# @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 FORWARD FUSELAGE AREA AT SECTION 13 AND 14 FROM FR19 TO FR37.4 **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR None MINOR 203702D50760 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 forward fuselage area at Section 13 and 14, from Frame (FR)19 to FR22 and from FR26/28 to FR37.4. The fastener installation and condition at the affected locations are inspected by Inspection Service Bulletin No. A330-53-3202. 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.: A330-53-3216 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 533216D01R01 1 75.00 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. A330-53-3202 NOTE: - A330-53-3202 FUSELAGE - FORWARD FUSELAGE - INSPECTION FOR SUSPECTED MISSING/NON-CONFORMING FASTENERS AT SECTION 13 AND 14 FROM FR19 TO 37.4 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 533216-831-848-001: Modification TOTAL MANHOURS 9.75 ELAPSED TIME (HOURS) 9.75 APPENDICES None

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 2 6

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# @A330 SERVICE BULLETIN SUMMARY
**CONF ALL

FR20 FR37.3FR37.4 

## A FR19

Z130 STGR52LH STGR53LH

STGR43RH

STGR43LH 

## D FR21

FR21 FR22 Y1456

Y1959 Y−1456

Y−953



## B

**C** FR22 Z240 

### A **B C** 

**D E**  **F G** 

G_SB_533216_6_SAAA_01_00 Figure A-GSAAA - Sheet 01
DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 3 6

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# @A330 SERVICE BULLETIN SUMMARY
**CONF ALL

FR34 FR35 FR36 FR37

STGR25RH

FR30FR31FR32FR33 FR35FR36FR37 FR37.1 FR37.2 FR37.4FR38 FR37.3

FR30 FR29 FR28

STGR26LH

STGR33LH STGR34LH FR34

STGR24RH 

## E

**F**
**G** STGR41RH STGR42RH

G_SB_533216_6_SAAA_02_01 Figure A-GSAAA - Sheet 02
DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 4 6

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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 FORWARD FUSELAGE AREA AT SECTION 13 AND 14 FROM FR19 TO FR37.4 MODIFICATION No.: 203702D50760 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.: A330-53-3216 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 533216D01R01 1 Consumable CMLD01 As required B. CONCURRENT REQUIREMENTS Service Bulletin(s) to be accomplished previously or simultaneously: Service Bulletin No. A330-53-3202 NOTE: - A330-53-3202 FUSELAGE - FORWARD FUSELAGE - INSPECTION FOR SUSPECTED MISSING/NON-CONFORMING FASTENERS AT SECTION 13 AND 14 FROM FR19 TO 37.4 C. REASON (1) History Prior to delivery of an A330-200F aircraft, fasteners were found missing at some locations in the forward fuselage area at Section 13 and 14, from Frame (FR)19 to FR22 and from FR26/28 to FR37.4.

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 2 6

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# @A330 SERVICE BULLETIN (2) Objective/Action The fastener installation and condition at the affected locations are inspected by Inspection Service Bulletin No. A330-53-3202. In the event of findings at that inspection, this Modification Service Bulletin details the procedure to install the correct fasteners at the identified locations. (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 533216-831-848-001: Modification (1) Install the Fasteners at FR19, between STGR52/STGR53 LH (2) Install the Fasteners at FR20 and STGR43 LH (3) Install the Fasteners between FR21 and FR22 LH (4) Install the Fasteners between FR21 and FR22 RH (5) Install the Fastener at FR26/28 and STGR26 LH (6) Install the Fasteners at FR30 between STGR33/STGR34 LH (7) Install the Fasteners from FR30 thru FR37.1, FR37.3 and FR37.4 between STGR41/42 RH (8) Install the Fasteners at FR35 between STGR24/STGR25 RH (9) Install the Fasteners at FR37.3 and STGR44 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 after Inspection Service Bulletin No. A330-53-3202.
DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 3 6

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# @A330 SERVICE BULLETIN Accomplishment of this Service Bulletin is recommended at the earliest opportunity where manpower and facilities are available. F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. Task 533216-831-848-001: Modification Get Access 3.50 On Aircraft Install the Fasteners at FR19, between STGR52/STGR53 LH 0.25 Install the Fasteners at FR20 and STGR43 LH 0.50 Install the Fasteners between FR21 and FR22 LH 0.25 Install the Fasteners between FR21 and FR22 RH 0.25 Install the Fastener at FR26/28 and STGR26 LH 0.25 Install the Fasteners at FR30 between STGR33/STGR34 LH 0.25 Install the Fasteners from FR30 thru FR37.1, FR37.3 and FR37.4 between STGR41/42 RH 0.50 Install the Fasteners at FR35 between STGR24/STGR25 RH 0.25 Install the Fasteners at FR37.3 and STGR44 RH 0.25 Close-Up 3.50 TOTAL MANHOURS 9.75 ELAPSED TIME (HOURS) 9.75 H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 4 6

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# @A330 SERVICE BULLETIN
J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53 12-34-24 20-21-11 25-23-43 25-52-00 25-80-00 52-31-00 52-80-00 53-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Service Bulletin (SB) A330-53-3202 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.: A330-53-3216 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 533216D01R01 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 533216D01R01 Cost 75.00 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 533216D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 DAN5-6-4 11 PIN 2 DAN6-6-3 10 PIN 3 DAN6-6-4 3 PIN 4 EN6081D4-10 8 RIVET DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 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 EN6081D5-20 4 RIVET 6 EN6081D6-20 6 RIVET 7 NSA5075-6 24 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.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 8 6

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# @A330 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 533216-831-848-001 - 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 130 240 Access Door 821 831 Panel 131DF 131NG 132DF 132FG 132HG 132KG 132NX 242DW 242EW 242FW 242GW Manpower TOTAL MANHOURS 9.75 ELAPSED TIME (HOURS) 9.75 DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 9 6

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# @A330 SERVICE BULLETIN
A. GENERAL (1) Subtask 533216-910-201-001 - 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.: A330-53-3216 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 533216-839-201-001 - 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 533216-941-201-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 130 Access Door 821 Panel 131DF, Panel 131NG, Panel 132DF, Panel 132HG, Panel 132KG, Panel 132FG, Panel 132NX 240 Access Door 831 Panel 242DW, Panel 242EW, Panel 242FW, Panel 242GW Manpower Resources Skills NON SPECIFIC DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 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 25-23-43-000-802 Task 25-52-00-000-801 Task 25-80-00-000-801 52-31-00, Page Block 001 Task 53-00-00-000-802 (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 FWD cargo-compartment door 821. (d) Open the FWD cargo-compartment door 821, refer to AMM 52-31-00, Page Block 001. (e) In the Main-Deck cargo-compartment, at Frame 35 RH, remove the lining panels 242DW, 242EW, 242FW, and 242GW, refer to AMM Task 25-23-43-000-802. (f) In the FWD cargo-compartment, remove the floor panels 131NG, 131DF, 132DF, 132FG, 132HG and 132KG, refer to AMM Task 53-00-00-000-802. (g) In the FWD cargo-compartment, remove the sidewall panel 132NX, refer to AMM Task 25-52-00-000-801. (h) 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.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 12 6

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# @A330 SERVICE BULLETIN
C. PROCEDURE (1) Subtask 533216-831-201-001 - Install the Fasteners at FR19, between STGR52/STGR53 LH Work Zones and Access Panels Zone Access/Work location 130 Access Door 821 Panel 131NG Work location Frame 19 from Stringer 52LH to Stringer 53LH Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 533216D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 DAN6-6-4 2 PIN 7 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-GBAAA Installation of fasteners at FR19, between STGR52/STGR53 LH Sheet 01
(a) Install the fasteners at FR19, between STGR52/STGR53 LH. 1 As shown in Fig. A-GBAAA Sheet 01: a Mark the fastener hole positions and pilot drill the fastener holes to 2.5 mm (0.0984 in.) diameter in the structure. b Open the fastener holes to between 4.78 mm and 4.821 mm (0.1882 in. and 0.1898 in.) diameter and countersink.

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 13 6

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# @A330 SERVICE BULLETIN
2 As shown in Fig. A-GBAAA Sheet 01, wet install: 2 Pin DAN6-6-4 Item 3 2 Collar NSA5075-6 Item 7 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. (2) Subtask 533216-831-202-001 - Install the Fasteners at FR20 and STGR43 LH Work Zones and Access Panels Zone Access/Work location 130 Access Door 821 Panel 131NG Work location Frame 20 Stringer 43LH Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 533216D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 6 EN6081D6-20 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
References Structural Repair Manual (SRM) 51-75-12 Fig. A-GBBAA Installation of fasteners at FR20 and STGR43 LH Sheet 01 Sheet 02

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 14 6

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# @A330 SERVICE BULLETIN (a) Install the fasteners at FR20 and STGR43 LH. 1 As shown in Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02, if no fasteners were installed in the structure at this location: a Transfer drill the pilot holes to 2.5 mm (0.0984 in.) diameter in the structure. b Open the fastener holes to between 4.85 mm and 4.95 mm (0.191 in. to 0.195 in.) diameter. 2 As shown in Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02, if fasteners of 4.0 mm (0.189 in.) were installed in the structure at this location: a Measure the fastener hole size. b Open the fastener holes to between 4.85 mm and 4.95 mm (0.191 in. to 0.195 in.) diameter in the structure. 3 As shown in Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02, wet install: 6 Rivet EN6081D6-20 Item 6 with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

4 Apply surface protection to the fasteners which you have installed in accordance with SRM 51-75-12. (3) Subtask 533216-831-203-001 - Install the Fasteners between FR21 and FR22 LH Work Zones and Access Panels Zone Access/Work location 130 Access Door 821 Panel 131DF Work location from Frame 21 to Frame 22 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 533216D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 EN6081D4-10 4 RIVET DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 15 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 fasteners at FR21 and FR22 LH and RH Sheet 01
(a) Install the fasteners between FR21 and FR22 LH. 1 As shown in Fig. A-GBCAA 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 3.25 mm and 3.35 mm (0.128 in. and 0.132 in.) diameter. 2 As shown in Fig. A-GBCAA Sheet 01, wet install: 4 Rivet EN6081D4-10 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. (4) Subtask 533216-831-209-001 - Install the Fasteners between FR21 and FR22 RH Work Zones and Access Panels Zone Access/Work location 130 Access Door 821 Panel 132DF Work location from Frame 21 to Frame 22 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 16 6

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# @A330 SERVICE BULLETIN Material necessary to do the job Kit 533216D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 EN6081D4-10 4 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-GBCAA Installation of fasteners at FR21 and FR22 LH and RH Sheet 01
(a) Install the fasteners between FR21 and FR22 RH. 1 As shown in Fig. A-GBCAA 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 3.25 mm and 3.35 mm (0.128 in. and 0.132 in.) diameter. 2 As shown in Fig. A-GBCAA Sheet 01, wet install: 4 Rivet EN6081D4-10 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. (5) Subtask 533216-831-204-001 - Install the Fastener at FR26/28 and STGR26 LH Work Zones and Access Panels Zone Access/Work location 130 Access Door 821 Work location Frame 26/28 Stringer 26LH

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 17 6

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# @A330 SERVICE BULLETIN Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 533216D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 DAN6-6-4 1 PIN 7 NSA5075-6 1 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-GBDAA Installation of fasteners at FR26/28 and STGR26 LH Sheet 01
(a) Install the fastener at FR26/28 and STGR26 LH. 1 As shown in Fig. A-GBDAA Sheet 01: NOTE: If the hole is in the surrounding structure only, you must transfer drill the holes to the attaching parts. a Measure the existing fastener hole size. b If the fastener hole is not at the correct size, open the hole to between 4.78 mm and 4.821 mm (0.1882 in. and 0.1898 in.) diameter and countersink. 2 As shown in Fig. A-GBDAA Sheet 01, wet install: 1 Pin DAN6-6-4 Item 3 1 Collar NSA5075-6 Item 7 with: Polysulfide Sealant - General Purpose Brushable 06AAA1 As required

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 18 6

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# @A330 SERVICE BULLETIN
3 Apply surface protection to the fasteners which you have installed in accordance with SRM 51-75-12. (6) Subtask 533216-831-205-001 - Install the Fasteners at FR30 between STGR33/STGR34 LH Work Zones and Access Panels Zone Access/Work location 130 Access Door 821 Panel 132NX Work location Frame 30 from Stringer 33LH to Stringer 34LH Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 533216D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 DAN6-6-3 10 PIN 7 NSA5075-6 10 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-GBEAA Installation of fasteners at FR30 between STGR33/STGR34 LH Sheet 01
(a) Install the fasteners at FR30 between STGR33/STGR34 LH. 1 As shown in Fig. A-GBEAA 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 4.78 mm and 4.821 mm (0.1882 in. and 0.1898 in.) diameter and countersink.

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 19 6

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# @A330 SERVICE BULLETIN
2 As shown in Fig. A-GBEAA Sheet 01, wet install: 10 Pin DAN6-6-3 Item 2 10 Collar NSA5075-6 Item 7 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. (7) Subtask 533216-831-206-001 - Install the Fasteners from FR30 thru FR37.1, FR37.3 and FR37.4 between STGR41/42 RH Work Zones and Access Panels Zone Access/Work location 130 Access Door 821 Panel 132FG, Panel 132HG, Panel 132KG Work location from Frame 30 to Frame 37.1 Frame 37.3 Frame 37.4 from Stringer 41RH to Stringer 42RH Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 533216D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 DAN5-6-4 11 PIN 7 NSA5075-6 11 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
DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 20 6

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# @A330 SERVICE BULLETIN
References Fig. A-GBFAA Installation of fasteners at FR30 thru FR37.1, FR37.3 and FR37.4 between STGR 41/42 RH Sheet 01 Sheet 02
(a) Install the fasteners from FR30 thru FR37.1, FR37.3 and FR37.4 between STGR41/42 RH. Refer to 1 As shown in Fig. A-GBFAA Sheet 01 and Fig. A-GBFAA Sheet 02: a Transfer drill the pilot holes to 2.5 mm (0.0984 in.) diameter in the structure. b Open the pilot holes to between 4.78 mm and 4.821 mm (0.1882 in. and 0.1898 in.) diameter. 2 As shown in Fig. A-GBFAA Sheet 01 and Fig. A-GBFAA Sheet 02, wet install: 11 Pin DAN5-6-4 Item 1 11 Collar NSA5075-6 Item 7 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 533216-831-207-001 - Install the Fasteners at FR35 between STGR24/STGR25 RH Work Zones and Access Panels Zone Access/Work location 240 Access Door 831 Panel 242DW, Panel 242EW, Panel 242FW, Panel 242GW Work location Frame 35 from Stringer 24RH to Stringer 25RH Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME
DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 21 6

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

# @A330 SERVICE BULLETIN Material necessary to do the job Kit 533216D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 5 EN6081D5-20 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-GBGAA Installation of fasteners at FR35 between STGR24/STGR25 RH Sheet 01 Sheet 02 (a) Install the fasteners at FR35 between STGR24/25 RH. 1 As shown in Fig. A-GBGAA Sheet 01 and Fig. A-GBGAA Sheet 02: a Transfer drill the pilot holes to 2.5 mm (0.0984 in.) diameter in the structure. b Open the pilot holes to between 4.06 mm and 4.17 mm (0.160 in. and 0.164 in.) diameter. 2 As shown in Fig. A-GBGAA Sheet 01 and Fig. A-GBGAA Sheet 02, wet install: 2 Rivet EN6081D5-20 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. (9) Subtask 533216-831-208-001 - Install the Fasteners at FR37.3 and STGR44 RH Work Zones and Access Panels Zone Access/Work location 130 Access Door 821 Panel 132KG Work location Frame 37.3 Stringer 44RH
DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 22 6

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

# @A330 SERVICE BULLETIN Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 533216D01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 5 EN6081D5-20 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-GBHAA Installation of fasteners at FR37.3 and STGR44 RH Sheet 01 Sheet 02 (a) Install the fasteners at FR37.4 and STGR44 RH. 1 As shown in Fig. A-GBHAA Sheet 01 and Fig. A-GBHAA Sheet 02, if no fasteners were installed in the structure at this location: a Transfer drill the pilot holes to 2.5 mm (0.0984 in.) diameter in the structure. b Open the pilot 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 and Fig. A-GBHAA Sheet 02, if 3.2 mm (0.126 in.) diameter fastener were installed in the structure at this location: a Measure the existing fastener hole sizes. b Open the holes to between 4.06 mm and 4.17 mm (0.160 in. and 0.164 in.) diameter. 3 As shown in Fig. A-GBHAA Sheet 01 and Fig. A-GBHAA Sheet 02, wet install: 2 Rivet EN6081D5-20 Item 5 with:
DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 23 6

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

4 Apply surface protection to the fasteners which you have installed in accordance with SRM 51-75-12. D. TEST None E. CLOSE-UP (1) Subtask 533216-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 130 Access Door 821 Panel 131DF, Panel 131NG, Panel 132DF, Panel 132HG, Panel 132KG, Panel 132FG, Panel 132NX 240 Access Door 831 Panel 242DW, Panel 242EW, Panel 242FW, Panel 242GW Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 25-23-43-400-802 Task 25-52-00-400-801 52-31-00, Page Block 001 Task 52-80-00-400-801 Task 53-00-00-400-802 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the insulation blankets that you removed to get access to the work areas, refer to AMM Task 52-80-00-400-801. (c) In the Main-Deck Cargo Compartment (MDCC), at Frame 35 RH, install the lining panels 242DW, 242EW, 242FW, and 242GW, refer to AMM Task 25-23-43-400-802. (d) In the FWD cargo-compartment, install the sidewall panel 132NX, refer to AMM Task 25-52-00-400-801. (e) In the FWD cargo-compartment, install the floor panels 131NG, 131DF, 132DF, 132FG, 132HG and 132KG, refer to AMM Task 53-00-00-400-802. (f) Close the FWD cargo-compartment door 821, refer to AMM 52-31-00, Page Block 001. DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 24 6

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# @A330 SERVICE BULLETIN (g) Remove the access platform(s).

DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 25 6

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# @A330 SERVICE BULLETIN

**CONF ALL



### A



## A FR19 Z130 

### B

STGR52LH

STGR53LH STGR52LH

STGR53LH

STGR54LH

**FWD** 

## B FR19 11.8 mm (0.404 in) ± 0.2 mm (0.007 in) 24 mm (0.994 in) ± 0.2 mm (0.007 in) 11.8 mm (0.404 in) ± 0.2 mm (0.007 in) 24 mm (0.994 in) ± 0.2 mm (0.007 in) 3 7 3 7

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

01

G_SB_533216_6_BAAA_01_01 Figure A-GBAAA - Sheet 01 Installation of fasteners at FR19, between STGR52/STGR53 LH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 26 6

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# @A330 SERVICE BULLETIN

**CONF ALL

Z130

FR20 FR25 

### A

**B**


## A

STGR44LH STGR43LH

STGR50LH FR20



## B **C**

G_SB_533216_6_BBAA_01_00 Figure A-GBBAA - Sheet 01 Installation of fasteners at FR20 and STGR43 LH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 27 6

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# @A330 SERVICE BULLETIN

**CONF ALL

FR20

STGR43LH

STGR44LH 

## C VIEW LOOKING FWD INNER FLANGE 6

6

G_SB_533216_6_BBAA_02_00 Figure A-GBBAA - Sheet 02 Installation of fasteners at FR20 and STGR43 LH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 28 6

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# @A330 SERVICE BULLETIN

**CONF ALL



### B **C A** 

Z130

TYPICAL FR20 FR21 FR22

FR21 FR22

FR21 FR22 Y1456

Y1959 Y−1456

Y−953 

## A

**B**

**C D** 

**D D** 

**D**



## D 4

G_SB_533216_6_BCAA_01_00 Figure A-GBCAA - Sheet 01 Installation of fasteners at FR21 and FR22 LH and RH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 29 6

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# @A330 SERVICE BULLETIN

**CONF ALL

Z130



## B Y2244 Y2462 Y2525.5

FR29

**FWD** FR30 FR29 STGR26LH 

### B



## A **A**

FR26/28

FR26/28 3 7

**NOTE:**AREA OF MODIFICATION G_SB_533216_6_BDAA_01_01 Figure A-GBDAA - Sheet 01 Installation of fasteners at FR26/28 and STGR26 LH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 30 6

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# @A330 SERVICE BULLETIN

**CONF ALL



## A FR32 FR31 FR30 FR29

STGR33LH Z130 

### A
STGR34LH 

### B

FR30

STGR33LH

STGR34LH

STGR35LH

VIEW LOOKING ON OUTER SKIN **FWD** 

## B 2 7 2 7

G_SB_533216_6_BEAA_01_01 Figure A-GBEAA - Sheet 01 Installation of fasteners at FR30 between STGR33/STGR34 LH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 31 6

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# @A330 SERVICE BULLETIN

**CONF ALL

Z130 

### A

FR30 FR31 FR32 FR33 FR34 FR35 FR36 FR37 FR37.1 FR37.2 FR37.4 FR38 FR37.3



## A **B**

**B B**  **B B**  **B** STGR41RH STGR42RH

G_SB_533216_6_BFAA_01_01 Figure A-GBFAA - Sheet 01 Installation of fasteners at FR30 thru FR37.1, FR37.3 and FR37.4 between STGR 41/42 RH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 32 6

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# @A330 SERVICE BULLETIN

**CONF ALL

STGR41RH

STGR42RH

STGR43RH 

### C

FR STGR41RH STGR42RH STGR43RH

**F W**  **D** TYPICAL 

## B

**C** VIEW LOOKING FWD

1 7

G_SB_533216_6_BFAA_02_00 Figure A-GBFAA - Sheet 02 Installation of fasteners at FR30 thru FR37.1, FR37.3 and FR37.4 between STGR 41/42 RH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 33 6

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# @A330 SERVICE BULLETIN

**CONF ALL

Z240

FR32 FR33 FR34 FR35 FR36 FR37

STGR11RH

STGR24RH STGR25RH FR32 FR37

STGR11RH STGR31RH 

### B

**C**



## B **A**

STGR31RH 

### A

G_SB_533216_6_BGAA_01_00 Figure A-GBGAA - Sheet 01 Installation of fasteners at FR35 between STGR24/STGR25 RH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 34 6

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# @A330 SERVICE BULLETIN

**CONF ALL

FR35

STGR24RH



## C 5

G_SB_533216_6_BGAA_02_00 Figure A-GBGAA - Sheet 02 Installation of fasteners at FR35 between STGR24/STGR25 RH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 35 6

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# @A330 SERVICE BULLETIN

**CONF ALL

Z130 

### A



## A FR36 FR37.3FR37.4 

### B

STGR44RH

STGR50RH FR37.3



### C



## B

G_SB_533216_6_BHAA_01_00 Figure A-GBHAA - Sheet 01 Installation of fasteners at FR37.3 and STGR44 RH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 36 6

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# @A330 SERVICE BULLETIN

**CONF ALL

FR37.3

STGR44RH

VIEW LOOKING FWD 

## C 5

G_SB_533216_6_BHAA_02_00 Figure A-GBHAA - Sheet 02 Installation of fasteners at FR37.3 and STGR44 RH DATE: May 06/14 SERVICE BULLETIN No.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 37 6

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# @A330 SERVICE BULLETIN REPORTING SHEET 

### TITLE: FUSELAGE - GENERAL - IMPROVE RIVETING IN FORWARD FUSELAGE AREA AT SECTION 13 AND 14 FROM FR19 TO FR37.4 MODIFICATION No.: 203702D50760 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.: A330-53-3216 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.: A330-53-3216 REVISION No.: 00 - May 06/14 Page: 1 6

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