# @A330 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 53 

### TITLE: FUSELAGE - CENTER FUSELAGE - 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

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# @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
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# @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

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# @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

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# @A330 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft. 

# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 53 

### TITLE: FUSELAGE - CENTER FUSELAGE - 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

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# @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

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# @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

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# @A330 SERVICE BULLETIN SUMMARY

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# @A330 SERVICE BULLETIN
AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 53 

### TITLE: FUSELAGE - CENTER FUSELAGE - 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

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# @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

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# @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 TimescaleCompliance 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

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# @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 Aviation Safety Agency (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

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# @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

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# @A330 SERVICE BULLETIN

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# @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

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# @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

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# @A330 SERVICE BULLETIN (2) Tools- Fatigue Technology Incorporated (FTI) has allocated tool kit number FTIA330-53-3127-1 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

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# @A330 SERVICE BULLETIN

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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

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# @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 stowagecompartments, (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

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# @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

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# @A330 SERVICE BULLETIN

**CONF ALL

FR38 FR54

STGR5 STGR5 STGR13

STGR13 STGR5 C L A/C



### B **C 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

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# @A330 SERVICE BULLETIN

**CONF ALL

FR53.3

FWD

SYMBOL REMOVED ITEMS NEW HOLE DIAMETER NEW BOLT NEW NUT NUT BOLT PN ITEM ASNA2026V4−8 ITEM PN (1) (2) 6.310 (0.24842) 6.350 (0.25000) 2 1 ASNA2528−4 (1) 6.310 (0.24842) 6.350 (0.25000) 1 ASNA2528−4 (3) 3

FASTENERS NOT REMOVED C L A/C

STGR5 STGR4 STGR3 STGR1

STGR2

(1) 6.310 (0.24842) 6.350 (0.25000) 1 ASNA2528−4 

## 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 11 6.310 (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

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# @A330 SERVICE BULLETIN

**CONF ALL

FR53.3

STGR5

STGR6

STGR7

STGR8

STGR9 FWD

SYMBOL REMOVED ITEMS NEW HOLE DIAMETER NEW BOLT NEW NUT NUT BOLT PN ITEM ASNA2026V4−8 ITEM PN (1) (2) 6.310 (0.24842) 6.350 (0.25000) 2 1 ASNA2528−4 (1) 6.310 (0.24842) 6.350 (0.25000) 1 ASNA2528−4 (3) 3

FASTENERS NOT REMOVED 

## C

(in.) (in.) MAX. mm MIN. 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) 3 ASNA2026V4−11 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

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# @A330 SERVICE BULLETIN

**CONF ALL

FR53.3

FWD

SYMBOL REMOVED ITEMS NEW HOLE DIAMETER NEW BOLT NEW NUT NUT BOLT PN ITEM ASNA2026V4−8 ITEM PN (1) (2) 6.310 (0.24842) 6.350 (0.25000) 2 1 ASNA2528−4 (1) 6.310 (0.24842) 6.350 (0.25000) 1 ASNA2528−4 (3) 3

FASTENERS NOT REMOVED (1) 6.310 (0.24842) 6.350 (0.25000) (1) 6.310 (0.24842) 6.350 (0.25000) 1 ASNA2528−4 (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 11 6.310 (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

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# @A330 SERVICE BULLETIN

**CONF ALL

FR53.3

FWD

NUT BOLT (1) (1) =

STGR5 TO A/C C L

**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

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# @A330 SERVICE BULLETIN

**CONF ALL

STGR5 STGR5

STGR13 FR53.3 STGR12 STGR11 C L A/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**  SHIM 

### 12 **12** SHIM

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

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# @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

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# @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

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# @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

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# @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

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# @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. AFACAA). 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

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# @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

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# @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

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# @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 TRIPOD 6 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 343A63KN2 LOAD CELL 14 343A100KN2 LOAD 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

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# @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 0 0 0 00 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

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# @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

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# @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 60 0 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 14.25 4

57.00 14.25 4

57.00 14.25 4

PAINT THE AREA MODIFIED 4.50 2.25 2 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 2.00 2

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

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# @A330 SERVICE BULLETIN REPORTING SHEET 

### TITLE: FUSELAGE - CENTER FUSELAGE - 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 concerned (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 FAX: (+33) 5 61 93 28 06 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

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# @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 FAX : (33) 5 61 93 42 51 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

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