN
2
 If crack is found:
a
 Do SUBTASK 573114-833-010 001 Oversize the hole to the first
Oversize in comparison with the current hole diameter of the Area B, LH
side and check if crack is found with a rototest inspection before next
flight.
<1> If crack is found after the rototest inspection:
<a> Contact Airbus before next flight.
<2> If no crack is found after the rototest inspection:
<a> Do SUBTASK 573114-833-006 001 Install new fastener of the
Area B in transition fit, LH side before next flight
and
Repeat the rototest inspection as described in SUBTASK
573114-832-005 001 Do a Rototest Inspection of the Hole of
the Area B of the frame 40, LH side at the interval given in the
table 5 of the Planning Information Paragraph E.(2).
(b) Upload the inspection report in AirbusWorld, refer to Appendix 01 - Inspection
Report
 .
NOTE
: Complete the inspection report sheets with detailed damage report
and pictures.
(10) Subtask 573114-832-010-001 - Do a Rototest Inspection of the Hole of the Area B
of the frame 40, RH side
Work Zones and Access Panels
Zone
 Access/Work location
138
 Work location
 Frame 40
Manpower Resources
Manhours
 0.25
Minimum number of person
 1
Subtask elapsed time
 0.25
Skills
 NON SPECIFIC
References
Non Destructive Test Manual (NTM)
 51-10-01
Fig. A-FCBAA
Inspection Area
Sheet
 01
Sheet
 02
Sheet
 03
Fig. A-FEAAA
Removal/Installation of the fasteners of
the Area B
Sheet
 01
Sheet
 02
Sheet
 03
Sheet
 04
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 43
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 58

@A330
SERVICE BULLETIN
Refer to Fig. A-FEAAA
At the threshold given in the Planning Information Paragraph E.(2):
(a) Do a rototest inspection of the area B of the
 Frame 40, RH side.
- Remove fastener at hole H39, RH side, refer to Fig. A-FEAAA Sheet 02
 :
1 Bolt Item (3) Discard
1 Nut Item (4) Discard
- Do a rototest inspection at hole H39, RH side.
Refer to Fig. A-FCBAA
Refer to NTM 51-10-01
1
 If no crack is found:
a
 Do SUBTASK 573114-833-014 001 Install new same fastener of the Area
B in transition fit, RH side before next flight
and
Repeat the rototest inspection as described in SUBTASK
573114-832-010 001 Do a Rototest Inspection of the Hole of the Area B
of the frame 40, RH side at the interval given in the table 5 of the
Planning Information Paragraph E.(2).
2
 If crack is found:
a
 Do SUBTASK 573114-833-017 001 Oversize the hole to the first
Oversize in comparison with the current hole diameter of the Area B, RH
side and check if crack is found with a rototest inspection before next
flight.
<1> If crack is found after the rototest inspection:
<a> Contact Airbus before next flight.
<2> If no crack is found after the rototest inspection:
<a> Do SUBTASK 573114-833-020 001 Install new fastener of the
Area B in transition fit, RH side before next flight
and
Repeat the rototest inspection as described in SUBTASK
573114-832-010 001 Do a Rototest Inspection of the Hole of
the Area B of the frame 40, RH side at the interval given in the
table 5 of the Planning Information Paragraph E.(2).
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 44
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 59

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SERVICE BULLETIN
(b) Upload the inspection report in AirbusWorld, refer to Appendix 01 - Inspection
Report
 .
NOTE
: Complete the inspection report sheets with detailed damage report
and pictures.
D. TEST
(1) Subtask 573114-700-003-001 - Testing
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 21-20-00-410-801
Task 21-52-41-400-801
Task 25-52-00-400-801
Task 36-22-19-400-801
Task 53-35-13-400-802
NOTE
: This Service Bulletin requires the accomplishment of the following Tests
which are given in subtasks included in the topic Close-Up. The
manhours for the tests are included in the referenced Service Bulletin
subtasks.
(a) Job Set-up:
1
 Remove the Safety clips and tags and close the circuit breakers as specified
after the Installation of the Belly Fairing Access-Panels 193DB and 192PB,
refer to
 AMM Task 53-35-13-400-802.
2
 Remove the Safety clips and tags and close the circuit breakers as specified
after the Installation of the Wing Bleed-air Duct Sensing Elements, refer to
AMM Task 36-22-19-400-801.
3
 Remove the Safety clips and tags and close the circuit breakers as specified
after the Installation of the Air Conditioning Pack, refer to
 AMM Task
21-52-41-400-801.
4
 Remove the Safety clips and tags and close the circuit breakers as specified
after the Installation of the Ceiling Panels, the Partition Panels and the
Sidewall Panels in the Forward Cargo Compartment 131CX, 131DX, 132CX
and 132DX, refer to
 AMM Task 25-52-00-400-801.
5
 Remove the Safety clips and tags and close the circuit breakers as specified
after the Installation of the Air-Conditioning Distribution Ducts, refer to
 AMM
Task 21-20-00-410-801.
(b) Procedure:
1
 If wing bleed-air ducts sensing elements have been removed for access, do
test procedure as specified after the Installation of the Wing Bleed-air Duct
Sensing Elements, refer to
 AMM Task 36-22-19-400-801.
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 45
5
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### Page 60

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SERVICE BULLETIN
2
 Do test procedure as specified after the Installation of the Air Conditioning
Pack, refer to
 AMM Task 21-52-41-400-801.
3
 If air-conditioning distribution ducts have been removed for access, do test
procedure as specified after the Installation of the Air-Conditioning Distribution
Ducts, refer to
 AMM Task 21-20-00-410-801.
E. CLOSE-UP
NOTE
: If you intend to accomplish an associated Repair Task during the same
layover period, the subsequent Close-up procedure is not necessary.
(1) Subtask 573114-410-001-001 - Install/Close Items Removed/Opened for access in
the Belly Fairing Area RH side
Manpower Resources
Skills
 NON SPECIFIC
Material necessary to do the job
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Polysulfide Sealant-Fuel
Contaminated Area Brusha
06ADA1
 As required
Adhesion Promoter-For
Polysulfide Sealant
06PAG1
 As required
References
Aircraft Maintenance Manual (AMM)
 Task 21-20-00-410-801
Task 21-52-41-400-801
Task 25-80-00-400-801
Task 36-22-19-400-801
Task 53-35-13-400-802
Fig. A-FBAAA
Removal/Installation of the Heat Shield
Sheet 01
Sheet 02
Fig. A-FDBAA
Removal/Installation of the Air
Conditioning Ducts between FR39.1 and
FR40 (Belly Fairing Area)
Sheet 01
Fig. A-FDCAA
Removal/Installation of the Air
Conditioning Ducts between FR39.1 and
FR40 (Belly Fairing Area)
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.
DATE: Mar 12/13 SERVICE BULLETIN No.: A330-57-3114
REVISION No.: 01 - Jan 13/17 Page: 46
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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