# Airbus Service Bulletin A330-53-3127

Copy: Revision 02 ("U.S. DOT/FAA - A330-53-3127 R02"), 56 pages: PDF https://openairdocs.org/files/sha256/cb/62/cb627b8f641bb764bb66081637e2cdd46014df786d2c758bdd85bbff72cfc8bf; text https://openairdocs.org/service-documents/airbus/a330-53-3127/file/cb627b8f641b.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2014-0061; AD 2014-16-25 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: A330-53-3127
- Latest revision known: A330-53-3127, Revision 02, dated December 7, 2011 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a330-53-3127

## ADs that cite it (3) (OpenAirDocs)

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

- [AD 2014-16-25](https://openairdocs.org/ad/2014-16-25.md), effective Oct 8, 2014: Revisions 01 and 02
- [AD 2007-06-12](https://openairdocs.org/ad/2007-06-12.md), effective Apr 20, 2007: Revision 01
- [AD 2005-20-07](https://openairdocs.org/ad/2005-20-07.md), effective Oct 19, 2005: Revision 01

Also cited in [2 proposed ADs](https://openairdocs.org/service-documents/airbus/a330-53-3127/proposed.md).

## Text (56 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2014-0061; AD 2014-16-25 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

@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: 53
TITLE: FUSELAGE - CENTER FUSELAG E - CIRCUMFERENTIAL JOINT FRAME
53.3, STGR 13 LH TO STGR 13 RH - FATIGUE LIFE IMPROVEMENT
MODIFICATION No.: 49403S16334
This page transmits Revision No.02 of Service Bulletin No.A330-53-3127
ADDITIONAL WORK
**CONF ALL
NOTE
: No additional work is required by this revision for aircraft modified by any previous
issue.
REASON
Revision No. 02 is issued to add the new thresholds and modify the Appendix 01.
CHANGES
SUMMARY
MODIFICATIONS
 Minor editorial or document structure change
 N
REASON/DESCRIPTION/OPERATIONAL
CONSEQUENCES
Minor editorial or document structure change
 N
GENERAL EVALUATION
 Minor editorial or document structure change
 N
MATERIAL PRICE INFORMATION
 Minor editorial or document structure change
 N
EFFECTIVITY
 Minor editorial or document structure change
 N
CONCURRENT REQUIREMENTS
 Minor editorial or document structure change
 N
REFERENCES / REPERCUSSIONS
 Minor editorial or document structure change
 N
NATURE OF THE WORK
 Minor editorial or document structure change
 N
MANPOWER
 Minor editorial or document structure change
 N
APPENDICES
 Minor editorial or document structure change
 N
Fig. A-FSAAA
 Minor editorial or document structure change
 N
Fig. A-FSAAA Sheet 01
 Minor editorial or document structure change
 N
PLANNING INFORMATION
EFFECTIVITY
 Minor editorial or document structure change
 N
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 2

@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Configuration definition
 Minor editorial or document structure change
 N
CONF 001
 Minor editorial or document structure change
 N
Material Effectivity
 Minor editorial or document structure change
 N
Minor editorial or document structure change
 N
CONCURRENT REQUIREMENTS
 Minor editorial or document structure change
 N
REASON
 Minor editorial or document structure change
 N
History
 Minor editorial or document structure change
 N
Objective/Action
 Minor editorial or document structure change
 N
Advantages
 Minor editorial or document structure change
 N
Operational/Maintenance
Consequences
Minor editorial or document structure change
 N
DESCRIPTION
 Minor editorial or document structure change
 N
COMPLIANCE
 Minor editorial or document structure change
 N
Classification
 Minor editorial or document structure change
 N
Accomplishment Timescale
 Threshold revised
 N
APPROVAL
 Minor editorial or document structure change
 N
Minor editorial or document structure change
 N
MANPOWER
 Minor editorial or document structure change
 N
Minor editorial or document structure change
 N
WEIGHT AND BALANCE
 Minor editorial or document structure change
 N
Minor editorial or document structure change
 N
ELECTRICAL LOAD DATA
 Minor editorial or document structure change
 N
REFERENCES
 Minor editorial or document structure change
 N
Minor editorial or document structure change
 N
PUBLICATION AFFECTED
 Minor editorial or document structure change
 N
Minor editorial or document structure change
 N
INTERCHANGEABILITY/MIXABILITY
 Minor editorial or document structure change
 N
SPARES
 Minor editorial or document structure change
 N
MATERIAL INFORMATION
MATERIAL - PRICE AND AVAILABILITY
 Minor editorial or document structure change
 N
Procurement Addresses
 Minor editorial or document structure change
 N
Price and Availability
 Minor editorial or document structure change
 N
INDUSTRY SUPPORT INFORMATION
 Minor editorial or document structure change
 N
LIST OF COMPONENTS
 Minor editorial or document structure change
 N
Kit 533127A01R05
 Minor editorial or document structure change
 N
LIST OF MATERIALS - OPERATOR
SUPPLIED
Minor editorial or document structure change
 N
Consumable Materials
 Minor editorial or document structure change
 N
Consumable CMLA01
 Minor editorial or document structure change
 N
Components
 Minor editorial or document structure change
 N
Equipment
 Minor editorial or document structure change
 N
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 3

@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
PARTS TO BE RE-IDENTIFIED BY
OPERATOR
Minor editorial or document structure change
 N
TOOLING
 Minor editorial or document structure change
 N
Tooling - Price and Availability
 Minor editorial or document structure change
 N
Tools
 Minor editorial or document structure change
 N
Special Tools
 Minor editorial or document structure change
 N
ACCOMPLISHMENT INSTRUCTIONS
TASK 533127- 831-801-001-
MODIFICATION
Minor editorial or document structure change
 N
Task associated data - 001
 Minor editorial or document structure change
 N
Subtask 533127-910-001-001
 Minor editorial or document structure change
 N
Subtask 533127-839-001-001
 Minor editorial or document structure change
 N
Subtask 533127-941-001-001
 Minor editorial or document structure change
 N
Subtask 533127-831-004-001
 Minor editorial or document structure change
 N
Subtask 533127-831-005-001
 Minor editorial or document structure change
 N
Subtask 533127-831-006-001
 Minor editorial or document structure change
 N
Subtask 533127-831-007-001
 Minor editorial or document structure change
 N
Subtask 533127-831-008-001
 Minor editorial or document structure change
 N
Subtask 533127-700-009-001
 Minor editorial or document structure change
 N
Subtask 533127-942-010-001
 Minor editorial or document structure change
 N
Fig. A-FBAAA
 Minor editorial or document structure change
 N
Fig. A-FBAAA Sheet 01
 Minor editorial or document structure change
 N
Fig. A-FBAAA Sheet 02
 Minor editorial or document structure change
 N
Fig. A-FBAAA Sheet 03
 Minor editorial or document structure change
 N
Fig. A-FBAAA Sheet 04
 Minor editorial or document structure change
 N
Fig. A-FBAAA Sheet 05
 Minor editorial or document structure change
 N
Fig. A-FBAAA Sheet 06
 Minor editorial or document structure change
 N
Fig. A-FBAAA Sheet 07
 Minor editorial or document structure change
 N
Fig. A-FBAAA Sheet 08
 Minor editorial or document structure change
 N
Appendix - 01
APPENDIX CONTENT
 Minor editorial or document structure change
 N
Fig. A-FAAAA
 Minor editorial or document structure change
 N
Fig. A-FAAAA Sheet 01
 Minor editorial or document structure change
 N
Fig. A-FABAA
 Minor editorial or document structure change
 N
Fig. A-FABAA Sheet 01
 Minor editorial or document structure change
 N
Fig. A-FACAA
 Minor editorial or document structure change
 N
Fig. A-FACAA Sheet 01
 Minor editorial or document structure change
 N
Appendix - 02
APPENDIX CONTENT
 Minor editorial or document structure change
 N
Fig. A-FADAA
 Minor editorial or document structure change
 N
Fig. A-FADAA Sheet 01
 Minor editorial or document structure change
 N
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 3
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 4

@A330
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
FILLING INSTRUCTIONS
This Service Bulletin has been generated electronically and is reissued as a complete document.
Replace the complete document.
Put this Revision Transmittal Sheet in front of the Service Bulletin.
HISTORY OF PREVIOUS REVISIONS
No previous revisions.
Revision No. 01 issued to supersede Airworthiness Directive (Consigne de Navigabilite) No.
2002-529(B) by No. F-2003-415(B), to modify the manpower and Kit 533127A01R05 further to
validation of this Service Bulletin on MSN 0059.
Also, Mat. No. 09-013 has been added.
REVISION SEQUENCE
ORIGINAL: Oct 30/02
REVISION No. : 02 - Dec 07/11
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 4
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 5

@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: 53
TITLE: FUSELAGE - CENTER FUSELAG E - CIRCUMFERENTIAL JOINT FRAME
53.3, STGR 13 LH TO STGR 13 RH - FATIGUE LIFE IMPROVEMENT
**CONF ALL
MODIFICATIONS
MODIFICATION CLASSIFICATION
MAJOR
 49403S16334
MINOR
 None
NOTE
: As per EASA IR 21, a minor change is one that has no appreciable effect on the
mass, balance, structural strength, reliability, operational characteristics affecting the
airworthiness of the product. All other changes are major changes.
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
Further to damages occurred during fatigue tests, it has been decided to install an external stiffener of
butt strap type at the upper part of the circumferential joint at Frame 53.3, in order to improve fatigue
life.
This Service Bulletin requires the reinforcement of the circumferencial joint at the upper part at Frame
53.3 by installing external stiffeners between LH and RH STGR13.
Accomplishment of this Service Bulletin will allow improving fatigue life of the circumferencial joint at
Frame 53.3 and will thus postpone the next inspection to beyond the design service goal.
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
 YES
 VENDOR SB INVOLVED
 NO
NOTE
 (1)
: Service Bulletin must be accomplished.
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 6

@A330
SERVICE BULLETIN
SUMMARY
MATERIAL PRICE INFORMATION
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 533127A01R05
 1
 13,390.00
 Butt Straps, Shims
EFFECTIVITY
This Service Bulletin is applicable to this (these) operator(s) :
BEL CPA G8E HDA HFY MAS OHY THA TSC VLK XAX
CONCURRENT REQUIREMENTS
None
REFERENCES / REPERCUSSIONS
TFU
 None
OEB
 None
AOT
 None
SIL
 None
LINE MAINTENANCE AFFECTED
 No
LIFE LIMIT
 None
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
HARD
 NO
SOFT
 NO
OBRM
 NO
MANPOWER
Task 533127-831-801-001: MODIFICATION
TOTAL MANHOURS
 314.50
ELAPSED TIME (HOURS)
 56.25
APPENDICES
Appendix - 01
Appendix - 02
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 7

@A330
SERVICE BULLETIN
SUMMARY
**CONF ALL
FR38
FR54
STGR5
STGR5
STGR13
FR53.3
BUTT STRAPS
G_SB_533127_5_SAAA_01_00
Figure A-FSAAA - Sheet 01
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 3
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 8

@A330
SERVICE BULLETIN
SUMMARY
This Page Intentionally Left Blank
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 4
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 9

@A330
SERVICE BULLETIN
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 53
TITLE: FUSELAGE - CENTER FUSELAG E - CIRCUMFERENTIAL JOINT FRAME
53.3, STGR 13 LH TO STGR 13 RH - FATIGUE LIFE IMPROVEMENT
MODIFICATION No.: 49403S16334
This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the
property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with
any information contained in it. It is delivered on the express condition that said document and the
information contained in it shall be treated as confidential, shall not be used for any purpose other than
that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall
not be duplicated in any manner (except for the purposes of performing the tasks described hereunder
and provided that any recipient of such document shall comply with the conditions herein), without
AIRBUS prior written consent.
1. PLANNING INFORMATION
**CONF ALL
A. EFFECTIVITY
NOTE
: This modification is only applicable to aircraft on which
Mod. No. 41652S11819 (FUSELAGE-STRUCTURE-INTRODUCE A340
COMMONALITY ITEMS) is not embodied.
This Service Bulletin has been validated on A330 aircraft 0059.
(1) Models
330-301 330-321 330-322 330-342
(2) Effectivity by MSN
0012 0017 0030 0037 0045 0050 0054-0055 0059-0060 0062 0064-0067 0069-0073
0077 0082-0083 0086-0087 0095-0096 0098-0100 0102 0106-0107 0109-0112
(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: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 10

@A330
SERVICE BULLETIN
OPERATOR
 MSN
BEL
 0030 0037 0045 0082 0095
CPA
 0012 0017 0071 0102
G8E
 0059
HDA
 0083 0099 0106 0109
HFY
 0096
MAS
 0067 0069 0073 0077 0100 0107 0110
OHY
 0072 0087 0098
THA
 0050 0060 0062 0064 0065 0066 0112
TSC
 0111
VLK
 0055 0070 0086
XAX
 0054
(4) Configuration by MSN
MSN
 CONFIGURATION
0012 0017 0030 0037 0045 0050 0054 0055 0059 0060 0062
0064 0065 0066 0067 0069 0070 0071 0072 0073 0077 0082
0083 0086 0087 0095 0096 0098 0099 0100 0102 0106 0107
0109 0110 0111 0112
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 533127A01R05
 1
Consumable CMLA01
 1
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
Further to damages occurred during fatigue tests, it has been decided to install an
external stiffener of butt strap type at the upper part of the circumferential joint at Frame
53.3, in order to improve fatigue life.
(2) Objective/Action
This Service Bulletin requires the reinforcement of the circumferencial joint at the upper
part at Frame 53.3 by installing external stiffeners between LH and RH STGR13.
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 11

@A330
SERVICE BULLETIN
(3) Advantages
Accomplishment of this Service Bulletin will allow improving fatigue life of the
circumferencial joint at Frame 53.3 and will thus postpone the next inspection to beyond
the design service goal.
(4) Operational/Maintenance Consequences
None
D. DESCRIPTION
To accomplish this Service Bulletin it is necessary to :
Task 533127-831-801-001: MODIFICATION
(1) Install the butt strap Item 6 and the shims Item 12 at FR53.3, on the fuselage skin
between LH and RH STGR5.
(2) Install the butt strap Item 7 and the shim Item 9 at FR53.3, on the fuselage skin
between LH STGR5 and LH STGR13
(3) Install the butt strap Item 8 and the shim Item 10 at FR53.3, on the fuselage skin
between RH STGR5 and RH STGR13
(4) Apply sealant around the butt straps
(5) Paint the modified area
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
Compliance Times
(Whichever occurs first)
Condition
 Action
Threshold
 Grace Period
Interval
For the Short
Range (SR)
Mission : 15,300FC
/ 46,100FH
None
Config. 001
 Do the TASK
533127-831-801
001
MODIFICATION
For the Long
Range (LR)
Mission : 13,200FC
/ 79,300FH
None
None
Accomplishment Timescale Table
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 3
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 12

@A330
SERVICE BULLETIN
One set of threshold (Short Range, Threshold (SR) and Long Range, Threshold (LR))
has been established. This set ensure continued airworthiness and could be used to
cover any type of A/C utilization. This approach is an equivalent damage approach
corresponding to a trade off between FC/FH to better suit the fleet utilization. As the set
of thresholds ensure continued airworthiness and could be used to cover any type of
utilization, for the 1st inspection, operators may select either SR (Threshold) or LR
(Threshold) (depending of the A/C utilization evolution). If a non optimal set of threshold
is selected, airworthiness will be ensured, but will penalize the operator because the
inspection will be performed sooner than necessary. As a consequence, the selection of
SR or LR threshold can be changed whenever. Threshold is whichever occurs first
between FC and FH for a set of threshold between SR and LR. This means that the set
FC/FH must be considered jointly (ie FCSR cannot be used with FHLR and vice versa).
This Service Bulletin has been classified Mandatory by the issue of an Airworthiness
Directive (AD) published by the European Av iation Safety Agenc y (EASA). The AD must
be used as the reference document for the mandated accomplishment timescale.
F. APPROVAL
The technical content of this document is approved under the authority of Design
Organisation Approval No. EASA.21J.031.
If an aircraft listed in the effectivity has a modification or repair embodied that is not of
AIRBUS origin, and which affects the content of this Service Bulletin, the operator is
responsible for obtaining approval by its airworthiness authority for any adaptation necessary
before incorporation of the Service Bulletin.
G. MANPOWER
The manpower estimates given in this Service Bulletin are based on the direct labor cost to
do the work. These estimates assume that the work will be done by experienced personnel,
and may need to be revised upwards to suit operator’s circumstances. The estimates do not
include the time to prepare, plan or inspect the work. Manufacture and procurement of parts
and tools, drying times for paints, sealants, etc., and general administration work are also not
included.
Task 533127-831-801-001: MODIFICATION
Get Access
 66.00
On Aircraft
Install the butt strap Item 6 and the shims Item 12 at
FR53.3, on the fuselage skin between LH and RH
STGR5.
57.00
Install the butt strap Item 7 and the shim Item 9 at
FR53.3, on the fuselage skin between LH STGR5 and
LH STGR13
57.00
Install the butt strap Item 8 and the shim Item 10 at
FR53.3, on the fuselage skin between RH STGR5 and
RH STGR13
57.00
Apply sealant around the butt straps
 4.00
Paint the modified area
 4.50
Tests
 3.00
Close-Up
 66.00
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 4
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 13

@A330
SERVICE BULLETIN
Task 533127-831-801-001: MODIFICATION
TOTAL MANHOURS
 314.50
ELAPSED TIME (HOURS)
 56.25
NOTE
: For the elapsed time assumptions, refer to Appendix - 02 .
H. WEIGHT AND BALANCE
The weight and balance estimates given in this Service Bulletin are based on the
Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of
MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07.
Manufacturers Empty Weight +4.3 KG (+9.4797 LB)
Effect on Balance +173.982 KGM (+1258.411 LB.FT )
I. ELECTRICAL LOAD DATA
Not Changed
J. REFERENCES
Aircraft Maintenance Manual (AMM)
 05-53-00 12-34-24 20-21-11
21-20-00 25-23-41 25-24-51
25-24-61 25-80-00 52-10-00
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
Non Destructive Test Manual (NTM)
 51-10-01
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-21-11 51-23-11 51-42-11
51-43-00 51-46-11 51-48-00
51-76-11
Weight and Balance Manual (WBM)
 Chapter 1-00-07
Aircraft Maintenance Manual (AMM)
 07-11-00
Structural Repair Manual (SRM)
 51-51-00
K. PUBLICATION AFFECTED
Structural Repair Manual (SRM)
 53-31-11
L. INTERCHANGEABILITY/MIXABILITY
Not Applicable
M. SPARES
None
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 5
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 14

@A330
SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 6
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 15

@A330
SERVICE BULLETIN
2. MATERIAL INFORMATION
**CONF ALL
A. MATERIAL - PRICE AND AVAILABILITY
(1) Procurement Addresses
Customers with aircraft shown in the effectivity of this Service Bulletin should send a
purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is :
Kit 533127A01R05
 AIRBUS Material, Logistics and Suppliers
Weg beim Jaeger 150
D-22335 HAMBURG
GERMANY
For ordering by internet:
http://spares.airbus.com
For ordering by fax: +49 40 50 76 2590
For ordering by E-mail: airbus.kit@airbus.com
(2) Price and Availability
Kit 533127A01R05
Cost
 13,390.00 USD
Availability
 90 calendar days from receipt of order
The Kit availability given above is the standard lead time from the date of your purchase
order. If you require Kits 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 at the issue date of the
Service Bulletin.
B. INDUSTRY SUPPORT INFORMATION
This Service bulletin is subject to the Fatigue Test Integration Program. Refer to the FTIP
policy.
C. LIST OF COMPONENTS
Kit 533127A01R05
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
1
 ASNA2528-4
 744
 Nut
2
 ASNA2026V4-8
 284
 Bolt
3
 ASNA2026V4-11
 432
 Bolt
5
 ASNA2026V4-13
 88
 Bolt
6
 F5332579020096
 1
 Strap
7
 F5332579120096
 1
 Strap
8
 F5332579120196
 1
 Strap
9
 F5332579220096
 1
 Shim
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 7
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 16

@A330
SERVICE BULLETIN
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
10
 F5332579220196
 1
 Shim
11
 ASNA2531-4
 60
 Nut
12
 F5332578120095
 2
 Shim
NOTE
: If you find part numbers of hardware components in the related kit(s) which
you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,
refer to Standards Manual (SM). The SM will give you the correct part number
to part number relationship.
D. LIST OF MATERIALS - OPERATOR SUPPLIED
(1) Consumable Materials
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
Corrosion Inhibiting Brush
Consistency
09-013
 As required
Sealant
 09-016
 As required
Solvent General Purpose
 11-026
 As required
Chemical Conversion Coating
 13-002
 As required
Anti-Corrosion Primer
 16-001
 As required
Polyurethane Top Coat Grey
 16-002
 As required
External Decoration Paint
 16-016
 As required
External Top Coat
 16-018
 As required
Wash Primer
 16-020
 As required
(2) Components
None
(3) Equipment
None
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
F. TOOLING
(1) Tooling - Price and Availability
None
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 8
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 17

@A330
SERVICE BULLETIN
(2) Tools
- Fatigue Technology Incorporated (FTI) has allocated tool kit number FTI-
A330-53-3127-1 for accomplishment of this Service Bulletin. Operators interested in
obtaining the FTI tool kit should contact :
Fatigue Technology Inc.
401 Andover Park East
SEATTLE WA 98188-7605
USA
Tel : (206) 246-2010
Telex : 321004
Fax : (206) 244-9886
To accomplish this Service Bulletin, it is necessary to use the following tools and
equipment :
- Equipment and materials for check of holes as per NTM 51-10-01, Part 6,
Procedure A.
- Equipment and materials for the jacking procedure (Refer to Appendix - 01 ).
(3) Special Tools
None
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 9
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 18

@A330
SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 10
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 19

@A330
SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS
Task 533127-831-801-001 - MODIFICATION
WARNING
: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
CAUTION
: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP
ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY
AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE
WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,
COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO
THIS :
- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC., AS
NECESSARY ON WIRING AND COMPONENTS
- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND
OTHER CONTAMINATION
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION
AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.
IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.
Task Associated Data
Zone
250
Manpower
TOTAL MANHOURS
 314.50
ELAPSED TIME (HOURS)
 56.25
A. GENERAL
(1) Subtask 533127-910-001-001 - Standard Practices
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
Solvent General Purpose
 11-026
 As required
Chemical Conversion
Coating
13-002
 As required
Anti-Corrosion Primer
 16-001
 As required
Polyurethane Top Coat
Grey
16-002
 As required
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 11
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 20

@A330
SERVICE BULLETIN
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
External Decoration Paint
 16-016
 As required
External Top Coat
 16-018
 As required
Wash Primer
 16-020
 As required
References
Aircraft Maintenance Manual (AMM)
 20-21-11, Page Block 201
Consumable Material List (CML)
Structural Repair Manual (SRM)
 51-21-11
51-23-11
51-42-11
51-43-00
51-46-11
51-48-00
51-76-11
(a) For the specification of the material numbers (Mat. No.), refer to the CML.
(b) Remove and install the fasteners, (Refer to SRM 51-42-11).
(c) For the cold expansion of the fastener holes, (Refer to SRM 51-48-00).
(d) Countersink the holes, (Refer to SRM 51-46-11).
(e) Clean the surface to seal with :
Solvent General
Purpose
11-026 As required
(f) To apply sealant, (Refer to SRM 51-76-11).
(g) Torque the standard threaded fasteners, (Refer to AMM 20-21-11 Page Block 201).
(h) For alternative and substitute fasteners (Refer to SRM 51-43-00).
(i) Renew the protective finish with :
(Refer to SRM 51-21-11 and SRM 51-23-11)
Chemical
Conversion Coating
13-002 As required
or
Wash Primer 16-020 As required
and
Anti-Corrosion
Primer
16-001 As required
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 12
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 21

@A330
SERVICE BULLETIN
Polyurethane Top
Coat Grey
16-002 As required
and
External Top Coat 16-018 As required
or
External Decoration
Paint
16-016 As required
(j) If the length of any fastener specified in this Service Bulletin does not meet
installation standards given in SRM Chapter 51, then a fastener of the same
specification, or an approved substitute, with a length which meets the installation
standards given in SRM Chapter 51 may be used. In addition, washers may be
installed for fasteners grip length in accordance with SRM Chapter 51.
(2) Subtask 533127-839-001-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in the
Service Bulletin.
B. PREPARATION
(1) Subtask 533127-941-001-001 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 12-34-24, Page Block 201
21-20-00, Page Block 401
25-23-41, Page Block 401
25-24-51, Page Block 401
25-24-61, Page Block 401
25-80-00, Page Block 201
52-10-00, Page Block 201
(a) Electrically ground the aircraft, (Refer to AMM 12-34-24 Page Block 201).
(b) Put the access platform(s) in position.
(c) Open the passenger/crew door 831, (Refer to AMM 52-10-00 Page Block 201).
(d) Remove the ceiling panels 251PC, 251QC, 252PC and 252QC, (Refer to AMM
25-23-41 Page Block 401).
(e) Remove the center stowage compartment at Frame 53.3, (Refer to AMM 25-24-61
Page Block 401).
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 13
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 22

@A330
SERVICE BULLETIN
(f) Remove the LH and RH lateral overhead stowage compartments at Frame 53.3,
(Refer to AMM 25-24-51 Page Block 401).
(g) Remove the air distribution ducts for an easier access to the work area, (Refer to
AMM 21-20-00 Page Block 401).
(h) Disengage the electrical wires and the insulation blankets from the work area,
(Refer to AMM 25-80-00 Page Block 201).
NOTE
: If necessary, disengage the support plates of the decoder/encoder
units 200RH17 and 200RH18 to get access to the work area. Hold
the support plates because you must not pull the electrical wires.
Retain the fasteners.
(i) Do the jacking procedure, (Refer to Appendix - 01 ).
C. PROCEDURE
WARNING
: WEAR AND ATTACH A SAFETY HARNESS WHEN YOU WORK ON HIGH
SECTIONS. A FALL CAN KILL OR INJURE YOU.
NOTE
: Do not remove all the fasteners from the fuselage at the same time. First,
remove the fasteners between the LH and RH STGR 5 and install the upper
butt strap Item 6 and the shims Item 12. Then you can remove the other
fasteners and install the butt strap Items 7 and 8, and the shims Items 9 and
10 at the same time.
(1) Subtask 533127-831-004-001 - Install the butt strap Item 6 and the shims Item 12 at
FR53.3, on the fuselage skin between LH and RH STGR5.
Work Zones and Access Panels
Zone
 Access/Work location
250
 Work location
 Frame 53.3
from Stringer 5 LH to Stringer 5 RH
Manpower Resources
Manhours
 57.00
Minimum number of person
 4
Subtask elapsed time
 14.25
Skills
 AIRFRAME
Material necessary to do the job
Kit 533127A01R05
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 ASNA2528-4
 264
 Nut
2
 ASNA2026V4-8
 96
 Bolt
3
 ASNA2026V4-11
 160
 Bolt
5
 ASNA2026V4-13
 36
 Bolt
6
 F5332579020096
 2
 Strap
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 14
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 23

@A330
SERVICE BULLETIN
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
11
 ASNA2531-4
 28
 Nut
12
 F5332578120095
 4
 Shim
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Corrosion Inhibiting Brush
Consistency
09-013
 As required
Sealant
 09-016
 As required
Chemical Conversion
Coating
13-002
 As required
Anti-Corrosion Primer
 16-001
 As required
Polyurethane Top Coat
Grey
16-002
 As required
References
Non Destructive Test Manual (NTM)
 51-10-01 Part 6, Procedure A
Fig. A-FBAAA
Butt Strap Installation
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Sheet 07
Sheet 08
(a) Remove the fasteners between LH and RH STGR5
Refer to Fig. A-FBAAA Sheet 01
 , Fig. A-FBAAA Sheet 02
 and Fig. A-FBAAA Sheet
05
1
 From the LH side, remove :
Refer to Fig. A-FBAAA Sheet 02
140 Nut Item (1) Discard
48 Bolt Item (2) Discard
78 Bolt Item (3) Discard
14 Bolt Item (5) Discard
Refer to Fig. A-FBAAA Sheet 05
6 Nut Item (1) Discard
2 Bolt Item (3) Discard
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 15
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 24

@A330
SERVICE BULLETIN
4 Bolt Item (5) Discard
2
 From the RH side, remove :
Refer to Fig. A-FBAAA Sheet 02
140 Nut Item (1) Discard
48 Bolt Item (2) Discard
78 Bolt Item (3) Discard
14 Bolt Item (5) Discard
Refer to Fig. A-FBAAA Sheet 05
6 Nut Item (1) Discard
2 Bolt Item (3) Discard
4 Bolt Item (5) Discard
(b) Do an inspection of the holes
1
 Do a rototest in the 152 holes of the removed bolts, (Refer to NTM 51-10-01
Part 6, Procedure A), (Refer to Fig. A-FBAAA Sheet 02
 ).
2
 If a crack is found, contact AIRBUS.
3
 If no crack is found, do the steps that follow.
(c) Put the butt strap and the shims in position on the skin between LH and RH
STGR5
Refer to Fig. A-FBAAA Sheet 01
 , Fig. A-FBAAA Sheet 06
 , Fig. A-FBAAA Sheet 07
and Fig. A-FBAAA Sheet 08
1
 As shown in View E, Section AA and Section DD, put in position and hold :
1 Butt Strap F5332579020096 Item 6
2 Shim F5332578120095 Item 12
NOTE
 (1)
: Put the shims Item 12 in position between the fuselage skin
and the butt strap Item 6 to fill the clearance between the skin
and the butt strap.
(d) Counter-drill the fastener holes in the butt strap Item 6 and the shims Item 12
(Refer to Fig. A-FBAAA Sheet 01
 and Fig. A-FBAAA Sheet 02
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 16
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 25

@A330
SERVICE BULLETIN
CAUTION
: DO NOT DRILL THE 12 HOLES AT LH AND RH STGR5 AT THIS
TIME. YOU WILL DRILL THESE HOLES DURING THE COLD
EXPANSION STEP.
1
 In the butt strap Item 6 and in the shims Item 12 , counter-drill 280 holes,
temporarily attach the butt strap at the same time.
(e) Deburr the holes.
(f) For the cold expansion of the 12 holes at LH and RH STGR5 do the steps that
follow :
Refer to Fig. A-FBAAA Sheet 05
1
 For the cold expansion, use the tools supplied in Kit FTI-A330-53-3127-1.
2
 On the LH and the RH sides, counter-drill 12 holes in the butt strap Item 6 and
in the shims Item 12.
3
 Ream the 12 holes to the start hole diameter between 5.75 mm and 5.79 mm
(0.22638 in. and 0.22795 in.).
4
 Deburr the holes.
5
 Identify with a mark the LH and RH sides on the butt strap Item 6 before
removal, to prevent a wrong position when you install it.
NOTE
: If necessary, adjust the length of the butt strap Item 6 and the
shims Item 12.
Renew the protective finish on the reworked surfaces with :
Chemical
Conversion Coating
13-002 As required
Anti-Corrosion
Primer
16-001 As required
Polyurethane Top
Coat Grey
16-002 As required
6
 Remove the butt strap Item 6 and the shims Item 12.
7
 Do the cold expansion of the holes in the fuselage.
(g) Apply to the attachment areas between the butt strap, the shims and the fuselage :
Sealant 09-016 As required
(h) Install the butt strap Item 6 and the shims Item 12
Refer to Fig. A-FBAAA Sheet 01
 , Fig. A-FBAAA Sheet 02
 , Fig. A-FBAAA Sheet 05
 ,
Fig. A-FBAAA Sheet 06
 , Fig. A-FBAAA Sheet 07
 and Fig. A-FBAAA Sheet 08
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 17
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 26

@A330
SERVICE BULLETIN
1
 Put the butt strap and the shims in position on the skin, between LH and RH
STGR5 :
1 Butt Strap F5332579020096 Item 6
2 Shim F5332578120095 Item 12
NOTE
: Temporarily attach the parts.
Smooth the burr of sealant.
Let the sealant dry as necessary.
(i) Ream the fastener holes in the butt strap and the shims
NOTE
: Ream the holes from the inner side of the fuselage.
To prevent butt strap debonding during reaming, do not remove all
the temporary fasteners at the same time. Install the new fasteners
in the reamed holes one after the other as specified in the steps
that follow.
1
 Ream the 12 cold expanded holes to the finish hole diameter between 6.227
mm. and 6.262 mm (0.24516 in. and 0.24654 in.).
Refer to Fig. A-FBAAA Sheet 05
2
 Ream the 280 holes to a diameter between 6.310 mm and 6.350 mm
(0.24842 in. and 0.25000 in.).
Refer to Fig. A-FBAAA Sheet 02
(j) Countersink the 292 holes in the butt strap Item 6 for the bolts Items 2, 3 and 4.
(k) Deburr the holes.
(l) Attach the butt strap Item 6 and the shims Item 12 with :
Refer to Fig. A-FBAAA Sheet 02
 and Fig. A-FBAAA Sheet 06
96 Bolt ASNA2026V4-8 Item 2
156 Bolt ASNA2026V4-11 Item 3
28 Bolt ASNA2026V4-13 Item 5
264 Nut ASNA2528-4 Item 1
16 Nut ASNA2531-4 Item 11
Refer to Fig. A-FBAAA Sheet 05
 and Fig. A-FBAAA Sheet 06
4 Bolt ASNA2026V4-11 Item 3
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 18
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 27

@A330
SERVICE BULLETIN
8 Bolt ASNA2026V4-13 Item 5
12 Nut ASNA2531-4 Item 11
NOTE
: Apply to the countersunk holes before fastener installation :
Corrosion Inhibiting
Brush Consistency
09-013 As required
(2) Subtask 533127-831-005-001 - Install the butt strap Item 7 and the shim Item 9 at
FR53.3, on the fuselage skin between LH STGR5 and LH STGR13
Work Zones and Access Panels
Zone
 Access/Work location
250
 Work location
 Frame 53.3
from Stringer 5 LH to Stringer 13 LH
Manpower Resources
Manhours
 57.00
Minimum number of person
 4
Subtask elapsed time
 14.25
Skills
 AIRFRAME
Material necessary to do the job
Kit 533127A01R05
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 ASNA2528-4
 240
 Nut
2
 ASNA2026V4-8
 94
 Bolt
3
 ASNA2026V4-11
 136
 Bolt
5
 ASNA2026V4-13
 26
 Bolt
7
 F5332579120096
 2
 Strap
9
 F5332579220096
 2
 Shim
11
 ASNA2531-4
 16
 Nut
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Corrosion Inhibiting Brush
Consistency
09-013
 As required
Sealant
 09-016
 As required
Chemical Conversion
Coating
13-002
 As required
Anti-Corrosion Primer
 16-001
 As required
Polyurethane Top Coat
Grey
16-002
 As required
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 19
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 28

@A330
SERVICE BULLETIN
References
Non Destructive Test Manual (NTM)
 51-10-01 Part 6, Procedure A
Fig. A-FBAAA
Butt Strap Installation
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Sheet 07
Sheet 08
(a) Remove the fasteners between LH STGR5 and LH STGR13
Refer to Fig. A-FBAAA Sheet 03
 and Fig. A-FBAAA Sheet 04
1
 Between LH STGR5 and LH STGR13, remove :
Refer to Fig. A-FBAAA Sheet 03
128 Nut Item (1) Discard
56 Bolt Item (2) Discard
72 Bolt Item (3) Discard
Refer to Fig. A-FBAAA Sheet 04
128 Nut Item (1) Discard
38 Bolt Item (2) Discard
64 Bolt Item (3) Discard
26 Bolt Item (5) Discard
(b) Do an inspection of the holes
1
 Do a rototest in the 128 holes of the removed bolts, (Refer to NTM 51-10-01
Part 6, Procedure A), (Refer to Fig. A-FBAAA Sheet 03
 and Fig. A-FBAAA
Sheet 04
).
2
 If a crack is found, contact AIRBUS.
3
 If no crack is found, do the steps that follow.
(c) Put the butt strap in position on the skin between LH STGR5 and LH STGR13
Refer to Fig. A-FBAAA Sheet 01
 , Fig. A-FBAAA Sheet 06
 , Fig. A-FBAAA Sheet 07
and Fig. A-FBAAA Sheet 08
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 20
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 29

@A330
SERVICE BULLETIN
1
 As shown in View E, Section BB, Section CC and Section DD, put in position
and hold :
1 Butt Strap F5332579120096 Item 7
1 Shim F5332579220096 Item 9
NOTE
 (1)
: Put the shim Item 9 in position between the fuselage skin and
the butt strap Item 7 to fill the clearance between the skin and
the butt strap.
(d) Counter-drill the fastener holes in the butt strap Item 7 and shim Item 9
Refer to Fig. A-FBAAA Sheet 01
 , Fig. A-FBAAA Sheet 03
 and Fig. A-FBAAA Sheet
04
1
 In the butt strap Item 7 and the shim Item 9, counter-drill 256 holes,
temporarily attach the butt strap at the same time.
(e) Deburr the holes.
(f) Identify with a mark the upper and lower sides on the butt strap Item 7 before
removal, to prevent a wrong position when you install it.
NOTE
: If necessary, adjust the length of the butt strap Item 7 and the
shims Item 9.
Renew the protective finish on the reworked surfaces with :
Chemical
Conversion Coating
13-002 As required
Anti-Corrosion
Primer
16-001 As required
Polyurethane Top
Coat Grey
16-002 As required
(g) Remove the butt strap Item 7 and the shim Item 9.
(h) Apply to the attachment areas between the butt strap, the shim and the fuselage :
Sealant 09-016 As required
(i) Install the butt strap Item 7 and the shim Item 9
Refer to Fig. A-FBAAA Sheet 06
 , Fig. A-FBAAA Sheet 07
 and Fig. A-FBAAA Sheet
08
1
 Put the butt strap and the shim in position on the skin, between LH STGR5
and LH STGR13 :
1 Butt Strap F5332579120096 Item 7
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 21
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 30

@A330
SERVICE BULLETIN
1 Shim F5332579220096 Item 9
NOTE
: Temporarily attach the parts.
Smooth the burr of sealant.
Let the sealant dry as necessary.
(j) Ream the 256 holes to a diameter between 6.310 mm and 6.350 mm (0.24842 in.
and 0.25000 in.).
Refer to Fig. A-FBAAA Sheet 01
 , Fig. A-FBAAA Sheet 03
 and Fig. A-FBAAA Sheet
04
NOTE
: Ream the holes from the inner side of the fuselage.
To prevent butt strap debonding during reaming, do not remove all
the temporary fasteners at the same time. Install the new fasteners
in the reamed holes one after the other as specified in the steps
that follow.
(k) Countersink the 256 holes in the butt strap Item 7 for the bolts Items 2, 3, 4 and 5.
(l) Deburr the holes.
(m) Attach the butt strap Item 7 and the shim Item 9 with :
Refer to Fig. A-FBAAA Sheet 03
 , Fig. A-FBAAA Sheet 04
 and Fig. A-FBAAA Sheet
06
94 Bolt ASNA2026V4-8 Item 2
136 Bolt ASNA2026V4-11 Item 3
26 Bolt ASNA2026V4-13 Item 5
240 Nut ASNA2528-4 Item 1
16 Nut ASNA2531-4 Item 11
NOTE
: Apply to the countersunk holes before fastener installation :
Corrosion Inhibiting
Brush Consistency
09-013 As required
(3) Subtask 533127-831-006-001 - Install the butt strap Item 8 and the shim Item 10 at
FR53.3, on the fuselage skin between RH STGR5 and RH STGR13
Work Zones and Access Panels
Zone
 Access/Work location
250
 Work location
 Frame 53.3
from Stringer 5 RH to Stringer 13 RH
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 22
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 31

@A330
SERVICE BULLETIN
Manpower Resources
Manhours
 57.00
Minimum number of person
 4
Subtask elapsed time
 14.25
Skills
 AIRFRAME
Material necessary to do the job
Kit 533127A01R05
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 ASNA2528-4
 240
 Nut
2
 ASNA2026V4-8
 94
 Bolt
3
 ASNA2026V4-11
 136
 Bolt
5
 ASNA2026V4-13
 26
 Bolt
8
 F5332579120196
 1
 Strap
10
 F5332579220196
 2
 Shim
11
 ASNA2531-4
 16
 Nut
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Corrosion Inhibiting Brush
Consistency
09-013
 As required
Sealant
 09-016
 As required
Chemical Conversion
Coating
13-002
 As required
Anti-Corrosion Primer
 16-001
 As required
Polyurethane Top Coat
Grey
16-002
 As required
References
Non Destructive Test Manual (NTM)
 51-10-01 Part 6, Procedure A
Fig. A-FBAAA
Butt Strap Installation
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Sheet 07
Sheet 08
(a) Remove the fasteners between RH STGR5 and RH STGR13
Refer to Fig. A-FBAAA Sheet 03
 and Fig. A-FBAAA Sheet 04
1
 Between RH STGR5 and RH STGR13, remove :
Refer to Fig. A-FBAAA Sheet 03
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 23
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 32

@A330
SERVICE BULLETIN
128 Nut Item (1) Discard
56 Bolt Item (2) Discard
72 Bolt Item (3) Discard
Refer to Fig. A-FBAAA Sheet 04
128 Nut Item (1) Discard
38 Bolt Item (2) Discard
64 Bolt Item (3) Discard
26 Bolt Item (5) Discard
(b) Do an inspection of the holes
1
 Do a rototest in the 128 holes of the removed bolts, (Refer to NTM 51-10-01
Part 6, Procedure A), (Refer to Fig. A-FBAAA Sheet 03
 and Fig. A-FBAAA
Sheet 04
).
2
 If a crack is found, contact AIRBUS.
3
 If no crack is found, do the steps that follow.
(c) Put the butt strap in position on the skin between RH STGR5 and RH STGR13
Refer to Fig. A-FBAAA Sheet 01
 , Fig. A-FBAAA Sheet 06
 , Fig. A-FBAAA Sheet 07
and Fig. A-FBAAA Sheet 08
1
 As shown in View E, Section BB, Section CC and Section DD, put in position
and hold :
1 Butt Strap F5332579120196 Item 8
1 Shim F5332579220196 Item 10
NOTE
 (1)
: Put the shim Item 10 in position between the fuselage skin and
the butt strap Item 8 to fill the clearance between the skin and
the butt strap.
(d) Counter-drill the fastener holes in the butt strap Item 8 and shim Item 10
Refer to Fig. A-FBAAA Sheet 01
 , Fig. A-FBAAA Sheet 03
 and Fig. A-FBAAA Sheet
04
1
 In the butt strap Item 8 and the shim Item 10, counter-drill 256 holes,
temporarily attach the butt strap at the same time.
(e) Deburr the holes.
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 24
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 33

@A330
SERVICE BULLETIN
(f) Identify with a mark the upper and lower sides on the butt strap Item 8 before
removal, to prevent a wrong position when you install it.
NOTE
: If necessary, adjust the length of the butt strap Item 8 and the
shims Item 10.
Renew the protective finish on the reworked surfaces with :
Chemical
Conversion Coating
13-002 As required
Anti-Corrosion
Primer
16-001 As required
Polyurethane Top
Coat Grey
16-002 As required
(g) Remove the butt strap Item 8 and the shim Item 10.
(h) Apply to the attachment areas between the butt strap, the shim and the fuselage :
Sealant 09-016 As required
(i) Install the butt strap Item 8 and the shim Item 10
Refer to Fig. A-FBAAA Sheet 06
 , Fig. A-FBAAA Sheet 07
 and Fig. A-FBAAA Sheet
08
1
 Put the butt strap and the shim in position on the skin, between RH STGR5
and RH STGR13 :
1 Butt Strap F5332579120196 Item 8
1 Shim F5332579220196 Item 10
NOTE
: Temporarily attach the parts.
Smooth the burr of sealant.
Let the sealant dry as necessary.
(j) Ream the 256 holes to a diameter between 6.310 mm and 6.350 mm (0.24842 in.
and 0.25000 in.).
Refer to Fig. A-FBAAA Sheet 01
 , Fig. A-FBAAA Sheet 03
 and Fig. A-FBAAA Sheet
04
NOTE
: Ream the holes from the inner side of the fuselage.
To prevent butt strap debonding during reaming, do not remove all
the temporary fasteners at the same time. Install the new fasteners
in the reamed holes one after the other as specified in the steps
that follow.
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 25
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 34

@A330
SERVICE BULLETIN
(k) Countersink the 256 holes in the butt strap Item 8 for the bolts Items 2, 3, 4 and 5.
(l) Deburr the holes.
(m) Attach the butt strap Item 8 and the shim Item 10 with :
Refer to Fig. A-FBAAA Sheet 03
 , Fig. A-FBAAA Sheet 04
 and Fig. A-FBAAA Sheet
06
94 Bolt ASNA2026V4-8 Item 2
136 Bolt ASNA2026V4-11 Item 3
26 Bolt ASNA2026V4-13 Item 5
240 Nut ASNA2528-4 Item 1
16 Nut ASNA2531-4 Item 11
NOTE
: Apply to the countersunk holes before fastener installation :
Corrosion Inhibiting
Brush Consistency
09-013 As required
(4) Subtask 533127-831- 007-001 - Apply sealant around the butt straps
Work Zones and Access Panels
Zone
 Access/Work location
250
 Work location
 Frame 53.3
from Stringer 13 LH to Stringer 13 RH
Manpower Resources
Manhours
 4.00
Minimum number of person
 2
Subtask elapsed time
 2.00
Skills
 NON SPECIFIC
Material necessary to do the job
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Sealant
 09-016
 As required
(a) Around the butt straps, apply a bed of
Sealant 09-016 As required
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 26
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 35

@A330
SERVICE BULLETIN
(5) Subtask 533127-831-008-001 - Paint the modified area
Work Zones and Access Panels
Zone
 Access/Work location
250
 Work location
 Frame 53.3
from Stringer 13 LH to Stringer 13 RH
Manpower Resources
Manhours
 4.50
Minimum number of person
 2
Subtask elapsed time
 2.25
Skills
 NON SPECIFIC
Material necessary to do the job
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Anti-Corrosion Primer
 16-001
 As required
External Decoration Paint
 16-016
 As required
External Top Coat
 16-018
 As required
(a) Apply
Anti-Corrosion
Primer
16-001 As required
to the bolt heads then apply
External Top Coat 16-018 As required
or
External Decoration
Paint
16-016 As required
to the bolt heads and the butt straps.
D. TEST
(1) Subtask 533127-700-009-001 - Testing
Manpower Resources
Skills
 NON SPECIFIC
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 27
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 36

@A330
SERVICE BULLETIN
References
Aircraft Maintenance Manual (AMM)
 05-53-00, Page Block 501
21-20-00, Page Block 401
25-23-41, Page Block 401
25-24-51, Page Block 401
25-24-61, Page Block 401
25-80-00, Page Block 201
(a) Do a test for leakage in the repair area at a differential pressure of 280 mbar (4.06
psi), (Refer to AMM 05-53-00 Page Block 501).
(b) Install the removed equipment
1
 Install the electrical wires and the insulation blankets that you disengaged to
get access to the work area, (Refer to AMM 25-80-00 Page Block 201).
NOTE
: If you disengaged the support plates of the decoder/encoder
units 200RH17 and 200RH18, put them in position and attach
with the fasteners retained at removal.
2
 Install the air distribution ducts that you removed for an easier access to the
work area, (Refer to AMM 21-20-00 Page Block 401).
3
 Install the LH and RH lateral overhead stowage compartments at Frame 53.3,
(Refer to AMM 25-24-51 Page Block 401).
4
 Install the center stowage compartment at Frame 53.3, (Refer to AMM
25-24-61 Page Block 401).
5
 Install the ceiling panels 251PC, 251QC, 252PC and 252QC, (Refer to AMM
25-23-41 Page Block 401).
(c) Do the test after the removal/installation of the ceiling panels, (Refer to AMM
25-23-41 Page Block 401).
(d) Do the test after the removal/installation of the center-overhead stowage
compartments, (Refer to AMM 25-24-61 Page Block 401).
(e) Do the test after the removal/installation of the lateral-overhead stowage-
compartments, (Refer to AMM 25-24-51 Page Block 401).
E. CLOSE-UP
(1) Subtask 533127-942-010-001 - Close-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 12-34-24, Page Block 201
52-10-00, Page Block 201
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 28
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 37

@A330
SERVICE BULLETIN
(a) Put the aircraft on its wheels and remove the jacking equipment, (Refer to
Appendix - 01 ).
(b) Close the passenger/crew door 831, (Refer to AMM 52-10-00 Page Block 201).
(c) Remove the access platform(s).
(d) Disconnect the aircraft electrical ground-connection, (Refer to AMM 12-34-24 Page
Block 201).
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 29
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 38

@A330
SERVICE BULLETIN
**CONF ALL
FR38
FR54
STGR5
STGR5
STGR13
STGR13
STGR5
CLA/C
BC
D
B C
D
A
E
FR53.3
STGR13
STGR5
FR53.3
STGR9 STGR9
A
G_SB_533127_5_BAAA_01_01
Figure A-FBAAA - Sheet 01
Butt Strap Installation
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 30
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 39

@A330
SERVICE BULLETIN
**CONF ALL
FR53.3
FWD
SYMBOLSYMBOL REMOVED ITEMS NEW HOLE DIAMETER NEW BOLT NEW NUT
NUT BOLT PN ITEM
ASNA2026V4−8
ITEMPN
(1) (2) 6.310(0.24842) 6.350(0.25000) 2 1ASNA2528−4
(1) 6.310(0.24842) 6.350(0.25000) 1ASNA2528−4(3) 3
FASTENERS NOT REMOVED
CLA/C
STGR5
STGR4
STGR3
STGR1
STGR2
(1) 6.310(0.24842) 6.350(0.25000) 1ASNA2528−4
B
MIN. mm
(in.) (in.)
MAX. mm
DO A ROTOTEST IN THESE HOLES
A
DO A COLD EXPANSION OF THESE HOLES
(REFER TO DETAIL SHEET 5)
(1) 6.350(0.25000)
LH SIDE SHOWN FROM THE INSIDE
RH SIDE SYMMETRICAL
(5) ASNA2026V4−13 5
ASNA2026V4−11
(3) ASNA2026V4−11 3 ASNA2531−4 116.310(0.24842)
G_SB_533127_5_BAAA_02_00
Figure A-FBAAA - Sheet 02
Butt Strap Installation
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 31
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 40

@A330
SERVICE BULLETIN
**CONF ALL
FR53.3
STGR5
STGR6
STGR7
STGR8
STGR9
FWD
SYMBOLSYMBOL REMOVED ITEMS NEW HOLE DIAMETER NEW BOLT NEW NUT
NUT BOLT PN ITEM
ASNA2026V4−8
ITEMPN
(1) (2) 6.310(0.24842) 6.350(0.25000) 2 1ASNA2528−4
(1) 6.310(0.24842) 6.350(0.25000) 1ASNA2528−4(3) 3
FASTENERS NOT REMOVED
C
(in.) (in.)
MAX. mmMIN. mm
DO A ROTOTEST IN THESE HOLES
LH SIDE SHOWN FROM THE INSIDE
RH SIDE SYMMETRICAL
(1) 6.310(0.24842) 6.350(0.25000)(3) 3ASNA2026V4−11 ASNA2531−4 11
ASNA2026V4−11
G_SB_533127_5_BAAA_03_00
Figure A-FBAAA - Sheet 03
Butt Strap Installation
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 32
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 41

@A330
SERVICE BULLETIN
**CONF ALL
FR53.3
FWD
SYMBOLSYMBOL REMOVED ITEMS NEW HOLE DIAMETER NEW BOLT NEW NUT
NUT BOLT PN ITEM
ASNA2026V4−8
ITEMPN
(1) (2) 6.310(0.24842) 6.350(0.25000) 2 1ASNA2528−4
(1) 6.310(0.24842) 6.350(0.25000) 1ASNA2528−4(3) 3
FASTENERS NOT REMOVED
(1) 6.310(0.24842) 6.350(0.25000)
(1) 6.310(0.24842) 6.350(0.25000) 1ASNA2528−4(5) ASNA2026V4−13 5
STGR9
STGR10
STGR11
STGR12
STGR13
MIN. mm
(in.) (in.)
MAX. mm
D
DO A ROTOTEST IN THESE HOLES
(1) 6.350(0.25000)(3) ASNA2026V4−11 3 ASNA2531−4 116.310(0.24842)
LH SIDE SHOWN FROM THE INSIDE
RH SIDE SYMMETRICAL
ASNA2026V4−13
ASNA2026V4−11
5 ASNA2531−4 11(5)
G_SB_533127_5_BAAA_04_00
Figure A-FBAAA - Sheet 04
Butt Strap Installation
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 33
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 42

@A330
SERVICE BULLETIN
**CONF ALL
FR53.3
FWD
NUT BOLT
(1)
(1)
=
STGR5
TO A/C CL
A
B
HOLES
N
A
B
MIN. MAX.
REMOVED
ITEMS STDN
MIN. MAX.
NEW
BOLT
NEW
NUT
mm
(in.)
mm
(in.)
(3) 5.75(0.22638) 5.79(0.22795) 6.3N 6.227(0.24516) 6.262(0.24654) 3
5.75
(0.22638)
5.79
(0.22795) 6.3N 6.227(0.24516) 6.262(0.24654)
FASTENERS NOT REMOVED
COLD EXPANSION, HOLES AND FASTENERS DATA
PN/ITEM PN/ITEM
*
START *
HOLE DIAMETER
FINISH *
HOLE DIAMETER
ASNA
2531−4
ASNA
2531−4
11
11
A
− REAM THE START HOLE DIAMETERS WITH THE BUTT STRAP ITEM 6 AND THE SHIMS
ITEM 12 AND 13 ATTACHED TO THE FUSELAGE
− REMOVE THE BUTT STRAP ITEM 6 AND THE SHIMS ITEM 12 AND 13 AND DO THE
COLD EXPANSION OF HOLES IN THE FUSELAGE
LH SIDE SHOWN FROM THE INSIDE
RH SIDE SYMMETRICAL
DETAIL
COLD EXPANSION OF THE HOLES
B
B B A
PRINCIPLE DIAGRAM FOR
THE INSTALLATION
DIRECTION OF THE
EXPANSION SLEEVE:
− ATTACH THE BUTT STRAP ITEM 6 AND THE SHIMS ITEM 12 AND 13 AGAIN TO THE
FUSELAGE AND REAM THE FINISH HOLE DIAMETERS.
(5)
ASNA
2026V4−11
ASNA
2026V4−13 5
G_SB_533127_5_BAAA_05_00
Figure A-FBAAA - Sheet 05
Butt Strap Installation
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 34
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 43

@A330
SERVICE BULLETIN
**CONF ALL
STGR5
STGR5
STGR13
FR53.3
STGR12
STGR11
CLA/C
STGR13
STGR12
STGR11
10
A
A
9
E
SHIM
6*
* : IF NECESSARY ADJUST THE LENGTH
8*
7*
SHIM
SKIN
PANELS
D
B
B
C
C
D
SHIM12
12SHIM
G_SB_533127_5_BAAA_06_00
Figure A-FBAAA - Sheet 06
Butt Strap Installation
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 35
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 44

@A330
SERVICE BULLETIN
**CONF ALL
FWD
FR53.3
STGR11
STGR12
STGR13
SECTION
7
8
LH
RH
LH
RH
SECTION
7
8
LH
RH
NOTE: LH SIDE SECTIONS SHOWN
RH SIDE SYMMETRICAL
*
9*
10*
LH
RH
9*
10*
: ADJUST IF NECESSARY
B−B
C−C
VIEW LOOKING AFT
G_SB_533127_5_BAAA_07_00
Figure A-FBAAA - Sheet 07
Butt Strap Installation
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 36
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 45

@A330
SERVICE BULLETIN
**CONF ALL
7
8
LH
RH
6
SECTION
VIEW LOOKING AFT
D−D
12
FR53.3
6
SECTION
A−A
FWD
12*
G_SB_533127_5_BAAA_08_00
Figure A-FBAAA - Sheet 08
Butt Strap Installation
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 37
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 46

@A330
SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 38
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 47

@A330
SERVICE BULLETIN
Appendix - 01
**CONF ALL
(1) Jacking procedure for the installation of the butt straps on the fuselage skin at FR53.3, between
STGR13 LH and STGR13 RH
(a) FIXTURE, TOOLS, TEST AND SUPPORT EQUIPMENT
ITEM
 PART NUMBER
 QTY
 DESCRIPTION
RECOMMEND
 ALTERNATIVE
2
 98F07203002000
 98F07203002001
 6
 HOIST TRIPOD
4
 98F07203000150
 98F07203000120
 1
 FR17 HOIST
FITTING
5
 98F07203000151
 98F07203000121
 1
 FR17 HOIST
FITTING
6
 98F07203000140
 98F07203000110
 1
 FR59 HOIST
FITTING
7
 98F07203000141
 98F07203000111
 1
 FR59 HOIST
FITTING
8
 98F07203000142
 98F07203000126
 1
 FR76 HOIST
FITTING
9
 98F07203000143
 98F07203000127
 1
 FR76 HOIST
FITTING
11
 343A160KN2
 1
 LOAD CELL
12
 343A1MN3
 2
 LOAD CELL
13
 343A63KN2
 3
 LOAD CELL
14
 343A100KN2
 4
 LOAD CELL
15
 98A07003906200
 8
 LOAD CELL
ADAPTOR
16
 98A07003912200
 2
 LOAD CELL
ADAPTOR
17
 98A07003907200
 7
 LOAD CELL
ADAPTOR
18
 98A07003907201
 2
 LOAD CELL
ADAPTOR
20
 98A07003907202
 1
 LOAD CELL
ADAPTOR
Refer to Fig. A-FABAA
NOTE
: For Main Jack, Front Jack and Safety Jack, use your own standard tool or
refer to SRM 51-51-00.
(b) AIRCRAFT CONFIGURATION
- This jacking procedure is only applicable to the configuration below: The aircraft without :
. Fuel (except undrainable fuel)
. Payload
. Water (potable)
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 48

@A330
SERVICE BULLETIN
Appendix - 01
. Baggage containers
. Pallets
. Emergency equipment
. Catering
. Documents and aircraft tool package.
- For the remaining aircraft configuration :
. Refer to Fig. A-FAAAA
NOTE
 (1)
: If the aircraft configuration is not the same as the configuration above, contact
AIRBUS.
NOTE
 (2)
: If you do other tasks on the aircraft at the same time, contact AIRBUS.
(c) JACKING PROCEDURE
1
 Obey the general jacking instructions, (Refer to SRM 51-51-00).
2
 Lift the aircraft on the front, main and safety jacks shown in Fig. A-FACAA
 , (Refer to
AMM 07-11-00, Page Block 201).
3
 Install the additional jacking equipment at FR17, FR59 and FR76 (Refer to Fig. A-
FACAA
).
4
 Apply the loads to the jacks at FR17, FR59 and FR76, one step after the other
Refer to Fig. A-FACAA
a
 Gradually apply the loads shown in step 1 to the jacks at FR17, FR59 and FR76.
Wait until the loads on the jacks become stable and make sure that they are within
a tolerance of +/- 10 percent. Make sure that the safety jack at FR87 is in contact
without load.
b
 Continue the same procedure as above to apply the loads shown in step 2, then
step 3 and step 4.
NOTE
: When the loads given in step 4 are stable within a tolerance of
+/- 10 percent on the jacks at FR17, FR59 and FR76, you can
do the procedure given in ACCOMPLISHMENT INSTRUCTIONS,
paragraph B.
(d) CLOSE-UP
1
 Gradually decrease the loads one step after the other, from step 4 to zero on the jacks
at FR17, FR59 and FR76 (Refer to Fig. A-FACAA
).
2
 Remove the jacks at FR17, FR59 and FR76.
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 49

@A330
SERVICE BULLETIN
Appendix - 01
3
 Lower the aircraft and remove the front, main and safety jacks, (Refer to AMM 07-11-00,
Page Block 201).
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 3
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 50

@A330
SERVICE BULLETIN
Appendix - 01
**CONF ALL
X
X
X
X
FUSELAGE
AIRCRAFT CONFIGURATION FOR JACKING:
X
X
X
X
X
X
X
X
INSTALLED REMOVED
X
X
X
X
X
INSTALLED REMOVED
NOSE LANDING GEAR
L/H MAIN LANDING GEAR
R/H MAIN LANDING GEAR
LANDING GEARS
MOVABLE ELEMENTS
X
X
X
INSTALLED REMOVED
X
L/H WING
INSTALLED REMOVED
X
X
INSTALLED REMOVED
R/H WING
X
X
INSTALLED REMOVED
ENGINES
L/H ENGINE
R/H ENGINE
PYLONS
L/H PYLON
R/H PYLON
FUEL
O
O
O
EXCEPT UNDRAINABLE FUEL
EQUIPEMENT/FURNISHING INSTALLED REMOVED
X
X
X
X
X
X
X
X
X
X
X
HORIZONTAL STABILIZER
VERTICAL STABILIZER
L/H PAX DOOR 1
R/H PAX DOOR 1
L/H PAX DOOR 2
R/H PAX DOOR 2
L/H PAX DOOR 3
R/H PAX DOOR 3
L/H PAX DOOR 4
R/H PAX DOOR 4
FWD CARGO DOOR
AFT CARGO DOOR
BULK CARGO DOOR
APU
CREW REST X
L/H WINGLET
L/H SLATS
L/H FLAPS
L/H SPOILERS
L/H AILERONS X
X
X
X
X
X
X
X
INSTALLED REMOVED
L/H ENGINE
R/H ENGINE
THRUST REVERSERS
L/H WING TANKS
R/H WING TANKS
TRIM TANKS
FUSELAGE SECTION 11
FUSELAGE SECTION 12
FUSELAGE SECTION 13
FUSELAGE SECTION 14
FUSELAGE SECTION 14A
FUSELAGE SECTION 15
FUSELAGE SECTION 16
FUSELAGE SECTION 17
FUSELAGE SECTION 18
FUSELAGE SECTION 19
FUSELAGE SECTION 19.1
R/H WINGLET
R/H SLATS
R/H FLAPS
R/H SPOILERS
R/H AILERONS
G_SB_533127_5_AAAA_01_01
Figure A-FAAAA - Sheet 01
Aircraft Configuration for Jacking
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 4
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 51

@A330
SERVICE BULLETIN
Appendix - 01
**CONF ALL
2
5
14
15
17
11
15
20
2
4
14
15
17
12
16
18
12
16
18
2
8
14
15
17
2
9
14
15
17
13
15
17
ITEM
2
DESIGNATION PART NUMBER
HOIST TRIPOD6
4 1 FR17 HOIST FITTING
5 1 FR17 HOIST FITTING
6 1 FR59 HOIST FITTING
7 1 FR59 HOIST FITTING
8 1 FR76 HOIST FITTING
9 1 FR76 HOIST FITTING
11 1 LOAD CELL
12 2 LOAD CELL
13 343A63KN2LOAD CELL
14 343A100KN2LOAD CELL
15 8
16 2
17 7
18 2
20 1
QUANTITY
343A160KN2
LOAD CELL ADAPTOR
LOAD CELL ADAPTOR
LOAD CELL ADAPTOR
LOAD CELL ADAPTOR
LOAD CELL ADAPTOR
2
7
13
15
17
2
6
13
15
17
98F07203002000
98F07203000120
98F07203000121
98F07203000110
98F07203000111
98A07003906200
98A07003912200
98A07003907200
98A07003907202
98A07003907201
98F07203000126
98F07203000127
343A1MN3
3
4
G_SB_533127_5_ABAA_01_01
Figure A-FABAA - Sheet 01
Jacking Equipment
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 5
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 52

@A330
SERVICE BULLETIN
Appendix - 01
**CONF ALL
JACKING POINTS
MAX.
PERMIS.
LOADS STEP 1 STEP 2 STEP 3 STEP 4
% OF
TOTAL
LOADS
APPLIED LOADS (Kg)
+/− 10%
FR87 (SAFETY JACK)
     (CONTACT ONLY)
FR17 (2 JACKS)
     (SEE NOTE 2)
FR59 (2 JACKS)
     (SEE NOTE 2)
FR76 (2 JACKS)
     (SEE NOTE 2)
4590 00 00 0
16820 2800 5610 8410 11210
8050 530 1060 1580 2110 2
15190 3450 6900 10350 13800 12
WITH TWO JACKS, THE LOAD FOR EACH JACK IS THE APPLIED
LOAD DIVIDED BY TWO).
FRONT JACK
LH MAIN JACK
RH MAIN JACK
MAX.
PERMIS.
LOADS
12540
75130
75130
FOR INFORMATION
FOR INFORMATION
FOR INFORMATION
REMAINING LOADS (Kg)SUPPORT POINTS
11200
38100
38100
10
33
33
CORRESPONDING WEIGHT OF THE AIRCRAFT:   114400 (INCLUDING BALLASTS IF ANY)
10
ACTUAL
LOADS
(SEE NOTE 1)
NOTE 2: APPLIED LOADS ARE TOTAL LOADS PER STATION (FOR A STATION
NOTE 1: TO INSTALL KIT A01 (REFER TO ACCOMPLISHEMENT INSTRUCTION,
PARAGRAPH B.), MAKE SURE THAT THE ACTUAL LOADS ARE
IN A TOLERANCE OF +/− 10% OF THE VALUES GIVEN IN STEP 4.
G_SB_533127_5_ACAA_01_01
Figure A-FACAA - Sheet 01
Jacking Procedure
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 6
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 53

@A330
SERVICE BULLETIN
Appendix - 02
**CONF ALL
Refer to the subsequent Gantt Chart for the detail concerning the elapsed time assumptions.
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 54

@A330
SERVICE BULLETIN
Appendix - 02
**CONF ALL
ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A330−53−3127
SB ELAPSED TIME
(HOURS)
GET ACCESS
MH ET/S
TOTAL MANHOURS
SB ELAPSED TIME
314.50
56.25
STEPS
66.00 11.00
10 15 600
TEST 3.00 1.50
CLOSE−UP 66.00 11.00
MH
ET/S:
PER
MANHOURS
ELAPSED TIME PER STEP
NUMBER OF PERSONS
01
02
THIS CHART IS ONLY A PROPOSAL.
OPERATORS MAY DETERMINE THAT ANOTHER WAY
TO DO THE WORK IS MORE SUITABLE FOR THEM.
MANHOURS GIVEN IN VENDOR SERVICE BULLETINS
ARE NOT REFLECTED IN THIS GANTT CHART.
01
02
NOTES:
PER
6
2
6
:
:
INSTALL THE BUTT STRAP AT FR53.3 57.00 14.254
57.00 14.254
57.00 14.254
PAINT THE AREA MODIFIED 4.50 2.252
APPLY SEALANT
G_SB_533127_5_ADAA_01_01
BETWEEN LH AND RH STRG5
INSTALL THE BUTT STRAP AT FR53.3
BETWEEN LH STGR5 AND LH STRG13
INSTALL THE BUTT STRAP AT FR53.3
BETWEEN RH STGR5 AND RH STRG13
4.00 2.002
5 20 25 30 40 45 50 35 55
Figure A-FADAA - Sheet 01
Gantt Chart
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 55

@A330
SERVICE BULLETIN
REPORTING SHEET
TITLE: FUSELAGE - CENTER FUSELAG E - CIRCUMFERENTIAL JOINT FRAME
53.3, STGR 13 LH TO STGR 13 RH - FATIGUE LIFE IMPROVEMENT
MODIFICATION No.: 49403S16334
Please complete the appropriate item (A or B):
A - SB WILL BE
 embodied YES/NO (if NO please comment)
If YES, aircraft concer ned (as per SB effectivity by default) and planned dates (month/year) of
embodiment:
B - SB HAS BEEN
 embodied on aircraft:
Operator comments:
From Airline:
Name/Title:
Signature: Date:
If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to
next normal revision or prior to SB embodiment, please indicate required service(s):
Either: Modification Operational Impact (MOI), if available YES/NO
Or : Intermediate revision YES/NO
Important Information:
 This SB will only be incorporated in your maintenance and operational
documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With
the next feasible revision, this will result in
- Updating of maintenance documentation to show pre and post SB data.
- Updating of maintenance and operational documentation to show post SB data after embodiment.
If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically
include them in the manual revisions. Refer to SIL 00-037 for detailed information.
Please return this completed sheet to:
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX FRANCE
Attn: SDC32 Technical Data and Documentation Services
F A X :( + 3 3 )56 19 32 80 6
e-mail: sb.reporting@airbus.com
or via your Resident Customer Support Office.
Alternatively, SB lists via letters or fax are also accepted.
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 56

@A330
SERVICE BULLETIN
QUALITY PERCEPTION FORM
Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data
that you provide us will be used to analyse areas of difficulties and to take corrective action to further
improve the quality of our Service Bulletins.
We thank you for the time you have taken in completing this form.
(Please rate on a scale of 1 to 4, with 4 being the highest score)
- Quality rating of this SB 4321
- Quality rating of the Accomplishment Instructions 4321
- Quality rating of the Illustrations 4321
- Is this SB easy to understand ? Y/N
If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a
short description of the issue.
Planning Material Instructions
X Effectivity X Kit content X Preparation
X Reason X List of Materials Operator Supplied X Mod/Inspection
X Manpower X Industry support X Test
X References X Re-identification X Close-Up
X Publication X Tooling X Illustrations
Comments:
Operator: Date:
Name/Title:
Please return this form to:
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX FRANCE
Attn : SEM4 Service Bulletins Management
F A X:( 3 3 )56 19 34 25 1
Or via your Resident Customer Support Office.
DATE: Oct 30/02 SERVICE BULLETIN No.: A330-53-3127
REVISION No.: 02 - Dec 07/11 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.