# @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. ATA SYSTEM: 53 

### TITLE: FUSELAGE - GENERAL - IMPROVE RIVETING IN REAR FUSELAGE AREA AT SECTION 17 FROM FR57 TO FR59 **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR None MINOR 203702D50759 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 Prior to delivery of an A330-200F aircraft, fasteners were found missing at some locations in the rear fuselage area at Section 17, from Frame (FR)57 to FR59. The fastener installation and condition at the affected locations are inspected by Inspection Service Bulletin No. A330-53-3212. In the event of findings at that inspection, this Modification Service Bulletin details the procedure to install the correct fasteners at the identified locations. Accomplishment of this Service Bulletin will make sure that the aircraft will be restored to the original approved design integrity. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB YES POTENTIAL AD NO 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 recommended to be accomplished to prevent significant operational disruptions.

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 1 6

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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 533217D01R01 1 50.00 Fasteners EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

CRK ETD MAS MNB QTR THY TPA YZR CONCURRENT REQUIREMENTS Service Bulletin(s) to be accomplished previously or simultaneously: Service Bulletin No. A330-53-3212 NOTE: - A330-53-3212 FUSELAGE - FORWARD FUSELAGE - INSPECTION FOR SUSPECTED MISSING/NON-CONFORMING FASTENERS AT SECTION 17 FROM FR57 TO FR59 REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER Task 533217-831-848-001: Modification TOTAL MANHOURS 10.00 ELAPSED TIME (HOURS) 10.00 APPENDICES None

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 2 6

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# @A330 SERVICE BULLETIN SUMMARY

**CONF ALL

Z150 

### B **A C** 
Z260

**NOTE:**MODIFICATION AREAS LH SHOWN RH SYMMETRICAL

FR60 FR59 FR58 FR57 FR56

STGR26
FR57 FR58 FR59 FR58 

## A FR60 STGR23RH STGR25RH

FR59



## B

**C** STGR40RH STGR38RH

FR58A STGR30RH STGR32RH

FR59

STGR41RH

STGR41LH

G_SB_533217_6_SAAA_01_00 Figure A-GSAAA - Sheet 01
DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 3 6

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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 ATA SYSTEM: 53 

### TITLE: FUSELAGE - GENERAL - IMPROVE RIVETING IN REAR FUSELAGE AREA AT SECTION 17 FROM FR57 TO FR59 MODIFICATION No.: 203702D50759 This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY NOTE: This modification is applicable by Service Bulletin only. NOTE: The intent of this modification is achieved in production on A330 aircraft with Manufacturer Serial Number (MSN) 1442 and subsequent through Modification Number 202674D50581. (1) Models 330-223F 330-243F (2) Effectivity by MSN 1004 1032 1051 1062 1070 1092 1115 1136 1148 1164 1175 1180 1320 1332 1344 1350 1368 1380 1386 1406 1414 1418 1428 (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: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 1 6

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# @A330 SERVICE BULLETIN
OPERATOR MSN CRK 1051 1062 1115 1320 ETD 1032 1070 1414 MAS 1136 1148 1164 1180 MNB 1332 QTR 1350 1386 1406 THY 1004 1092 1344 1418 TPA 1368 1380 1428 YZR 1175 (4) Configuration by MSN MSN CONFIGURATION 1004 1032 1051 1062 1070 1092 1115 1136 1148 1164 1175 1180 1320 1332 1344 1350 1368 1380 1386 1406 1414 1418 1428 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 533217D01R01 1 Consumable CMLD01 As required B. CONCURRENT REQUIREMENTS Service Bulletin(s) to be accomplished previously or simultaneously: Service Bulletin No. A330-53-3212 NOTE: - A330-53-3212 FUSELAGE - FORWARD FUSELAGE - INSPECTION FOR SUSPECTED MISSING/NON-CONFORMING FASTENERS AT SECTION 17 FROM FR57 TO FR59 C. REASON (1) History Prior to delivery of an A330-200F aircraft, fasteners were found missing at some locations in the rear fuselage area at Section 17, from Frame (FR)57 to FR59. (2) Objective/Action The fastener installation and condition at the affected locations are inspected by Inspection Service Bulletin No. A330-53-3212. In the event of findings at that inspection, this Modification Service Bulletin details the procedure to install the correct fasteners at the identified locations. DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 2 6

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# @A330 SERVICE BULLETIN (3) Advantages Accomplishment of this Service Bulletin will make sure that the aircraft will be restored to the original approved design integrity. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 533217-831-848-001: Modification (1) Install the Fasteners at FR57, STGR26 LH (2) Install the Fasteners at FR57, STGR26 RH (3) Install the Fasteners at FR58 to FR59, STGR38 RH (4) Install the Fasteners at FR58, STGR41 LH (5) Install the Fasteners at FR58, STGR41 RH (6) Install the Fasteners at FR58A, between STGR29 RH and STGR30 RH (7) Install the Fasteners at FR58A, between STGR31 RH and STGR33 RH (8) Install the Fasteners at FR59, STGR23 RH, STGR24 RH and STGR25 RH (9) Install the Fasteners at FR59, STGR26 LH (10) Install the Fasteners at FR59, STGR40 RH E. COMPLIANCE (1) Classification RECOMMENDED: Service Bulletin recommended to be accomplished to prevent significant operational disruptions. (2) Accomplishment Timescale Accomplishment of this Service Bulletin is to be performed, when applicable, immediately, when applicable, after inspection Service Bulletin No. A330-53-3212. Accomplishment of this Service Bulletin is recommended at the earliest opportunity where manpower and facilities are available. F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031. DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 3 6

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# @A330 SERVICE BULLETIN If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. Task 533217-831-848-001: Modification Get Access 3.50 On Aircraft Install the Fasteners at FR57, STGR26 LH 0.25 Install the Fasteners at FR57, STGR26 RH 0.25 Install the Fasteners at FR58 to FR59, STGR38 RH 0.25 Install the Fasteners at FR58, STGR41 LH 0.25 Install the Fasteners at FR58, STGR41 RH 0.25 Install the Fasteners at FR58A, between STGR29 RH and STGR30 RH 0.25 Install the Fasteners at FR58A, between STGR31 RH and STGR33 RH 0.50 Install the Fasteners at FR59, STGR23 RH, STGR24 RH and STGR25 RH 0.50 Install the Fasteners at FR59, STGR26 LH 0.25 Install the Fasteners at FR59, STGR40 RH 0.25 Close-Up 3.50 TOTAL MANHOURS 10.00 ELAPSED TIME (HOURS) 10.00 H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53 12-34-24 20-21-11 25-53-00 25-55-22 25-80-00 52-10-00 52-30-00 53-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Service Bulletin (SB) A330-53-3212 DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 4 6

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# @A330 SERVICE BULLETIN Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-40-00 51-42-00 51-43-00 51-44-11 51-46-11 51-47-00 51-75-12 K. PUBLICATION AFFECTED None L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 5 6

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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 533217D01R01 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 533217D01R01 Cost 50.00 USD Availability 30 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. B. INDUSTRY SUPPORT INFORMATION For aircraft under warranty at Jun 01/11, AIRBUS will credit the manhours indicated in this Service Bulletin at the agreed in-house warranty labor rate for claims received not later than 90 days after completion of the last affected aircraft of your fleet. For aircraft under warranty at Jun 01/11, AIRBUS will share the costs of accomplishment of this Service Bulletin by providing the kits at no charge for orders placed before Dec 31/16. C. LIST OF COMPONENTS Kit 533217D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 ASNA2025-3 2 BUSH 2 DAN5-6-3 4 PIN 3 EN6069KE5-12 2 RIVET 4 EN6069KE6-12 4 RIVET DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 7 6

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# @A330 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 5 EN6081D5-12 5 RIVET 6 EN6081D5-14 17 RIVET 7 MBBN4481-0503 2 RIVET 8 NSA5075-6 4 COLLAR 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 CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 8 6

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# @A330 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 533217-831-848-001 - Modification WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. NOTE: The accomplishment instructions of this Service Bulletin refer to procedures included in other AIRBUS documents. When the words ’refer to’ are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words ’in accordance with’ are included in the instruction, the procedure in the AIRBUS document must be used. NOTE: The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. Task Associated Data Zone 150 260 Access Door 822 831 Panel 151FC 151HW 151JW 151QW 151RW 152FC 152HW 152JW 152MW 152NW 152VK 152WK 262WW 262XW Manpower TOTAL MANHOURS 10.00 ELAPSED TIME (HOURS) 10.00
DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 9 6

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# @A330 SERVICE BULLETIN
A. GENERAL (1) Subtask 533217-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-801 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-40-00 51-42-00 51-43-00 51-44-11 51-46-11 51-47-00 51-75-12 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Materials List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (e) Remove and install fasteners in accordance with SRM 51-42-00. (f) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00. (g) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 ’Mating Part’ column. (h) Obtain fastener hole diameters and drill and de-burr data in accordance with SRM 51-44-11. (i) Obtain fastener spacing and margin data in accordance with SRM 51-47-00. (j) For the drilling of rivet holes: - Use a soft lead pencil and make marks to show the position of the rivet holes. - Make sure that you have the correct edge clearance before you drill the fastener holes. - If not shown otherwise the tolerance for the rivet hole diameter is +0.1 mm (+0.004 in.). DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 10 6

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# @A330 SERVICE BULLETIN - If not shown otherwise the tolerance for the rivet hole position is +/-0.2 mm (+/-0.007 in.). - Transfer-drill the existing holes with a pilot drill and a drill bush. - Drill new fastener holes with a pilot drill of 2.5 mm (0.0984 in.) diameter. Increase the hole diameter to the correct size for the fastener which you must install. - Deburr the holes. (k) Cut the rivets to the necessary length. (l) Countersink the fastener holes in accordance with SRM 51-46-11. (m) Apply sealant in accordance with SRM 51-24-00. (n) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (o) Renew the protective finish in accordance with SRM 51-75-12. (p) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (2) Subtask 533217-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 533217-941-201-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 150 Access Door 822 Panel 151HW, Panel 151JW, Panel 151QW, Panel 151RW, Panel 152HW, Panel 152JW, Panel 152MW, Panel 152NW, Panel 152VK, Panel 152WK, Panel 151FC, Panel 152FC 260 Access Door 831 Panel 262WW, Panel 262XW Manpower Resources Skills NON SPECIFIC DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 11 6

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# @A330 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 25-53-00-000-801 Task 25-55-22-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Task 53-00-00-000-803 (a) The following items shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear). - Engine shut down, thrust reversers closed and locked. - Aircraft in clean configuration. - Parking brake applied. - Aircraft electrical network de-energized. - Hydraulic systems depressurized. - Access to the cockpit and cabin is available. - All circuit breakers are in closed position. - All controls in NORM, AUTO or OFF position. (b) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (c) Put access platform(s) in position below the AFT cargo-compartment door 822. (d) Open the AFT cargo-compartment door 822, refer to AMM Task 52-30-00-010-801. (e) In the Main-Deck Cargo Compartment (MDCC), remove the lining panels 262WW and 262XW, refer to AMM Task 25-55-22-000-801. (f) In the AFT cargo-compartment, remove the floor panels 152VK and 152WK, refer to AMM Task 53-00-00-000-803. (g) In the AFT cargo-compartment, remove the sidewall panels 151HW, 151JW, 151QW, 151RW, 152HW, 152JW, 152MW and 152NW, refer to AMM Task 25-53-00-000-801. (h) In the AFT cargo-compartment, remove the ceiling panels 151FC and 152FC, refer to AMM Task 25-53-00-000-801. (i) Remove the insulation blankets as necessary to get access to the work areas, refer to AMM Task 25-80-00-000-801.
DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 12 6

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# @A330 SERVICE BULLETIN
C. PROCEDURE (1) Subtask 533217-831-201-001 - Install the Fasteners at FR57, STGR26 LH Work Zones and Access Panels Zone Access/Work location 150 Access Door 822 Panel 151JW, Panel 151FC Work location Frame 57 Stringer 26LH Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 533217D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 EN6069KE6-12 2 RIVET Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required
References Structural Repair Manual (SRM) 51-75-12 Fig. A-GBAAA Installation of the fasteners at FR57, STGR26 LH and RH Sheet 01
(a) Install the fasteners at FR57, STGR26 LH. 1 As shown in Fig. A-GBAAA Sheet 01: a Mark the fastener hole positions and pilot drill the holes to 2.5 mm (0.0984 in.) diameter in the structure. b Open the fastener holes to between 4.85 mm and 4.95 mm (0.191 in. and 0.195 in.) diameter and countersink. 2 As shown in Fig. A-GBAAA Sheet 01, wet install: 2 Rivet EN6069KE6-12 Item 4 with: DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 13 6

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# @A330 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in accordance with SRM 51-75-12. (2) Subtask 533217-831-209-001 - Install the Fasteners at FR57, STGR26 RH Work Zones and Access Panels Zone Access/Work location 150 Access Door 822 Panel 152FC, Panel 152JW Work location Frame 57 Stringer 26RH Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 533217D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 EN6069KE6-12 2 RIVET Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required
References Structural Repair Manual (SRM) 51-75-12 Fig. A-GBAAA Installation of the fasteners at FR57, STGR26 LH and RH Sheet 01
(a) Install the fasteners at FR57, STGR26 RH. 1 As shown in Fig. A-GBAAA Sheet 01: a Mark the fastener hole positions and pilot drill the holes to 2.5 mm (0.0984 in.) diameter in the structure. b Open the pilot holes to between 4.85 mm and 4.95 mm (0.191 in. and 0.195 in.) diameter and countersink. DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 14 6

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# @A330 SERVICE BULLETIN
2 As shown in Fig. A-GBAAA Sheet 01, wet install: 2 Rivet EN6069KE6-12 Item 4 with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in accordance with SRM 51-75-12. (3) Subtask 533217-831-202-001 - Install the Fasteners at FR58 to FR59, STGR38 RH Work Zones and Access Panels Zone Access/Work location 150 Access Door 822 Panel 152WK Work location from Frame 58 to Frame 59 Stringer 38RH Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 533217D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 ASNA2025-3 2 BUSH 7 MBBN4481-0503 2 RIVET Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required
References Structural Repair Manual (SRM) 51-75-12 Fig. A-GBBAA Installation of the fasteners at FR58 to FR59, STGR38 RH Sheet 01

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 15 6

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# @A330 SERVICE BULLETIN (a) Install the fasteners at FR58 to FR59 to STGR38 RH. 1 As shown in Fig. A-GBBAA Sheet 01: a Mark the fastener hole positions and pilot drill the holes to 2.5 mm (0.984 in.) diameter in the structure. b Open the pilot holes to between 4.85 mm and 4.95 mm (0.191 in. and 0.195 in.) diameter and countersink. 2 As shown in Fig. A-GBBAA Sheet 01, wet install: 2 Rivet MBBN4481-0503 Item 7 2 Collar ASNA2025-3 Item 1 with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in accordance with SRM 51-75-12. (4) Subtask 533217-831-203-001 - Install the Fasteners at FR58, STGR41 LH Work Zones and Access Panels Zone Access/Work location 150 Access Door 822 Panel 151HW, Panel 151QW Work location Frame 58 Stringer 41LH Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 533217D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 DAN5-6-3 2 PIN 8 NSA5075-6 2 COLLAR

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 16 6

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# @A330 SERVICE BULLETIN
Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required
References Structural Repair Manual (SRM) 51-75-12 Fig. A-GBCAA Installation of the fasteners at FR58, STGR41 LH and RH Sheet 01
(a) Install the fasteners at FR58, STGR41 LH. 1 As shown in Fig. A-GBCAA Sheet 01: a Mark the fastener hole positions and pilot drill the holes to 2.5 mm (0.0984 in.) diameter in the structure. b Open the fastener holes to between 4.780 mm and 4.821 mm (0.1882 in. and 0.1898 in.) diameter. 2 As shown in Fig. A-GBCAA Sheet 01, wet install: 2 Pin DAN5-6-3 Item 2 2 Collar NSA5075-6 Item 8 with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in accordance with SRM 51-75-12. (5) Subtask 533217-831-210-001 - Install the Fasteners at FR58, STGR41 RH Work Zones and Access Panels Zone Access/Work location 150 Access Door 822 Panel 152HW, Panel 152MW Work location Frame 58 Stringer 41RH Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 17 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN Material necessary to do the job Kit 533217D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 DAN5-6-3 2 PIN 8 NSA5075-6 2 COLLAR Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required
References Structural Repair Manual (SRM) 51-75-12 Fig. A-GBCAA Installation of the fasteners at FR58, STGR41 LH and RH Sheet 01
(a) Install the fasteners at FR58, STGR41 RH. 1 As shown in Fig. A-GBCAA Sheet 01: a Mark the fastener hole positions and pilot drill the holes to 2.5 mm (0.0984 in.) diameter in the structure. b Open the fastener holes to between 4.780 mm and 4.821 mm (0.1882 in. and 0.1898 in.) diameter. 2 As shown in Fig. A-GBCAA Sheet 01, wet install: 2 Pin DAN5-6-3 Item 2 2 Collar NSA5075-6 Item 8 with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in accordance with SRM 51-75-12.

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 18 6

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# @A330 SERVICE BULLETIN (6) Subtask 533217-831-204-001 - Install the Fasteners at FR58A, between STGR29 RH and STGR30 RH Work Zones and Access Panels Zone Access/Work location 150 Access Door 822 Panel 152MW, Panel 152NW Work location Frame 58A from Stringer 29RH to Stringer 30RH Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 533217D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 6 EN6081D5-14 3 RIVET Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required
References Structural Repair Manual (SRM) 51-75-12 Fig. A-GBDAA Installation of the fasteners at FR58A, between STGR29 RH and STGR30 RH Sheet 01
(a) Install the fasteners at FR58A, STGR29 RH to STGR30 RH. 1 As shown in Fig. A-GBDAA Sheet 01: a Transfer drill the pilot holes to 2.5 mm (0.0984 in.) diameter in the structure. b Open the fastener holes to between 4.06 mm and 4.17 mm (0.160 in. to 0.164 in.) diameter. 2 As shown in Fig. A-GBDAA Sheet 01, wet install: 3 Rivet EN6081D5-14 Item 6 with: DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 19 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in accordance with SRM 51-75-12. (7) Subtask 533217-831-205-001 - Install the Fasteners at FR58A, between STGR31 RH and STGR33 RH Work Zones and Access Panels Zone Access/Work location 150 Access Door 822 Panel 152MW, Panel 152NW Work location Frame 58A from Stringer 31RH to Stringer 33RH Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 533217D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 6 EN6081D5-14 8 RIVET Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required
References Structural Repair Manual (SRM) 51-75-12 Fig. A-GBEAA Installation of the fasteners at FR58A, between STGR31 RH and STGR33 RH Sheet 01
(a) Install the fasteners at FR58A, STGR31 RH to STGR33 RH. 1 As shown in Fig. A-GBEAA Sheet 01: a Mark the two omitted fastener hole positions and pilot drill the two holes to 2.5 mm (0.09844 in.) diameter in the structure.

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 20 6

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# @A330 SERVICE BULLETIN
b Transfer drill the six pre-existing pilot holes to 2.5 mm (0.0984 in.) diameter in the structure.
c As shown in Fig. A-GBEAA Sheet 01, open the eight pilot holes to between 4.06 mm and 4.17 mm (0.160 in. to 0.164 in.) diameter. 2 As shown in, wet install: 8 Rivet EN6081D5-14 Item 6 with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in accordance with SRM 51-75-12. (8) Subtask 533217-831-206-001 - Install the Fasteners at FR59, STGR23 RH, STGR24 RH and STGR25 RH Work Zones and Access Panels Zone Access/Work location 260 Access Door 831 Panel 262WW, Panel 262XW Work location Frame 59 Stringer 23RH Stringer 24RH Stringer 25RH Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 533217D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 6 EN6081D5-14 6 RIVET Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 21 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-75-12 Fig. A-GBFAA Installation of the fasteners at FR59, STGR23 RH, STGR24 RH and STGR25 RH Sheet 01

(a) Install the fasteners at FR59, STGR23 RH, STGR24 RH and STGR25 RH. 1 As shown in Fig. A-GBFAA Sheet 01: a Transfer drill the pilot holes to 2.5 mm (0.0984 in.) diameter in the structure. b Open the fastener holes to between 4.06 mm and 4.17 mm (0.160 in. and 0.164 in.) diameter. 2 As shown in Fig. A-GBFAA Sheet 01, wet install: 6 Rivet EN6081D5-14 Item 6 with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in accordance with SRM 51-75-12. (9) Subtask 533217-831-207-001 - Install the Fasteners at FR59, STGR26 LH Work Zones and Access Panels Zone Access/Work location 150 Access Door 822 Panel 151RW Work location Frame 59 Stringer 26LH Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 533217D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 EN6069KE5-12 2 RIVET DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 22 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN
Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required
References Structural Repair Manual (SRM) 51-75-12 Fig. A-GBGAA Installation of the fasteners at FR59, STGR26 LH Sheet 01
(a) Install the fasteners at FR59, STGR26 LH. 1 As shown in Fig. A-GBGAA Sheet 01: a Mark the hole positions and pilot drill the holes to 2.5 mm (0.984 in.) diameter in the structure. b Open the fastener holes to between 4.06 mm and 4.17 mm (0.160 in. and 0.164 in.) diameter and countersink. 2 As shown in Fig. A-GBGAA Sheet 01, wet install: 2 Rivet EN6069KE5-12 Item 3 with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in accordance with SRM 51-75-12. (10) Subtask 533217-831-208-001 - Install the Fasteners at FR59, STGR40 RH Work Zones and Access Panels Zone Access/Work location 150 Access Door 822 Panel 152VK Work location Frame 59 Stringer 40RH Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 23 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN Material necessary to do the job Kit 533217D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 5 EN6081D5-12 5 RIVET Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant - General Purpose Brushable 06AAA1 As required
References Structural Repair Manual (SRM) 51-75-12 Fig. A-GBHAA Installation of the fasteners at FR59, STGR40 RH Sheet 01
(a) Install the fasteners at FR59, STGR40 RH. 1 As shown in Fig. A-GBHAA Sheet 01: a Transfer drill the pilot holes to 2.5 mm (0.0984 in.) diameter in the structure. b Open the fastener holes to between 4.06 mm and 4.17 mm (0.160 in. and 0.164 in.) diameter. 2 As shown in Fig. A-GBHAA Sheet 01, wet install: 5 Rivet EN6081D5-12 Item 5 with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

3 Apply surface protection to the fasteners which you have installed in accordance with SRM 51-75-12. D. TEST None

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 24 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN
E. CLOSE-UP (1) Subtask 533217-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 150 Access Door 822 Panel 151HW, Panel 151JW, Panel 151QW, Panel 151RW, Panel 152HW, Panel 152JW, Panel 152MW, Panel 152NW, Panel 152VK, Panel 152WK, Panel 151FC, Panel 152FC 260 Access Door 831 Panel 262WW, Panel 262XW Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 25-53-00-400-801 Task 25-55-22-400-801 Task 25-80-00-400-001 Task 52-10-00-410-801 Task 52-30-00-410-801 Task 53-00-00-400-803 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the insulation blankets which you removed to get access to the work areas, refer to AMM Task 25-80-00-400-001. (c) In the AFT cargo-compartment, install the ceiling panels 151FC and 152FC, refer to AMM Task 25-53-00-400-801. (d) In the AFT cargo-compartment, install the sidewall panels 151HW, 151JW, 151QW, 151RW, 152HW, 152JW, 152MW and 152NW, refer to AMM Task 25-53-00-400-801. (e) In the AFT cargo-compartment, install the floor panels 152VK and 152WK, refer to AMM Task 53-00-00-400-803. (f) In the Main-Deck Cargo Compartment (MDCC), install the lining panels 262WW and 262XW, refer to AMM Task 25-55-22-400-801. (g) Close the AFT cargo-compartment door 822, refer to AMM Task 52-30-00-410-801. (h) Remove the access platform(s).

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 25 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

Z150

LH SHOWN RH SYMMETRICAL 

## A FR58 FR57 FR56 FR55 FR54



### B STGR26 

### A

FR57

VIEW LOOKING ON OUTBOARD SKIN 

## B STGR25

STGR26

STGR27

**FWD** 8.4 mm (0.330 in) ± 0.2 mm (0.007 in)

12.4 mm (0.488 in) ± 0.2 mm (0.007 in) 26.3 mm (1.035 in) ± 0.2 mm (0.007 in)

23.5 mm (0.925 in) ± 0.2 mm (0.007 in) 4

DIMENSIONS ARE GIVEN IN CASE HOLES DO NOT PRE−EXIST. **NOTE:** 01 01

G_SB_533217_6_BAAA_01_01 Figure A-GBAAA - Sheet 01 Installation of the fasteners at FR57, STGR26 LH and RH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 26 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

Z150 

### A

FR58 FR59 STGR38RH 

### B

FR58

STGR38RH

**FWD** 

## B **A**

20 mm (0.787 in) ±0.2 mm (0.007 in) 39 mm (1.535 in) ±0.2 mm (0.007 in) 10 mm (0.393 in) ±0.2 mm (0.007 in)



### C 

## C 1 7

DIMENSIONS ARE GIVEN IN CASE HOLES DO NOT PRE−EXIST. **NOTE:** 01 01

G_SB_533217_6_BBAA_01_00 Figure A-GBBAA - Sheet 01 Installation of the fasteners at FR58 to FR59, STGR38 RH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 27 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

Z150 

### A FR57 FR58 FR59



## A

STGR41

STGR42

STGR43

STGR44

STGR45 FR58

LH SHOWN RH SYMMETRICAL 

### B

**B**



## B 12 mm (0.472 in) ± 0.2 mm (0.007 in) 34 mm (1.338 in) ± 0.2 mm (0.007 in) 11 mm (0.433 in) ± 0.2 mm (0.007 in)

DIMENSIONS ARE GIVEN IF HOLES DO NOT EXIST. **NOTE:** 01 01 01 01 2 8

G_SB_533217_6_BCAA_01_01 Figure A-GBCAA - Sheet 01 Installation of the fasteners at FR58, STGR41 LH and RH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 28 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

Z150 

### A

FR58 FR59 STGR30RH 

### B

VIEW LOOKING FORWARD STGR29RH

STGR30RH

STGR31RH

STGR32RH

STGR33RH FR58A 

## B **C**

FR58A

**FWD** 

## C **A** FR58A

6

G_SB_533217_6_BDAA_01_00 Figure A-GBDAA - Sheet 01 Installation of the fasteners at FR58A, between STGR29 RH and STGR30 RH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 29 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

Z150 

### A

FR58 FR59 STGR32RH 

### B

VIEW LOOKING FORWARD STGR29RH

STGR30RH

STGR31RH

STGR32RH

STGR33RH FR58A

## B **C** FR58A

**FWD** 

## C **A** FR58A

STGR32RH 20 mm (0.787 in) ±0.2 mm (0.007 in)

10 mm (0.393 in) ±0.2 mm (0.007 in) 11.2 mm (0.440 in) ±0.2 mm (0.007 in) 6 (8 POSITIONS)

DIMENSIONS ARE GIVEN IF HOLES DO NOT EXIST. **NOTE:** 01 01

PILOT HOLE POSITIONS OMITTED, HOLE POSITIONS ARE DIMENSIONED. 02 02

02

G_SB_533217_6_BEAA_01_01 Figure A-GBEAA - Sheet 01 Installation of the fasteners at FR58A, between STGR31 RH and STGR33 RH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 30 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

VIEW LOOKING FORWARD 

## B FR59 

## C TYPICAL INSTALLATION 

## A FR59 FR60 STGR23RH STGR25RH 

### B

STGR23RH

STGR24RH

STGR25RH 

### C **C C** 

**F W**  **D** 6 

### A

Z260

G_SB_533217_6_BFAA_01_00 Figure A-GBFAA - Sheet 01 Installation of the fasteners at FR59, STGR23 RH, STGR24 RH and STGR25 RH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 31 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

Z150



## A FR62 FR61 FR60 FR59 FR58



### B STGR26LH 

### A

VIEW LOOKING ON OUTBOARD SKIN 

## B STGR27LH

**FWD** STGR26LH STGR25LH FR59

25.5 mm (1.003 in) ± 0.2 mm (0.007 in) 23.5 mm (0.925 in) ± 0.2 mm (0.007 in) 9.7 mm (0.381 in) ± 0.2 mm (0.007 in) 3 3

DIMENSIONS ARE GIVEN IF HOLES DO NOT EXIST. **NOTE:** 01 01 01

23.5 mm (0.925 in) ± 0.2 mm (0.007 in)

G_SB_533217_6_BGAA_01_01 Figure A-GBGAA - Sheet 01 Installation of the fasteners at FR59, STGR26 LH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 32 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A330 SERVICE BULLETIN

**CONF ALL

Z150 

### A

FR58 FR59 

### B



## A FR59 STGR40RH

**FWD** 

### A

**A** 

## B **A A**  VIEW LOOKING FORWARD ON STGR40RH STGR40RH 5

G_SB_533217_6_BHAA_01_00 Figure A-GBHAA - Sheet 01 Installation of the fasteners at FR59, STGR40 RH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 33 6

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# @A330 SERVICE BULLETIN REPORTING SHEET 

### TITLE: FUSELAGE - GENERAL - IMPROVE RIVETING IN REAR FUSELAGE AREA AT SECTION 17 FROM FR57 TO FR59 MODIFICATION No.: 203702D50759 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: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 1 6

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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: May 06/14 SERVICE BULLETIN No.: A330-53-3217 REVISION No.: 00 - May 06/14 Page: 1 6

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