# Airbus Service Bulletin A310-57-2096 ## Copies (2) Copies the FAA filed in AD dockets on regulations.gov, newest revision first. A newer revision may exist. - Revision 04 ("SB_A310-57-2096_r04"), 121 pages: PDF https://openairdocs.org/files/sha256/c2/f7/c2f724f3c2621e01a187c73f07b9fa921bb8adbe6bfb9f9f4bb6402af180d471; text https://openairdocs.org/service-documents/airbus/a310-57-2096/file/c2f724f3c262.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2018-0071; AD 2018-10-05 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Revision 03 ("FAA-2015-3985_SB A310-57-2096_R3"), 88 pages: PDF https://openairdocs.org/files/sha256/f8/b1/f8b150ec2c0793c711a8bdfa035b52238e28bdff4f54d8266df6fed7b5fcb66b; text https://openairdocs.org/service-documents/airbus/a310-57-2096/file/f8b150ec2c07.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2015-3985; AD 2016-23-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md) - Type: Service bulletin (Service Bulletin) - Number: A310-57-2096 - Latest revision known: A310-57-2096, Revision 04, dated December 5, 2016 (OpenAirDocs) - Page: https://openairdocs.org/service-documents/airbus/a310-57-2096 ## ADs that cite it (3) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2018-10-05](https://openairdocs.org/ad/2018-10-05.md), effective Jun 19, 2018: Revisions 01, 02, 03 and 04 - [AD 2016-23-01](https://openairdocs.org/ad/2016-23-01.md), effective Dec 15, 2016: Revisions 01, 02 and 03 - [AD 2010-04-03](https://openairdocs.org/ad/2010-04-03.md), effective Mar 19, 2010: No revision named Also cited in [3 proposed ADs](https://openairdocs.org/service-documents/airbus/a310-57-2096/proposed.md). ## Text (121 pages) Revision 04, the newest copy. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2018-0071; AD 2018-10-05 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 MANDATORY MANDATORY MANDATORY ATA SYSTEM: 57 TITLE: WINGS - INSPECTION OF WING TOP SKIN PANEL 1 AND 2 AT RIB 2 AND RIB 3 MODIFICATION No.: None This page transmits Revision No.04 of Service Bulletin No.A310-57-2096 ADDITIONAL WORK **CONF ALL No Additional work is required by this revision for aircraft inspected by any previous issue. REASON Revision No. 04 issued to add a new inspection for aircraft that are post Modification No. 13785H5762, (Service Bulletin No. A310-57-2106) for the Rib 2 area and post Modification No. 13786H5767, (Service Bulletin No. A310-57-2107) for the Rib 3 area. CHANGES The main changes of this revision are: - Delete Config. 004 - Add Figure A -GSAAB Sheet 01 - Update the Compliance Table - Update the MANPOWER tables - Add Subtasks to do a check of the Aircraft Records for the LH Wing at Rib 2 - Add Subtasks to do a check of the Aircraft Records for the RH Wing at Rib 2 - Add Subtasks to do a check of the Aircraft Records for the LH Wing at Rib 3 - Add Subtasks to do a check of the Aircraft Records for the RH Wing at Rib 3 - Add Subtasks to do a Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 for aircraft post Modification No. 13785H5762, (Service Bulletin No. A310-57-2106) DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 1 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 2 @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET - Add Subtasks to do a Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 Modification No. 13785H5762, (Service Bulletin No. A310-57-2106) - Add Subtasks to do a Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 for aircraft post Modification No. 13786H5767, (Service Bulletin No. A310-57-2107) - Add Subtasks to do a Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 for aircraft post Modification No. 13786H5767, (Service Bulletin No. A310-57-2107) - Add Figures A-G BAAB Sheet s 01 and 02 - Add Figures A-G BBAA Sheet s 01 and 02 - Add Figures A-G BBAB Sheet s 01 and 02 - Update Figures A-GFAAA Sheets 01 and 02 - Apply minor changes. FRONT MATTER WINGS - INSPECTION OF WING TOP SKIN PANEL 1 AND 2 AT RIB 2 AND RIB 3 CONFIGURATION UPDATED R SUMMARY REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES REASON UPDATED R MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE DELETED FOR APPLICABLE MSN D EFFECTIVITY OPERATOR LIST UPDATED R MANPOWER MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER DELETED FOR APPLICABLE MSN D APPENDICES APPENDICES U PDATED R Fig. A-USAAA FIGURE SOLUTION UPDATED CONFIGURATION UPDATED R Fig. A-USAAB FIGURE SOLUTION ADDED N Fig. A-USAAB Sheet 01 SHEET ADDED N PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONFIGURATION LIST UPDATED R CONF 001 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R CONF 002 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R CONF 003 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R Configuration definition CONFIGURATION DELETED D DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 2 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 3 @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Material Effectivity MATERIAL EFFECTIVITY UPDATED R MATERIAL EFFECTIVITY ADDED N MATERIAL EFFECTIVITY DELETED FOR APPLICABLE MSN D REASON Operational/Maintenance Consequences OPERATIONAL/MAINTENANCE CONSEQUENCES UPDATED R DESCRIPTION DESCRIPTION UPDATED R COMPLIANCE Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED CONFIGURATION UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED CONFIGURATION UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED CONFIGURATION UPDATED R APPROVAL APPROVAL UPDATED R MANPOWER MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER DELETED FOR APPLICABLE MSN D REFERENCES REFERENCED DOCUMENTATION DELETED FOR APPLICABLE MSN D PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED R PUBLICATIONS AFFECTED UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 572096- 832-895-001-Inspection TASK SOLUTION UPDATED NOTE UPDATED CAUTION UPDATED R Task associated data - 001 MAN HOURS UPDATED ELAPSED TIME UPDATED R Task associated data - 002 MAN HOURS UPDATED ELAPSED TIME UPDATED R Task associated data - 003 MAN HOURS UPDATED ELAPSED TIME UPDATED R Task associated data - 004 TASK ASSOCIATED DATA DELETED FOR APPLICABLE MSN D Subtask 572096-910-403-001 SUBTASK SOLUTION ADDED N Subtask 572096-839-408-001 SUBTASK SOLUTION ADDED N Subtask 572096-910-401-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-839-401-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-910-403-001 SUBTASK SOLUTION ADDED N Subtask 572096-839-408-001 SUBTASK SOLUTION ADDED N Subtask 572096-839-401-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-910-403-001 SUBTASK SOLUTION ADDED N DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 3 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 4 @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 572096-839-408-001 SUBTASK SOLUTION ADDED N Subtask 572096-839-401-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D GENERAL TOPIC CONTENT DELETED FOR APPLICABLE MSN D Subtask 572096-941-403-001 SUBTASK SOLUTION ADDED N Subtask 572096-865-404-001 SUBTASK SOLUTION ADDED N Subtask 572096-941-405-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-941-403-001 SUBTASK SOLUTION ADDED N Subtask 572096-865-404-002 SUBTASK SOLUTION ADDED N Subtask 572096-941-405-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-941-403-001 SUBTASK SOLUTION ADDED N Subtask 572096-865-404-002 SUBTASK SOLUTION ADDED N Subtask 572096-941-405-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D PREPARATION TOPIC CONTENT DELETED FOR APPLICABLE MSN D Subtask 572096-839-404-001 SUBTASK SOLUTION ADDED N Subtask 572096-839-405-001 SUBTASK SOLUTION ADDED N Subtask 572096-839-406-001 SUBTASK SOLUTION ADDED N Subtask 572096-839-407-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-401-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-402-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-403-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-404-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-405-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-406-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-407-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-403-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-832-405-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-832-404-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-832-406-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-832-409-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-832-410-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 4 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 5 @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 572096-832-408-002 SUBTASK SOLUTION UPDATED ZONE UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED LOCATION UPDATED REFERENCES UPDATED R Subtask 572096-832-412-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-413-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-414-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-415-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-407-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-839-404-002 SUBTASK SOLUTION ADDED N Subtask 572096-839-405-002 SUBTASK SOLUTION ADDED N Subtask 572096-839-406-002 SUBTASK SOLUTION ADDED N Subtask 572096-839-407-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-401-001 SUBTASK SOLUTION UPDATED LOCATION UPDATED ZONE UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED REFERENCED DOCUMENTATION UPDATED NOTE UPDATED MANPOWER RESSOURCE UPDATED REFERENCES UPDATED R Subtask 572096-832-402-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-403-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED FIGURE REFERENCE UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED NOTE UPDATED MANPOWER RESSOURCE UPDATED REFERENCES UPDATED R Subtask 572096-832-404-001 SUBTASK SOLUTION UPDATED ZONE UPDATED FIGURE REFERENCE UPDATED CONFIGURATION UPDATED NOTE UPDATED LOCATION UPDATED REFERENCES UPDATED R DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 5 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 6 @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 572096-832-405-001 SUBTASK SOLUTION UPDATED ZONE UPDATED FIGURE REFERENCE UPDATED CONFIGURATION UPDATED NOTE UPDATED LOCATION UPDATED REFERENCES UPDATED R Subtask 572096-832-406-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED FIGURE REFERENCE UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED NOTE UPDATED LOCATION UPDATED MANPOWER RESSOURCE UPDATED REFERENCES UPDATED R Subtask 572096-832-409-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-832-410-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-832-408-002 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-832-407-001 SUBTASK SOLUTION UPDATED ZONE UPDATED FIGURE REFERENCE UPDATED CONFIGURATION UPDATED NOTE UPDATED LOCATION UPDATED REFERENCES UPDATED R Subtask 572096-832-408-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-412-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-413-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-414-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-415-002 SUBTASK SOLUTION ADDED N Subtask 572096-839-404-003 SUBTASK SOLUTION ADDED N Subtask 572096-839-405-003 SUBTASK SOLUTION ADDED N Subtask 572096-839-406-003 SUBTASK SOLUTION ADDED N Subtask 572096-839-407-003 SUBTASK SOLUTION ADDED N DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 6 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 7 @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 572096-832-401-001 SUBTASK SOLUTION UPDATED LOCATION UPDATED ZONE UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED REFERENCED DOCUMENTATION UPDATED NOTE UPDATED MANPOWER RESSOURCE UPDATED REFERENCES UPDATED R Subtask 572096-832-402-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-403-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED FIGURE REFERENCE UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED NOTE UPDATED MANPOWER RESSOURCE UPDATED REFERENCES UPDATED R Subtask 572096-832-404-001 SUBTASK SOLUTION UPDATED ZONE UPDATED FIGURE REFERENCE UPDATED CONFIGURATION UPDATED NOTE UPDATED LOCATION UPDATED REFERENCES UPDATED R Subtask 572096-832-405-001 SUBTASK SOLUTION UPDATED ZONE UPDATED FIGURE REFERENCE UPDATED CONFIGURATION UPDATED NOTE UPDATED LOCATION UPDATED REFERENCES UPDATED R Subtask 572096-832-406-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED FIGURE REFERENCE UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED NOTE UPDATED LOCATION UPDATED MANPOWER RESSOURCE UPDATED REFERENCES UPDATED R Subtask 572096-832-409-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 7 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 8 @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 572096-832-410-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-832-408-002 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-832-407-001 SUBTASK SOLUTION UPDATED ZONE UPDATED FIGURE REFERENCE UPDATED CONFIGURATION UPDATED NOTE UPDATED LOCATION UPDATED REFERENCES UPDATED R Subtask 572096-832-408-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-412-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-413-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-414-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-415-002 SUBTASK SOLUTION ADDED N PROCEDURE TOPIC CONTENT DELETED FOR APPLICABLE MSN D TEST TOPIC CONTENT DELETED FOR APPLICABLE MSN D Subtask 572096-865-402-001 SUBTASK SOLUTION UPDATED R Subtask 572096-942-401-001 SUBTASK SOLUTION ADDED N Subtask 572096-865-401-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-942-402-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-865-402-002 SUBTASK SOLUTION UPDATED R Subtask 572096-942-401-001 SUBTASK SOLUTION ADDED N Subtask 572096-865-401-002 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-942-402-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-865-402-002 SUBTASK SOLUTION UPDATED R Subtask 572096-942-401-001 SUBTASK SOLUTION ADDED N Subtask 572096-865-401-002 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 572096-942-402-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D CLOSE-UP TOPIC CONTENT DELETED FOR APPLICABLE MSN D Fig. A-UBAAA FIGURE SOLUTION UPDATED CONFIGURATION UPDATED R Fig. A-UBAAB FIGURE SOLUTION ADDED N Fig. A-UBAAB Sheet 01 SHEET ADDED N Fig. A-UBAAB Sheet 02 SHEET ADDED N Fig. A-UBBAA FIGURE SOLUTION ADDED N Fig. A-UBBAA Sheet 01 SHEET ADDED N DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 8 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 9 @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Fig. A-UBBAA Sheet 02 SHEET ADDED N Fig. A-UBBAB FIGURE SOLUTION ADDED N Fig. A-UBBAB Sheet 01 SHEET ADDED N Fig. A-UBBAB Sheet 02 SHEET ADDED N Fig. A-UFAAA FIGURE SOLUTION UPDATED CONFIGURATION UPDATED R Fig. A-UFAAA Sheet 01 SHEET UPDATED R Fig. A-UFAAA Sheet 02 SHEET ADDED N Fig. A-UFAAB FIGURE SOLUTION UPDATED CONFIGURATION UPDATED R Fig. A-UFAAB Sheet 01 SHEET UPDATED R Fig. A-UFAAB Sheet 02 SHEET ADDED N Fig. A-UFAAC FIGURE SOLUTION UPDATED CONFIGURATION UPDATED R Fig. A-UFAAC Sheet 01 SHEET UPDATED R Fig. A-UFAAC Sheet 02 SHEET ADDED N Fig. A-UFB FIGURE DELETED FOR APPLICABLE MSN D Fig. A-URA FIGURE DELETED FOR APPLICABLE MSN D Fig. A-URB FIGURE DELETED FOR APPLICABLE MSN D Appendix 01 - Inspection Report APPENDIX CONTENT APPENDIX CONTENT ADDED N Fig. A-UAAAA FIGURE SOLUTION ADDED N Fig. A-UAAAA Sheet 01 SHEET ADDED N Fig. A-UABAA FIGURE SOLUTION ADDED N Fig. A-UABAA Sheet 01 SHEET ADDED N FILING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS Revision No. 02 issued to: introduce revised repeat inspection intervals change the title of Visual Inspection to Detailed Inspection (DI) include a Special Detailed Inspection (SDI) (ultrasonic phase array) update the effectivity. Revision No. 03 issued to: DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 9 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 10 @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET extend inspection area to rib 3 as a result of FAA WFD analysis add reference to NTM 57-29-01 for inspection at Rib 2 add reference to NTM 57-29-01 for inspection at Rib 3 revise figures A-UBAAA and A-USAAA add figures A-UFBAA, A-UFBAB, A-UFBAC and A-URBAA. REVISION SEQUENCE ORIGINAL: May 06/08 REVISION No. : 02 - Mar 05/14 REVISION No. : 03 - Jun 30/15 REVISION No. : 04 - Dec 05/16 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 10 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 11 @A310 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 This summary is for information only and is not approved for modification of the aircraft. MANDATORY MANDATORY MANDATORY ATA SYSTEM: 57 TITLE: WINGS - INSPECTION OF WING TOP SKIN PANEL 1 AND 2 AT RIB 2 AND RIB 3 **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES Following scheduled maintenance, an operator reported cracks around fastener holes in the wing top skin panels 1 and 2 at Rib 2 on a number of A310 aircraft. Following Widespread Fatigue Damage (WFD) analysis the inspection programme is extended to cover wing top skin panels at both Rib 2 and Rib 3 attachments. The first crack was found during the refuelling of an aircraft in February 2006 when a visible fuel stain occurred at the crack. During the subsequent repair procedure further cracks were found by rotary eddy current inspection. All the cracks were in the Rib 2 area. The Operator carried out a fleet check and a further five aircraft were found to have cracks around fastener holes in the Rib 2 area. All the cracks were located at Rib 2 (LH and RH) between Stringers 2 and 14 and emanated from the fastener holes, generally in a forward and aft direction. The crack lengths varied from between 2.50 mm (0.098in.) to 25 mm (0.98in.) and were found on aircraft having accumulated between approximately 19300 Flight Cycles (FC) and 24800 FC. This Service Bulletin revision requires repeat inspection of the top skin panels 1 and 2 at Rib 2 and Rib 3. Detailed Inspections (DI) are required between the front and rear spars. Special Detailed Inspections (SDI) using an ultrasonic phased array technique are required to detect cracks around the fastener holes between stringers 2 and 10. The SDI will enable earlier detection of cracks with a length from 1.50 mm (0.059 in.). Early detection of damage will reduce the scope of potential repair action. For those aircraft that have already been repaired, then the inspection requirements of this Service Bulletin are not applicable to the repaired area. The repaired area must be inspected in accordance with the Repair Design Approval Sheet. However the Rib 2 and Rib 3 area not covered by the repair must be inspected in accordance with this Service Bulletin. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 1 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 12 @A310 SERVICE BULLETIN SUMMARY Accomplishment of this Service Bulletin will make sure that any cracks are found in the wing top skin panels 1 and 2 along Rib 2 and Rib 3. In case of findings, the aircraft must be repaired before the next flight. A detailed damage report must be sent to AIRBUS repair group SEOE. The Operational/Maintenance Consequences of this Service Bulletin are covered by the update of the affected publications detailed in ’PLANNING INFORMATION’. 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 YES ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO NOTE (1) : Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION **CONF 001 No Material **CONF 002 No Material **CONF 003 No Material EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) : 18T 19U 40T 50W 58X 82Z 98W 99Y AFG BBC CFC DGA F2I FDX GAF I2L IRA IRM IYE K1P KAC KZU PIA QQE R1T RJA ROT RZO SGX SUD TBN THY TSC UBD UZB WHT CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 57.20.12.001 OEB None AOT None SIL None ISI None DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 2 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 13 @A310 SERVICE BULLETIN SUMMARY LINE MAINTENANCE AFFECTED No LIFE LIMIT None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 572096-832-895-001: Inspection TOTAL MANHOURS 13.00 ELAPSED TIME (HOURS) 13.00 **CONF 002 Task 572096-832-895-001: Inspection TOTAL MANHOURS 13.00 ELAPSED TIME (HOURS) 13.00 **CONF 003 Task 572096-832-895-001: Inspection TOTAL MANHOURS 13.00 ELAPSED TIME (HOURS) 13.00 APPENDICES **CONF ALL Appendix 01 - Inspection Report DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 3 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 14 @A310 SERVICE BULLETIN SUMMARY **CONF 001 Z500 Z600 NOTE: INSPECTION AREA. LH SHOWN RH SIMILAR A FRONT SPAR REAR SPARTOP SKIN PANEL 1 TOP SKIN PANEL 2 TOP SKIN PANEL 3 RIB2RIB3 A A B_SB_572096_7_SAAA_01_01 Figure A-U SAAA - S heet 01 Inspection Area DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 4 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 15 @A310 SERVICE BULLETIN SUMMARY **CONF 002 thru 003 NOTE: INSPECTION AREA. LH SHOWN RH SYMMETRICAL A FRONT SPAR REAR SPARTOP SKIN PANEL 1 A A Z500 Z600 RIB2RIB3 TOP SKIN PANEL 2 B_SB_572096_7_SAAB_01_00 Figure A-U SAAB - S heet 01 Inspection Area DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 5 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 16 @A310 SERVICE BULLETIN SUMMARY This Page Intentionally Left Blank DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 6 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 17 @A310 SERVICE BULLETIN AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 MANDATORY MANDATORY MANDATORY ATA SYSTEM: 57 TITLE: WINGS - INSPECTION OF WING TOP SKIN PANEL 1 AND 2 AT RIB 2 AND RIB 3 MODIFICATION No.: None This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY (1) Models 310-203 310-221 310-222 310-304 310-308 310-322 310-324 310-325 (2) Effectivity by MSN 0162 0230 0245 0248 0267 0278 0281 0283 0331 0356 0362 0364 0369 0378 0394 0399 0413 0418 0421-0422 0425 0431 0434 0436-0437 0439 0441 0444-0447 0449 0452 0456-0458 0467 0472-0473 0478 0480 0482-0484 0488-0492 0494-0500 0503 0519-0520 0522-0524 0526 0537 0539 0545 0547 0549-0552 0562 0564-0565 0567-0568 0571 0574 0576 0585-0588 0590-0595 0597 0599-0600 0620 0622 0624 0636 0644 0646-0649 0651 0653 0656 0658 0660-0661 0663 0667 0671-0672 0674 0676 0678 0682 0687 0689 0691 0700 0704 0706 (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 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 1 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 18 @A310 SERVICE BULLETIN OPERATOR MSN 18T 0473 19U 0399 40T 0413 50W 0498 58X 0431 82Z 0550 0551 98W 0495 99Y 0489 AFG 0496 0497 BBC 0594 0700 CFC 0425 0441 0444 0446 0482 DGA 0418 0421 0422 F2I 0491 0520 FDX 0162 0230 0245 0248 0267 0278 0281 0283 0331 0356 0362 0364 0369 0378 0394 0439 0449 0452 0456 0457 0458 0467 0492 0500 0539 0549 0552 0593 GAF 0434 0484 0503 0522 0523 I2L 0661 IRA 0436 0671 IRM 0488 0499 0524 0526 0537 0547 0564 0567 0586 0595 0620 IYE 0568 0704 K1P 0648 KAC 0647 0649 0663 KZU 0592 0622 0646 PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691 QQE 0667 R1T 0591 RJA 0445 0490 ROT 0636 0644 RZO 0571 0624 0651 SGX 0519 0562 SUD 0437 TBN 0565 THY 0478 0480 TSC 0447 0472 0483 0545 0588 0597 0599 0600 0658 UBD 0672 0674 UZB 0574 0576 0706 WHT 0494 (4) Configuration by MSN MSN CONFIGURATION 0162 0230 0245 0248 0267 0278 0281 0283 0331 0356 0362 0364 0369 0394 001 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 2 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 19 @A310 SERVICE BULLETIN MSN CONFIGURATION 0378 0399 0413 0418 0421 0422 0425 0431 0434 0436 0437 0439 0441 0444 0445 0446 0447 0449 0452 0456 0457 0458 0467 0472 0473 0478 0480 0482 0483 0484 0488 0489 0490 0491 0492 0494 0495 0496 0497 0498 0499 0500 0503 0519 0520 0522 0523 0524 0526 0537 0539 0545 0547 0549 0550 0551 0552 0562 0564 0565 0567 0568 0571 0574 0576 0585 0586 0587 0588 0590 0591 0592 0593 0594 0595 0597 0599 0600 0620 0622 0624 0636 0644 0646 0647 0648 0649 0651 0653 0656 0658 0660 0661 0663 0667 0671 0672 0674 0676 0678 0682 0687 0689 0691 0700 0704 0706 002 003 (5) Configuration definition **CONF 001 Config. 001 is applicable to A310-200 aircraft. **CONF 002 Config. 002 is applicable to A310-300 aircraft with an average flight time of 4 hours or less than 4 hours (Short Range (SR) mission). **CONF 003 Config. 003 is applicable to A310-300 aircraft with an average flight time of 4 hours or greater than 4 hours (Long Range (LR) mission). (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Consumable CMLB01 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History Following scheduled maintenance, an operator reported cracks around fastener holes in the wing top skin panels 1 and 2 at Rib 2 on a number of A310 aircraft. Following Widespread Fatigue Damage (WFD) analysis the inspection programme is extended to cover wing top skin panels at both Rib 2 and Rib 3 attachments. The first crack was found during the refuelling of an aircraft in February 2006 when a visible fuel stain occurred at the crack. During the subsequent repair procedure further cracks were found by rotary eddy current inspection. All the cracks were in the Rib 2 area. The Operator carried out a fleet check and a further five aircraft were found to have cracks around fastener holes in the Rib 2 area. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 3 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 20 @A310 SERVICE BULLETIN All the cracks were located at Rib 2 (LH and RH) between Stringers 2 and 14 and emanated from the fastener holes, generally in a forward and aft direction. The crack lengths varied from between 2.50 mm (0.098in.) to 25 mm (0.98in.) and were found on aircraft having accumulated between approximately 19300 Flight Cycles (FC) and 24800 FC. (2) Objective/Action This Service Bulletin revision requires repeat inspection of the top skin panels 1 and 2 at Rib 2 and Rib 3. Detailed Inspections (DI) are required between the front and rear spars. Special Detailed Inspections (SDI) using an ultrasonic phased array technique are required to detect cracks around the fastener holes between stringers 2 and 10. The SDI will enable earlier detection of cracks with a length from 1.50 mm (0.059 in.). Early detection of damage will reduce the scope of potential repair action. For those aircraft that have already been repaired, then the inspection requirements of this Service Bulletin are not applicable to the repaired area. The repaired area must be inspected in accordance with the Repair Design Approval Sheet. However the Rib 2 and Rib 3 area not covered by the repair must be inspected in accordance with this Service Bulletin. (3) Advantages Accomplishment of this Service Bulletin will make sure that any cracks are found in the wing top skin panels 1 and 2 along Rib 2 and Rib 3. In case of findings, the aircraft must be repaired before the next flight. A detailed damage report must be sent to AIRBUS repair group SEOE. (4) Operational/Maintenance Consequences The Operational/Maintenance Consequences of this Service Bulletin are covered by the update of the affected publications detailed in ’PLANNING INFORMATION’. D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 572096-832-895-001: Inspection (1) Do a check of the Aircraft Records for the LH Wing at Rib 2 (2) Do a check of the Aircraft Records for the RH Wing at Rib 2 (3) Do a check of the Aircraft Records for the LH Wing at Rib 3 (4) Do a check of the Aircraft Records for the RH Wing at Rib 3 (5) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 (6) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 (7) Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 4 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 21 @A310 SERVICE BULLETIN (8) Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 (9) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 (10) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 (11) Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 (12) Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 (13) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 for Aircraft Post Service Bulletin A310-57-2106 (14) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 for Aircraft Post Service Bulletin A310-57-2106 (15) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 (16) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 **CONF 002 Task 572096-832-895-001: Inspection (1) Do a check of the Aircraft Records for the LH Wing at Rib 2 (2) Do a check of the Aircraft Records for the RH Wing at Rib 2 (3) Do a check of the Aircraft Records for the LH Wing at Rib 3 (4) Do a check of the Aircraft Records for the RH Wing at Rib 3 (5) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 (6) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 (7) Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 (8) Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 (9) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 (10) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 (11) Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 (12) Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 (13) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 for Aircraft Post Service Bulletin A310-57-2106 (14) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 for DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 5 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 22 @A310 SERVICE BULLETIN Aircraft Post Service Bulletin A310-57-2106 (15) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 (16) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 **CONF 003 Task 572096-832-895-001: Inspection (1) Do a check of the Aircraft Records for the LH Wing at Rib 2 (2) Do a check of the Aircraft Records for the RH Wing at Rib 2 (3) Do a check of the Aircraft Records for the LH Wing at Rib 3 (4) Do a check of the Aircraft Records for the RH Wing at Rib 3 (5) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 (6) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 (7) Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 (8) Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 (9) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 (10) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 (11) Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 (12) Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 (13) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 for Aircraft Post Service Bulletin A310-57-2106 (14) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 for Aircraft Post Service Bulletin A310-57-2106 (15) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 (16) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 6 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 23 @A310 SERVICE BULLETIN **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale **CONF 001 NOTE : Unless specified otherwise, the threshold Flight Cycles (FC) and Flight Hours (FH) are from aircraft first flight. NOTE : *The threshold values given are from embodiment of Mod. 13785H5762 (Service Bulletin No. A310-57-2106) and/or 13786H5767 (Service Bulletin No. A310-57-2107), as applicable. A/C TYPE LOCATION CONFIGURATION THRESHOLD INTERVAL INSPECTION METHOD Pre Mod. 13785H5762, Service Bulletin No. A310-57-2106 18700 FC / 37400 FH 2000 FC / 4100 FH Detailed Inspection (DI) Special Detailed Inspection (SDI) Top skin at Rib 2 Post Mod. 13785H5762, Service Bulletin No. A310-57-2106 *2000 FC / 4100 FH 2000 FC / 4100 FH Detailed Inspection (DI) Pre Mod. 13786H5767, Service Bulletin No. A310-57-2107 18700 FC / 37400 FH 2000 FC / 4100 FH Detailed Inspection (DI) Special Detailed Inspection (SDI) A310-200 Top skin at Rib 3 Post Mod. 13786H5767, Service Bulletin No. A310-57-2107 *2000 FC / 4100 FH 2000 FC / 4100 FH Detailed Inspection (DI) NOTE : GRACE PERIODS For aircraft that have already performed inspection of the top skin at rib 2 in accordance with this Service Bulletin at any previous revision, the inspection of the top skin at rib 3 can be performed at the next scheduled inspection of the top skin at rib 2 and rib 3. If no ultrasonic equipment is available for the first or the next due DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 7 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 24 @A310 SERVICE BULLETIN inspection, then that inspection may be conducted using the DI technique only. The following inspection should be conducted using both DI and SDI techniques. For aircraft that have been inspected using the DI technique only (accomplishment of Service Bulletin No. 57-2096 Revision 00 or Revision 01), the next inspection (DI and SDI) must be accomplished within the previous interval of 1700 FC / 3500 FH. This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Av iation Safety Agenc y (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF 002 NOTE : Unless specified otherwise, the Flight Cycles (FC) and Flight Hours (FH) are from aircraft first flight. NOTE : *The threshold values given are from embodiment of Mod. 13785H5762 (Service Bulletin No. A310-57-2106) and/or 13786H5767 (Service Bulletin No. A310-57-2107), as applicable. A/C TYPE LOCATION CONFIGURATION THRESHOLD INTERVAL INSPECTION METHOD Pre Mod. 13785H5762, Service Bulletin No. A310-57-2106 17300 FC / 48400 FH 2000 FC / 5600 FH Detailed Inspection (DI) Special Detailed Inspection (SDI) Top skin at Rib 2 Post Mod. 13785H5762, Service Bulletin No. A310-57-2106 *2000 FC / 5600 FH 2000 FC / 5600 FH Detailed Inspection (DI) Pre Mod. 13786H5767, Service Bulletin No. A310-57-2107 17300 FC / 48400 FH 2000 FC / 5600 FH Detailed Inspection (DI) Special Detailed Inspection (SDI) A310-300 Short Range (SR) Top skin at Rib 3 Post Mod. 13786H5767, Service Bulletin No. A310-57-2107 *2000 FC / 5600 FH 2000 FC / 5600 FH Detailed Inspection (DI) NOTE : GRACE PERIODS For aircraft that have already performed inspection of the top skin at DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 8 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 25 @A310 SERVICE BULLETIN rib 2 in accordance with this Service Bulletin at any previous revision, the inspection of the top skin at rib 3 can be performed at the next scheduled inspection of the top skin at rib 2 and rib 3. If no ultrasonic equipment is available for the first or the next due inspection, then that inspection may be conducted using the DI technique only. The following inspection should be conducted using both DI and SDI techniques. For aircraft that have been inspected using the DI technique only (accomplishment of Service Bulletin No. 57-2096 Revision 00 or Revision 01), the next inspection (DI and SDI) must be accomplished within the previous interval of 1600 FC / 4600 FH. This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Av iation Safety Agenc y (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF 003 NOTE : Unless specified otherwise, the Flight Cycles (FC) and Flight Hours (FH) are from aircraft first flight. NOTE : *The threshold values given are from embodiment of Mod. 13785H5762 (Service Bulletin No. A310-57-2106) and/or 13786H5767 (Service Bulletin No. A310-57-2107), as applicable. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 9 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 26 @A310 SERVICE BULLETIN A/C TYPE LOCATION CONFIGURATION THRESHOLD INTERVAL INSPECTION METHOD Pre Mod. 13785H5762, Service Bulletin No. A310-57-2106 12800 FC / 64300 FH 1500 FC / 7500 FH Detailed Inspection (DI) Special Detailed Inspection (SDI) Top skin at Rib 2 Post Mod. 13785H5762, Service Bulletin No. A310-57-2106 *1500 FC / 7500 FH 1500 FC / 7500 FH Detailed Inspection (DI) Pre Mod. 13786H5767, Service Bulletin No. A310-57-2107 12800 FC / 64300 FH 1500 FC / 7500 FH Detailed Inspection (DI) Special Detailed Inspection (SDI) A310-300 Long Range (LR) Top skin at Rib 3 Post Mod. 13786H5767, Service Bulletin No. A310-57-2107 *1500 FC / 7500 FH 1500 FC / 7500 FH Detailed Inspection (DI) NOTE : GRACE PERIODS For aircraft that have already performed inspection of the top skin at rib 2 in accordance with this Service Bulletin at any previous revision, the inspection of the top skin at rib 3 can be performed at the next scheduled inspection of the top skin at rib 2 and rib 3. If no ultrasonic equipment is available for the first or the next due inspection, then that inspection may be conducted using the DI technique only. The following inspection should be conducted using both DI and SDI techniques. For aircraft that have been inspected using the DI technique only (accomplishment of Service Bulletin No. 57-2096 Revision 00 or Revision 01), the next inspection (DI and SDI) must be accomplished within the previous interval of 1200 FC / 6100 FH. This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Av iation Safety Agenc y (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 10 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 27 @A310 SERVICE BULLETIN **CONF ALL F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approv al 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. NOTE : The manhours necessary to accomplish this Service Bulletin will depend on the Aircraft’s modification configuration and inspection results. **CONF 001 Task 572096-832-895-001: Inspection Get Access 0.50 On Aircraft Do a check of the Aircraft Records for the LH Wing at Rib 2 0.50 Do a check of the Aircraft Records for the RH Wing at Rib 2 0.50 Do a check of the Aircraft Records for the LH Wing at Rib 3 0.50 Do a check of the Aircraft Records for the RH Wing at Rib 3 0.50 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 0.75 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 0.75 Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 1.00 Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 1.00 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 0.75 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 0.75 Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 1.00 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 11 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 28 @A310 SERVICE BULLETIN Task 572096-832-895-001: Inspection Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 1.00 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 for Aircraft Post Service Bulletin A310-57-2106 0.75 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 for Aircraft Post Service Bulletin A310-57-2106 0.75 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 0.75 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 0.75 Close-Up 0.50 TOTAL MANHOURS 13.00 ELAPSED TIME (HOURS) 13.00 **CONF 002 Task 572096-832-895-001: Inspection Get Access 0.50 On Aircraft Do a check of the Aircraft Records for the LH Wing at Rib 2 0.50 Do a check of the Aircraft Records for the RH Wing at Rib 2 0.50 Do a check of the Aircraft Records for the LH Wing at Rib 3 0.50 Do a check of the Aircraft Records for the RH Wing at Rib 3 0.50 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 0.75 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 0.75 Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 1.00 Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 1.00 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 0.75 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 0.75 Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 1.00 Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 1.00 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 12 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 29 @A310 SERVICE BULLETIN Task 572096-832-895-001: Inspection Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 for Aircraft Post Service Bulletin A310-57-2106 0.75 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 for Aircraft Post Service Bulletin A310-57-2106 0.75 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 0.75 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 0.75 Close-Up 0.50 TOTAL MANHOURS 13.00 ELAPSED TIME (HOURS) 13.00 **CONF 003 Task 572096-832-895-001: Inspection Get Access 0.50 On Aircraft Do a check of the Aircraft Records for the LH Wing at Rib 2 0.50 Do a check of the Aircraft Records for the RH Wing at Rib 2 0.50 Do a check of the Aircraft Records for the LH Wing at Rib 3 0.50 Do a check of the Aircraft Records for the RH Wing at Rib 3 0.50 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 0.75 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 0.75 Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 1.00 Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 1.00 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 0.75 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 0.75 Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 1.00 Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 1.00 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 for Aircraft Post Service Bulletin A310-57-2106 0.75 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 13 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 30 @A310 SERVICE BULLETIN Task 572096-832-895-001: Inspection Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 for Aircraft Post Service Bulletin A310-57-2106 0.75 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 0.75 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 0.75 Close-Up 0.50 TOTAL MANHOURS 13.00 ELAPSED TIME (HOURS) 13.00 **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-31-57 20-16-00 24-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 57-29-01 Structural Repair Manual (SRM) 51-75-10 51-75-20 **CONF 002 Aircraft Maintenance Manual (AMM) 06-31-57 20-16-00 24-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 57-29-01 Structural Repair Manual (SRM) 51-75-10 51-75-20 **CONF 003 Aircraft Maintenance Manual (AMM) 06-31-57 20-16-00 24-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 57-29-01 Structural Repair Manual (SRM) 51-75-10 51-75-20 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 14 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 31 @A310 SERVICE BULLETIN **CONF ALL K. PUBLICATION AFFECTED Maintenance Planning Document (MPD) 572146-01-1 572146-01-2 Non Destructive Test Manual (NTM) 57-29-01 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 15 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 32 @A310 SERVICE BULLETIN This Page Intentionally Left Blank DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 16 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 33 @A310 SERVICE BULLETIN 2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY None B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner-General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 17 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 34 @A310 SERVICE BULLETIN This Page Intentionally Left Blank DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 18 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 35 @A310 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 572096-832-895-001 - Inspection 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 include procedures given in other documents or in other sections of the Service Bulletin. When the words ’refer to’ are used and the operator has a procedure accepted by the local authority he belongs to, the accepted alternative procedure can be used. When the words "in accordance with" are used then the given procedure must be followed. NOTE : The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE : Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE : This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition. NOTE : The purpose of flowcharts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin. NOTE : This Service Bulletin contains the instructions for the on-aircraft maintenance DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 19 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 36 @A310 SERVICE BULLETIN necessary to ensure the continued airworthiness of the aircraft. For any deviations to the instructions contained herein, contact Airbus for further instructions and approval. Task Associated Data **CONF 001 Zone 210 510 610 Manpower TOTAL MANHOURS 13.00 ELAPSED TIME (HOURS) 13.00 **CONF 002 Zone 210 510 610 Manpower TOTAL MANHOURS 13.00 ELAPSED TIME (HOURS) 13.00 **CONF 003 Zone 210 510 610 Manpower TOTAL MANHOURS 13.00 ELAPSED TIME (HOURS) 13.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 572096-910-403-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-57, Page Block 001 20-16-00, Page Block 201 Consumable Material List (CML) Structural Repair Manual (SRM) 51-75-10 51-75-20 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 20 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 37 @A310 SERVICE BULLETIN (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Materials List (CML). (b) For the identification of Ribs, refer to AMM 06-31-57, Page Block 001. (c) Do the stripping/removal of paint coating in accordance with SRM 51-75-20. (d) Do the repair of paint coating in accordance with SRM 51-75-10. (e) For circuit breaker safety practices, refer to AMM 20-16-00, Page Block 201. (2) Subtask 572096-839-408-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 002 (1) Subtask 572096-910-403-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-57, Page Block 001 20-16-00, Page Block 201 Consumable Material List (CML) Structural Repair Manual (SRM) 51-75-10 51-75-20 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Materials List (CML). (b) For the identification of Ribs, refer to AMM 06-31-57, Page Block 001. (c) Do the stripping/removal of paint coating in accordance with SRM 51-75-20. (d) Do the repair of paint coating in accordance with SRM 51-75-10. (e) For circuit breaker safety practices, refer to AMM 20-16-00, Page Block 201. (2) Subtask 572096-839-408-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 21 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 38 @A310 SERVICE BULLETIN **CONF 003 (1) Subtask 572096-910-403-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-57, Page Block 001 20-16-00, Page Block 201 Consumable Material List (CML) Structural Repair Manual (SRM) 51-75-10 51-75-20 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Materials List (CML). (b) For the identification of Ribs, refer to AMM 06-31-57, Page Block 001. (c) Do the stripping/removal of paint coating in accordance with SRM 51-75-20. (d) Do the repair of paint coating in accordance with SRM 51-75-10. (e) For circuit breaker safety practices, refer to AMM 20-16-00, Page Block 201. (2) Subtask 572096-839-408-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 572096-941-403-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 510 Work location Rib 2 Rib 3 610 Work location Rib 2 Rib 3 Manpower Resources Skills NON SPECIFIC DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 22 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 39 @A310 SERVICE BULLETIN References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic system s depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position. (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) Put warning notices in position to tell persons not to operate the slats/flaps. (c) Put access platforms in position to get access to the wing top surface at Rib 2 and Rib 3. (2) Subtask 572096-865-404-001 - C/B Opening Work Zones and Access Panels Zone Access/Work location 210 Work location Circuit Breaker Panel 127-VU Manpower Resources Skills ELECTRICAL (a) Open, safety and tag this (these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 127VU FLT CTL/KRUGER 45CV 704/M61 127VU FLT CTL/SFCC/NORM SUPPLY/SLATS/SYS 1 7CV 704/M64 127VU FLT CTL/SFCC/NORM SUPPLY/SLATS/SYS 2 8CV 704/M66 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 23 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 40 @A310 SERVICE BULLETIN PANEL DESIGNATION FIN LOCATION SEE NOTES 127VU FLT CTL/SFCC/LAND RECOVERY/SUPPLY/SLATS/ SYS 1 9CV 704/M65 127VU FLT CTL/SFCC/NORM SUPPLY/FLAPS/SYS 2 6CV 705/L66 127VU FLT CTL/SFCC/NORM SUPPLY/FLAPS/SYS 1 5CV 705/L65 127VU FLT CTL/SFCC/LAND RECOVERY/SUPPLY/FLAPS/ SYS 1 10CV 705/L64 **CONF 002 (1) Subtask 572096-941-403-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 510 Work location Rib 2 Rib 3 610 Work location Rib 2 Rib 3 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic system s depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 24 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 41 @A310 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) Put warning notices in position to tell persons not to operate the slats/flaps. (c) Put access platforms in position to get access to the wing top surface at Rib 2 and Rib 3. (2) Subtask 572096-865-404-002 - C/B Opening Work Zones and Access Panels Zone Access/Work location 210 Work location Circuit Breaker Panel 133-VU Manpower Resources Skills ELECTRICAL (a) Open, safety and tag this (these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 133VU FLT CTL/KRUGER 45CV 333/T61 133VU FLT CTL/SFCC/NORM SUPPLY/SLATS/SYS 1 7CV 333/T63 133VU FLT CTL/SFCC/NORM SUPPLY/SLATS/SYS 2 8CV 333/T64 133VU FLT CTL/SFCC/LAND RECOVERY/SUPPLY/SLATS/ SYS 1 9CV 335/R66 133VU FLT CTL/SFCC/NORM SUPPLY/FLAPS/SYS 2 6CV 331/V61 133VU FLT CTL/SFCC/NORM SUPPLY/FLAPS/SYS 1 5CV 332/U61 133VU FLT CTL/SFCC/LAND RECOVERY/SUPPLY/FLAPS/ SYS 1 10CV 335/R67 **CONF 003 (1) Subtask 572096-941-403-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 510 Work location Rib 2 Rib 3 610 Work location Rib 2 Rib 3 Manpower Resources Skills NON SPECIFIC DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 25 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 42 @A310 SERVICE BULLETIN References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic system s depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position. (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) Put warning notices in position to tell persons not to operate the slats/flaps. (c) Put access platforms in position to get access to the wing top surface at Rib 2 and Rib 3. (2) Subtask 572096-865-404-002 - C/B Opening Work Zones and Access Panels Zone Access/Work location 210 Work location Circuit Breaker Panel 133-VU Manpower Resources Skills ELECTRICAL (a) Open, safety and tag this (these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 133VU FLT CTL/KRUGER 45CV 333/T61 133VU FLT CTL/SFCC/NORM SUPPLY/SLATS/SYS 1 7CV 333/T63 133VU FLT CTL/SFCC/NORM SUPPLY/SLATS/SYS 2 8CV 333/T64 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 26 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 43 @A310 SERVICE BULLETIN PANEL DESIGNATION FIN LOCATION SEE NOTES 133VU FLT CTL/SFCC/LAND RECOVERY/SUPPLY/SLATS/ SYS 1 9CV 335/R66 133VU FLT CTL/SFCC/NORM SUPPLY/FLAPS/SYS 2 6CV 331/V61 133VU FLT CTL/SFCC/NORM SUPPLY/FLAPS/SYS 1 5CV 332/U61 133VU FLT CTL/SFCC/LAND RECOVERY/SUPPLY/FLAPS/ SYS 1 10CV 335/R67 **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 572096-839-404-001 - Do a check of the Aircraft Records for the LH Wing at Rib 2 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Fig. A-UFAAA Flowchart Sheet 01 Sheet 02 NOTE : If a previous repair has been embodied in the inspected area, further inspection of the repaired area should be performed in accordance with the repair design approval sheet (RDAS). Areas with no previous repairs must be inspected in accordance with the instructions of this Service Bulletin. (a) Do a check of the aircraft records. (b) Refer to Fig. A-UFAAA Sheet 01 to select which of the following work steps to complete. 1 If Service Bulletin A310-57-2106 has not been embodied then go to SUBTASK 572096-832-401 002 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1a n d2a tR i b2 . 2 If Service Bulletin A310-57-2106 has been embodied then go to SUBTASK 572096-832-412 002 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 for Aircraft Post Service Bulletin A310-57-2106 . DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 27 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 44 @A310 SERVICE BULLETIN (2) Subtask 572096-839-405-001 - Do a check of the Aircraft Records for the RH Wing at Rib 2 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Fig. A-UFAAA Flowchart Sheet 01 Sheet 02 NOTE : If a previous repair has been embodied in the inspected area, further inspection of the repaired area should be performed in accordance with the repair design approval sheet (RDAS). Areas with no previous repairs must be inspected in accordance with the instructions of this Service Bulletin. (a) Do a check of the aircraft records. (b) Refer to Fig. A-UFAAA Sheet 01 to select which of the following work steps to complete. 1 If Service Bulletin A310-57-2106 has not been embodied then go to SUBTASK 572096-832-402 002 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1a n d2a tR i b2 . 2 If Service Bulletin A310-57-2106 has been embodied then go to SUBTASK 572096-832-413 001 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 for Aircraft Post Service Bulletin A310-57-2106 . (3) Subtask 572096-839-406-001 - Do a check of the Aircraft Records for the LH Wing at Rib 3 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Fig. A-UFAAA Flowchart Sheet 01 Sheet 02 NOTE : If a previous repair has been embodied in the inspected area, further inspection of the repaired area should be performed in accordance with the repair design approval sheet (RDAS). Areas with no previous repairs must be inspected in accordance with the instructions of this Service Bulletin. (a) Do a check of the aircraft records. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 28 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 45 @A310 SERVICE BULLETIN (b) Refer to Fig. A-UFAAA Sheet 02 to select which of the following work steps to complete. 1 If Service Bulletin A310-57-2107 has not been embodied then go to SUBTASK 572096-832-405 002 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1a n d2a tR i b3 . 2 If Service Bulletin A310-57-2107 has been embodied then go to SUBTASK 572096-832-414 001 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 . (4) Subtask 572096-839-407-001 - Do a check of the Aircraft Records for the RH Wing at Rib 3 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC References Fig. A-UFAAA Flowchart Sheet 01 Sheet 02 NOTE : If a previous repair has been embodied in the inspected area, further inspection of the repaired area should be performed in accordance with the repair design approval sheet (RDAS). Areas with no previous repairs must be inspected in accordance with the instructions of this Service Bulletin. (a) Do a check of the aircraft records. (b) Refer to Fig. A-UFAAA Sheet 02 to select which of the following work steps to complete. 1 If Service Bulletin A310-57-2107 has not been embodied then go to SUBTASK 572096-832-406 002 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1a n d2a tR i b3 . 2 If Service Bulletin A310-57-2107 has been embodied then go to SUBTASK 572096-832-415 001 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 . (5) Subtask 572096-832-401-002 - Detailed Inspection (DI) of the LH Wing-skin Top P a n e l s1a n d2a tR i b2 Work Zones and Access Panels Zone Access/Work location 510 Work location Rib 2 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 29 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 46 @A310 SERVICE BULLETIN Manpower Resources Manhours 0.75 Minimum number of person 1 Subtask elapsed time 0.75 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner- General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection Area (Pre Mods. 13785H5762 and 13786H5767) Sheet 01 Sheet 02 Fig. A-UAAAA Inspection Report Sheet 01 NOTE : The worksteps that follow are for aircraft which have not embodied Service Bulletin A310-57-2106. NOTE : If a previous repair has been embodied in the inspected area, further inspection of the repaired area should be performed in accordance with the repair design approval sheet (RDAS). Areas with no previous repairs must be inspected in accordance with the instructions of this Service Bulletin. Refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02 . (a) At the threshold given in Paragraph 1.E.(2) ’Accomplishment Timescale’, do a Detailed Inspection (DI) of the LH wing-skin top panels 1 and 2 at Rib 2. 1 Make sure that the inspection area is clean and there is no area of loose or flaking paint. If there is loose or flaking paint, or if anti-slip paint has been applied within the inspection area, it must be removed before cleaning. Chemical paint stripping is recommended as removal by abrasion could hide any cracks. Use: Textile-Lint Free Cotton 14SBA1 As required made moist with: DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 30 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 47 @A310 SERVICE BULLETIN Non Aqueous Cleaner-General 08BAA9 As required 2 Use a good light source and if necessary use a source of magnification to make a careful inspection of the area. Look very closely around the fastener heads for typical cracks. NOTE : If the aircraft has been recently refuelled, a fuel stain around the head of a fastener is a good indication of a crack at that position. 3 If cracks are found, record all findings on the Inspection Report Sheet, Fig. A- UAAAA S heet 01 and return it to AIRBUS for a suitable repair before the next flight. Refer to Repair Drawing R57140308, sheets 2 and 4 to identify the fastener holes. 4 If no cracks are found, go to SUBTASK 572096-832-403 002 Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 . Report the nil findings on the Inspection Report Sheet, Fig. A-UAAAA Sheet 01 and return it to AIRBUS. (6) Subtask 572096-832-402-002 - Detailed Inspection (DI) of the RH Wing-skin Top P a n e l s1a n d2a tR i b2 Work Zones and Access Panels Zone Access/Work location 610 Work location Rib 2 Manpower Resources Manhours 0.75 Minimum number of person 1 Subtask elapsed time 0.75 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner- General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection Area (Pre Mods. 13785H5762 and 13786H5767) Sheet 01 Sheet 02 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 31 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 48 @A310 SERVICE BULLETIN References Fig. A-UAAAA Inspection Report Sheet 01 NOTE : The worksteps that follow are for aircraft which have not embodied Service Bulletin A310-57-2106. NOTE : If a previous repair has been embodied in the inspected area, further inspection of the repaired area should be performed in accordance with the repair design approval sheet (RDAS). Areas with no previous repairs must be inspected in accordance with the instructions of this Service Bulletin. Refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02 . (a) At the threshold given in Paragraph 1.E.(2) ’Accomplishment Timescale’, do a Detailed Inspection (DI) of the RH wing-skin top panels 1 and 2 at Rib 2. 1 Make sure that the inspection area is clean and there is no area of loose or flaking paint. If there is loose or flaking paint, or if anti-slip paint has been applied within the inspection area, it must be removed before cleaning. Chemical paint stripping is recommended as removal by abrasion could hide any cracks. Use: Textile-Lint Free Cotton 14SBA1 As required made moist with: Non Aqueous Cleaner-General 08BAA9 As required 2 Use a good light source and if necessary use a source of magnification to make a careful inspection of the area. Look very closely around the fastener heads for typical cracks. NOTE : If the aircraft has been recently refuelled, a fuel stain around the head of a fastener is a good indication of a crack at that position. 3 If cracks are found, record all findings on the Inspection Report Sheet, Fig. A- UAAAA S heet 01 and return it to AIRBUS for a suitable repair before the next flight. Refer to Repair Drawing R57140308, sheets 2 and 4 to identify the fastener holes. 4 If no cracks are found, go to SUBTASK 572096-832-404 002 Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 . Report the nil findings on the Inspection Report Sheet, Fig. A-UAAAA Sheet 01 and return it to AIRBUS. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 32 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 49 @A310 SERVICE BULLETIN (7) Subtask 572096-832-403-002 - Special Detailed Inspection (SDI) of the LH Wing- skin Top Panels 1 and 2 at Rib 2 Work Zones and Access Panels Zone Access/Work location 510 Work location Rib 2 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 57-29-01 Fig. A-UBAAA Inspection Area (Pre Mods. 13785H5762 and 13786H5767) Sheet 01 Sheet 02 Fig. A-UAAAA Inspection Report Sheet 01 NOTE : The worksteps that follow are for aircraft which have not embodied Service Bulletin A310-57-2106. NOTE : If a previous repair has been embodied in the inspected area, further inspection of the repaired area should be performed in accordance with the repair design approval sheet (RDAS). Areas with no previous repairs must be inspected in accordance with the instructions of this Service Bulletin. Refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02 . (a) At the threshold given in Paragraph 1.E(2) ’Accomplishment Timescale’, do a Special Detailed Inspection (SDI) (ultrasonic phased array) of the area around the fasteners, in accordance with NTM 57-29-01. 1 If cracks are found, record all findings on the Inspection Report Sheet, Fig. A- UAAAA S heet 01 and return it to AIRBUS for a suitable repair before the next flight. Refer to Repair Drawing R57140308, sheets 2 and 4 to identify the fastener holes. 2 If no cracks are found, restore the paint finish as necessary and go to SUBTASK 572096-832-405 002 Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 . Report the nil findings on the Inspection Report Sheet, Fig. A-UAAAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 33 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 50 @A310 SERVICE BULLETIN (8) Subtask 572096-832-404-002 - Special Detailed Inspection (SDI) of the RH Wing- skin Top Panels 1 and 2 at Rib 2 Work Zones and Access Panels Zone Access/Work location 610 Work location Rib 2 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 57-29-01 Fig. A-UBAAA Inspection Area (Pre Mods. 13785H5762 and 13786H5767) Sheet 01 Sheet 02 Fig. A-UAAAA Inspection Report Sheet 01 NOTE : The worksteps that follow are for aircraft which have not embodied Service Bulletin A310-57-2106. NOTE : If a previous repair has been embodied in the inspected area, further inspection of the repaired area should be performed in accordance with the repair design approval sheet (RDAS). Areas with no previous repairs must be inspected in accordance with the instructions of this Service Bulletin. Refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02 . (a) At the threshold given in Paragraph 1.E(2) ’Accomplishment Timescale’, do a Special Detailed Inspection (SDI) (ultrasonic phased array) of the area around the fasteners, in accordance with NTM 57-29-01. 1 If cracks are found, record all findings on the Inspection Report Sheet, Fig. A- UAAAA S heet 01 and return it to AIRBUS for a suitable repair before the next flight. Refer to Repair Drawing R57140308, sheets 2 and 4 to identify the fastener holes. 2 If no cracks are found, restore the paint finish as necessary and go to SUBTASK 572096-832-406 002 Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 . Report the nil findings on the Inspection Report Sheet, Fig. A-UAAAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 34 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 51 @A310 SERVICE BULLETIN (9) Subtask 572096-832-405-002 - Detailed Inspection (DI) of the LH Wing-skin Top P a n e l s1a n d2a tR i b3 Work Zones and Access Panels Zone Access/Work location 510 Work location Rib 3 Manpower Resources Manhours 0.75 Minimum number of person 1 Subtask elapsed time 0.75 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner- General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection Area (Pre Mods. 13785H5762 and 13786H5767) Sheet 01 Sheet 02 Fig. A-UABAA Inspection Report Sheet 01 NOTE : The worksteps that follow are for aircraft which have not embodied Service Bulletin A310-57-2107. NOTE : If a previous repair has been embodied in the inspected area, further inspection of the repaired area should be performed in accordance with the repair design approval sheet (RDAS). Areas with no previous repairs must be inspected in accordance with the instructions of this Service Bulletin. Refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02 . (a) At the threshold given in Paragraph 1.E.(2) ’Accomplishment Timescale’, do a Detailed Inspection (DI) of the LH wing-skin top panels 1 and 2 at Rib 3. 1 Make sure that the inspection area is clean and there is no area of loose or flaking paint. If there is loose or flaking paint, or if anti-slip paint has been applied within the inspection area, it must be removed before cleaning. Chemical paint stripping is recommended as removal by abrasion could hide any cracks. Use: DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 35 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 52 @A310 SERVICE BULLETIN Textile-Lint Free Cotton 14SBA1 As required made moist with: Non Aqueous Cleaner-General 08BAA9 As required 2 Use a good light source and if necessary use a source of magnification to make a careful inspection of the area. Look very closely around the fastener heads for typical cracks. NOTE : If the aircraft has been recently refuelled, a fuel stain around the head of a fastener is a good indication of a crack at that position. 3 If cracks are found, record all findings on the Inspection Report Sheet, Fig. A- UABAA S heet 01 and return it to AIRBUS for a suitable repair before the next flight. Refer to Repair Drawing R57140308, sheets 2 and 4 to identify the fastener holes. 4 If no cracks are found, go to SUBTASK 572096-832-407 002 Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 . Report the nil findings on the Inspection Report Sheet, Fig. A-UABAA Sheet 01 and return it to AIRBUS. (10) Subtask 572096-832-406-002 - Detailed Inspection (DI) of the RH Wing-skin Top P a n e l s1a n d2a tR i b3 Work Zones and Access Panels Zone Access/Work location 610 Work location Rib 3 Manpower Resources Manhours 0.75 Minimum number of person 1 Subtask elapsed time 0.75 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner- General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 36 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 53 @A310 SERVICE BULLETIN References Fig. A-UBAAA Inspection Area (Pre Mods. 13785H5762 and 13786H5767) Sheet 01 Sheet 02 Fig. A-UABAA Inspection Report Sheet 01 NOTE : The worksteps that follow are for aircraft which have not embodied Service Bulletin A310-57-2107. NOTE : If a previous repair has been embodied in the inspected area, further inspection of the repaired area should be performed in accordance with the repair design approval sheet (RDAS). Areas with no previous repairs must be inspected in accordance with the instructions of this Service Bulletin. Refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02 . (a) At the threshold given in Paragraph 1.E.(2) ’Accomplishment Timescale’, do a Detailed Inspection (DI) of the RH wing-skin top panels 1 and 2 at Rib 3. 1 Make sure that the inspection area is clean and there is no area of loose or flaking paint. If there is loose or flaking paint, or if anti-slip paint has been applied within the inspection area, it must be removed before cleaning. Chemical paint stripping is recommended as removal by abrasion could hide any cracks. Use: Textile-Lint Free Cotton 14SBA1 As required made moist with: Non Aqueous Cleaner-General 08BAA9 As required 2 Use a good light source and if necessary use a source of magnification to make a careful inspection of the area. Look very closely around the fastener heads for typical cracks. NOTE : If the aircraft has been recently refuelled, a fuel stain around the head of a fastener is a good indication of a crack at that position. 3 If cracks are found, record all findings on the Inspection Report Sheet, Fig. A- UABAA S heet 01 and return it to AIRBUS for a suitable repair before the next flight. Refer to Repair Drawing R57140308, sheets 2 and 4 to identify the fastener holes. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 37 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 54 @A310 SERVICE BULLETIN 4 If no cracks are found, go to SUBTASK 572096-832-408 002 Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 . Report the nil findings on the Inspection Report Sheet, Fig. A-UABAA Sheet 01 and return it to AIRBUS. (11) Subtask 572096-832-407-002 - Special Detailed Inspection (SDI) of the LH Wing- skin Top Panels 1 and 2 at Rib 3 Work Zones and Access Panels Zone Access/Work location 510 Work location Rib 3 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 57-29-01 Fig. A-UBAAA Inspection Area (Pre Mods. 13785H5762 and 13786H5767) Sheet 01 Sheet 02 Fig. A-UABAA Inspection Report Sheet 01 NOTE : The worksteps that follow are for aircraft which have not embodied Service Bulletin A310-57-2107. NOTE : If a previous repair has been embodied in the inspected area, further inspection of the repaired area should be performed in accordance with the repair design approval sheet (RDAS). Areas with no previous repairs must be inspected in accordance with the instructions of this Service Bulletin. Refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02 . (a) At the threshold given in Paragraph 1.E(2) ’Accomplishment Timescale’, do a Special Detailed Inspection (SDI) (ultrasonic phased array) of the area around the fasteners, in accordance with NTM 57-29-01. 1 If cracks are found, record all findings on the Inspection Report Sheet, Fig. A- UABAA S heet 01 and return it to AIRBUS for a suitable repair before the next flight. Refer to Repair Drawing R57140308, sheets 2 and 4 to identify the fastener holes. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 38 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 55 @A310 SERVICE BULLETIN 2 If no cracks are found, restore the paint finish as necessary and go to SUBTASK 572096-865-402 001 C/B Closing . Report the nil findings on the Inspection Report Sheet, Fig. A-UABAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’. (12) Subtask 572096-832-408-002 - Special Detailed Inspection (SDI) of the RH Wing- skin Top Panels 1 and 2 at Rib 3 Work Zones and Access Panels Zone Access/Work location 610 Work location Rib 3 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 57-29-01 Fig. A-UBAAA Inspection Area (Pre Mods. 13785H5762 and 13786H5767) Sheet 01 Sheet 02 Fig. A-UABAA Inspection Report Sheet 01 NOTE : The worksteps that follow are for aircraft which have not embodied Service Bulletin A310-57-2107. NOTE : If a previous repair has been embodied in the inspected area, further inspection of the repaired area should be performed in accordance with the repair design approval sheet (RDAS). Areas with no previous repairs must be inspected in accordance with the instructions of this Service Bulletin. Refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02 . (a) At the threshold given in Paragraph 1.E(2) ’Accomplishment Timescale’, do a Special Detailed Inspection (SDI) (ultrasonic phased array) of the area around the fasteners, in accordance with NTM 57-29-01. 1 If cracks are found, record all findings on the Inspection Report Sheet, Fig. A- UABAA S heet 01 and return it to AIRBUS for a suitable repair before the next flight. Refer to Repair Drawing R57140308, sheets 2 and 4 to identify the fastener holes. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 39 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 56 @A310 SERVICE BULLETIN 2 If no cracks are found, restore the paint finish as necessary and go to SUBTASK 572096-865-402 001 C/B Closing . Report the nil findings on the Inspection Report Sheet, Fig. A-UABAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’. (13) Subtask 572096-832-412-002 - Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 for Aircraft Post Service Bulletin A310-57-2106 Work Zones and Access Panels Zone Access/Work location 510 Work location Rib 2 Manpower Resources Manhours 0.75 Minimum number of person 1 Subtask elapsed time 0.75 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner- General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBBAA Inspection Area (Post Mods. 13785H5762 and 13786H5767) Sheet 01 Sheet 02 Fig. A-UAAAA Inspection Report Sheet 01 NOTE : If a previous repair has been embodied in the inspected area, further inspection of the repaired area should be performed in accordance with the repair design approval sheet (RDAS). Areas with no previous repairs must be inspected in accordance with the instructions of this Service Bulletin. (a) At the threshold given in Paragraph 1.E.(2) ’Accomplishment Timescale’, do a Detailed Inspection (DI) of the LH wing-skin top panels 1 and 2 at Rib 2. Refer to Fig. A-UBBAA Sheet 01 and Fig. A-UBBAA Sheet 02 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 40 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 57 @A310 SERVICE BULLETIN 1 Make sure that the inspection area is clean and there is no area of loose or flaking paint. If there is loose or flaking paint, or if anti-slip paint has been applied within the inspection area, it must be removed before cleaning. Chemical paint stripping is recommended as removal by abrasion could hide any cracks. Use: Textile-Lint Free Cotton 14SBA1 As required made moist with: Non Aqueous Cleaner-General 08BAA9 As required 2 Use a good light source and if necessary use a source of magnification to make a careful inspection of the area. Look very closely around the fastener heads for typical cracks. NOTE : If the aircraft has been recently refuelled, a fuel stain around the head of a fastener is a good indication of a crack at that position. 3 If cracks are found, record all findings on the Inspection Report Sheet, Fig. A- UAAAA S heet 01 and return it to AIRBUS for a suitable repair before the next flight. Refer to Repair Drawing R57140308, sheets 2 and 4 to identify the fastener holes. 4 If no cracks are found, go to SUBTASK 572096-865-402 001 C/B Closing . Report the nil findings on the Inspection Report Sheet, Fig. A-UAAAA Sheet 01 and return it to AIRBUS. (14) Subtask 572096-832-413-001 - Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 for Aircraft Post Service Bulletin A310-57-2106 Work Zones and Access Panels Zone Access/Work location 610 Work location Rib 2 Manpower Resources Manhours 0.75 Minimum number of person 1 Subtask elapsed time 0.75 Skills NON DESTRUCTIVE TESTING DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 41 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 58 @A310 SERVICE BULLETIN Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner- General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBBAA Inspection Area (Post Mods. 13785H5762 and 13786H5767) Sheet 01 Sheet 02 Fig. A-UAAAA Inspection Report Sheet 01 NOTE : If a previous repair has been embodied in the inspected area, further inspection of the repaired area should be performed in accordance with the repair design approval sheet (RDAS). Areas with no previous repairs must be inspected in accordance with the instructions of this Service Bulletin. (a) At the threshold given in Paragraph 1.E.(2) ’Accomplishment Timescale’, do a Detailed Inspection (DI) of the LH wing-skin top panels 1 and 2 at Rib 2. Refer to Fig. A-UBBAA Sheet 01 and Fig. A-UBBAA Sheet 02 1 Make sure that the inspection area is clean and there is no area of loose or flaking paint. If there is loose or flaking paint, or if anti-slip paint has been applied within the inspection area, it must be removed before cleaning. Chemical paint stripping is recommended as removal by abrasion could hide any cracks. Use: Textile-Lint Free Cotton 14SBA1 As required made moist with: Non Aqueous Cleaner-General 08BAA9 As required 2 Use a good light source and if necessary use a source of magnification to make a careful inspection of the area. Look very closely around the fastener heads for typical cracks. NOTE : If the aircraft has been recently refuelled, a fuel stain around the head of a fastener is a good indication of a crack at that position. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 42 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 59 @A310 SERVICE BULLETIN 3 If cracks are found, record all findings on the Inspection Report Sheet, Fig. A- UAAAA S heet 01 and return it to AIRBUS for a suitable repair before the next flight. Refer to Repair Drawing R57140308, sheets 2 and 4 to identify the fastener holes. 4 If no cracks are found, go to SUBTASK 572096-865-402 001 C/B Closing . Report the nil findings on the Inspection Report Sheet, Fig. A-UAAAA Sheet 01 and return it to AIRBUS. (15) Subtask 572096-832-414-001 - Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 Work Zones and Access Panels Zone Access/Work location 510 Work location Rib 3 Manpower Resources Manhours 0.75 Minimum number of person 1 Subtask elapsed time 0.75 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner- General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBBAA Inspection Area (Post Mods. 13785H5762 and 13786H5767) Sheet 01 Sheet 02 Fig. A-UABAA Inspection Report Sheet 01 NOTE : If a previous repair has been embodied in the inspected area, further inspection of the repaired area should be performed in accordance with the repair design approval sheet (RDAS). Areas with no previous repairs must be inspected in accordance with the instructions of this Service Bulletin. (a) At the threshold given in Paragraph 1.E.(2) ’Accomplishment Timescale’, do a Detailed Inspection (DI) of the LH wing-skin top panels 1 and 2 at Rib 3. Refer to Fig. A-UBBAA Sheet 01 and Fig. A-UBBAA Sheet 02 . DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 43 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 60 @A310 SERVICE BULLETIN 1 Make sure that the inspection area is clean and there is no area of loose or flaking paint. If there is loose or flaking paint, or if anti-slip paint has been applied within the inspection area, it must be removed before cleaning. Chemical paint stripping is recommended as removal by abrasion could hide any cracks. Use: Textile-Lint Free Cotton 14SBA1 As required made moist with: Non Aqueous Cleaner-General 08BAA9 As required 2 Use a good light source and if necessary use a source of magnification to make a careful inspection of the area. Look very closely around the fastener heads for typical cracks. NOTE : If the aircraft has been recently refuelled, a fuel stain around the head of a fastener is a good indication of a crack at that position. 3 If cracks are found, record all findings on the Inspection Report Sheet, Fig. A- UABAA S heet 01 and return it to AIRBUS for a suitable repair before the next flight. Refer to Repair Drawing R57140308, sheets 2 and 4 to identify the fastener holes. 4 If no cracks are found, go to SUBTASK 572096-865-402 001 C/B Closing . Report the nil findings on the Inspection Report Sheet, Fig. A-UABAA Sheet 01 and return it to AIRBUS. (16) Subtask 572096-832-415-001 - Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 for Aircraft Post Service Bulletin A310-57-2107 Work Zones and Access Panels Zone Access/Work location 610 Work location Rib 3 Manpower Resources Manhours 0.75 Minimum number of person 1 Subtask elapsed time 0.75 Skills NON DESTRUCTIVE TESTING DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 04 - Dec 05/16 Page: 44 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. The text continues at https://openairdocs.org/service-documents/airbus/a310-57-2096/file/c2f724f3c262.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). 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