# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 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.03 of Service Bulletin No.A310-57-2096 ADDITIONAL WORK **CONF ALL No Additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 03 issued to: - 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. CHANGES FRONT MATTER WINGS - INSPECTION OF WING TOP SKIN PANEL 1 AND 2 AT RIB 2 AND RIB 3 SB TITLE UPDATED R
SUMMARY REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES REASON UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE UPDATED R
DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 1 7

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

# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
MANPOWER MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R Fig. A-USAAA Fig. A-USAAA Sheet 01 SHEET UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONF 001 CONFIGURATION DEFINITION UPDATED R CONF 003 CONFIGURATION DEFINITION UPDATED R CONF 004 CONFIGURATION DEFINITION UPDATED R REASON History HISTORY UPDATED R Objective/Action OBJECTIVE/ACTION UPDATED R Advantages ADVANTAGES UPDATED R COMPLIANCE Accomplishment Timescale Repetitive inspection timescales updated. R Accomplishment Timescale Repetitive inspection timescales updated. R Accomplishment Timescale Repetitive inspection timescales updated. R APPROVAL APPROVAL UPDATED R MANPOWER Manhours revised. R Manhours revised. R Manhours revised. R Manhours revised. R ACCOMPLISHMENT INSTRUCTIONS TASK 572096- 832-895-001-Inspection Sentences S301, S302, S303, S304, S214 and S230 added 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 MAN HOURS UPDATED ELAPSED TIME UPDATED R Subtask 572096-941-405-001 CB opening moved to new subtask. R Subtask 572096-941-405-001 CB opening moved to new subtask. R Subtask 572096-941-405-001 CB opening moved to new subtask. R Subtask 572096-941-405-001 CB opening moved to new subtask. R Subtask 572096-832-403-001 Visual inspection changed to detailed inspection. Illustration references updated. R Subtask 572096-832-405-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-404-001 Subtask created for SDI. R DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 2 7

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

# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 572096-832-406-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-409-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-410-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-408-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-407-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-403-001 Visual inspection changed to detailed inspection. Illustration references updated. R Subtask 572096-832-405-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-404-001 Subtask created for SDI. R Subtask 572096-832-406-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-409-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-410-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-408-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-407-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-403-001 Visual inspection changed to detailed inspection. Illustration references updated. R Subtask 572096-832-405-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-404-001 Subtask created for SDI. R Subtask 572096-832-406-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-409-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-410-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-408-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-407-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-403-001 Visual inspection changed to detailed inspection. Illustration references updated. R Subtask 572096-832-405-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-404-001 Subtask created for SDI. R Subtask 572096-832-406-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-409-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-410-001 SUBTASK SOLUTION ADDED N Subtask 572096-832-408-002 SUBTASK SOLUTION ADDED N Subtask 572096-832-407-001 SUBTASK SOLUTION ADDED N Subtask 572096-942-402-001 CB closing moved to new subtask. R Subtask 572096-942-402-001 CB closing moved to new subtask. R Subtask 572096-942-402-001 CB closing moved to new subtask. R Subtask 572096-942-402-001 CB closing moved to new subtask. R Fig. A-UBAAA Fig. A-UBAAA Sheet 01 SHEET UPDATED R Fig. A-UBAAA Sheet 02 SHEET UPDATED R Fig. A-UFBAA FIGURE SOLUTION ADDED N Fig. A-UFBAA Sheet 01 SHEET ADDED N Fig. A-UFBAB FIGURE SOLUTION ADDED N Fig. A-UFBAB Sheet 01 SHEET ADDED N Fig. A-UFBAC FIGURE SOLUTION ADDED N
DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 3 7

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

# @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Fig. A-UFBAC Sheet 01 SHEET ADDED N Fig. A-URBAA FIGURE SOLUTION ADDED N Fig. A-URBAA Sheet 01 SHEET ADDED N FILLING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS 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 SEQUENCE ORIGINAL: May 06/08 REVISION No. : 02 - Mar 05/14 REVISION No. : 03 - Jun 30/15

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 4 7

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

# @A310 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft. 

# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 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.: 03 - Jun 30/15 Page: 1 7

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

# @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. 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 **CONF 004 No Material EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

18T 19U 40T 50W 58X 82Z 83V 98W 99Y AFG BBC CFC DGA F2I FDX GAF I2L IRA IRM IYE K1P KAC KZU PCA PIA QAF R1T RJA ROT RZO SGX SUD THY TSC TXP UBD UZB WHT CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 57.20.12.001 OEB None AOT None SIL None DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 2 7

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

# @A310 SERVICE BULLETIN SUMMARY ISI None 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 8.00 ELAPSED TIME (HOURS) 8.00 **CONF 002 Task 572096-832-895-001: Inspection TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 8.00 **CONF 003 Task 572096-832-895-001: Inspection TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 8.00 **CONF 004 Task 572096-832-895-001: Inspection TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 8.00 APPENDICES **CONF ALL None

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 3 7

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

# @A310 SERVICE BULLETIN SUMMARY

**CONF ALL

Z500 Z600

NOTE:INSPECTION AREA. LH SHOWN RH SIMILAR 

## A FRONT SPAR

REAR SPAR TOP SKIN PANEL 1

TOP SKIN PANEL 2

TOP SKIN PANEL 3 RIB2 RIB3 

### A A

B_SB_572096_7_SAAA_01_01 Figure A-USAAA - Sheet 01
DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 4 7

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

# @A310 SERVICE BULLETIN
AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 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 0407 0413 0418-0419 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.: 03 - Jun 30/15 Page: 1 7

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

# @A310 SERVICE BULLETIN

OPERATOR MSN 18T 0473 19U 0399 40T 0413 50W 0498 58X 0431 82Z 0550 0551 83V 0407 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 PCA 0419 PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691 QAF 0667 R1T 0591 RJA 0445 0490 ROT 0636 0644 RZO 0571 0624 0651 SGX 0519 0562 SUD 0437 THY 0478 0480 TSC 0447 0472 0483 0545 0588 0597 0599 0600 0658 TXP 0565 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.: 03 - Jun 30/15 Page: 2 7

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

# @A310 SERVICE BULLETIN

MSN CONFIGURATION 0378 0399 0407 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 003 004

0419 002 (5) Configuration definition **CONF 001 Config. 001 is applicable to A310-200 aircraft that have Circuit Breaker Panel 127VU installed. **CONF 002 Config. 002 is applicable to A310-200 aircraft that have Circuit Breaker Panel 133VU installed. **CONF 003 Config. 003 is applicable to A310-300 aircraft with an average flight time of 4 hours or less than 4 hours (Short Range (SR) mission). **CONF 004 Config. 004 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.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 3 7

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

# @A310 SERVICE BULLETIN 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. (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 None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 572096-832-895-001: Inspection (1) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 (2) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 (3) Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 (4) Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 4 7

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

# @A310 SERVICE BULLETIN (5) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 (6) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 (7) Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 (8) Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 **CONF 002 Task 572096-832-895-001: Inspection (1) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 (2) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 (3) Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 (4) Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 (5) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 (6) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 (7) Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 (8) Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 **CONF 003 Task 572096-832-895-001: Inspection (1) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 (2) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 (3) Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 (4) Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 (5) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 (6) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 (7) Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 (8) Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 **CONF 004 Task 572096-832-895-001: Inspection (1) Detailed Inspection (DI) 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.: 03 - Jun 30/15 Page: 5 7

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

# @A310 SERVICE BULLETIN (2) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 (3) Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 2 (4) Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 2 (5) Detailed Inspection (DI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 (6) Detailed Inspection (DI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 (7) Special Detailed Inspection (SDI) of the LH Wing-skin Top Panels 1 and 2 at Rib 3 (8) Special Detailed Inspection (SDI) of the RH Wing-skin Top Panels 1 and 2 at Rib 3 **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale **CONF 001 thru 002 NOTE: Unless specified otherwise, the Flight Cycles (FC) and Flight Hours (FH) are from aircraft first flight. Table 01: Detailed Inspection (DI) and Special Detailed Inspection (SDI) of the LH and RH wing skin top panel 1 and 2 at Rib 2 and Rib 3 COMPLIANCE TIME CONDITION ACTION THRESHOLD REPETITIVE INTERVAL NOT TO EXCEED For A310-200 aircraft that are below 18700 FC / 37400 FH Do a Detailed Inspection (DI) of the LH and RH wing skin top panels 1 and 2 for cracks 18700 FC / 37400 FH (whichever occurs first) 2000 FC / 4100 FH (whichever occurs first)
If cracks are found Contact AIRBUS for repair instruction Before next flight If no cracks are found Do a Special Detailed Inspection (SDI) of the LH and RH wing skin top panels 1 and 2 for cracks 18700 FC / 37400 FH (whichever occurs first) 2000 FC / 4100 FH (whichever occurs first)

If cracks are found Contact AIRBUS for repair instruction Before next flight If no cracks are found Repeat the inspection 2000 FC / 4100 FH (whichever occurs first) NOTE: GRACE PERIODS
DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 6 7

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

# @A310 SERVICE BULLETIN 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 1700 FC / 3500 FH. This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Aviation Safety Agency (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. Table 01: Detailed Inspection (DI) and Special Detailed Inspection (SDI) of the LH and RH wing skin top panel 1 and 2 at Rib 2 and Rib 3 COMPLIANCE TIME CONDITION ACTION THRESHOLD REPETITIVE INTERVAL NOT TO EXCEED For A310-300 (SR) aircraft that are below 17300 FC / 48400 FH Do a Detailed Inspection of the LH and RH wing skin top panels 1 and 2 for cracks 17300 FC / 48400 FH (whichever occurs first) 2000 FC / 5600 FH (whichever occurs first)
If cracks are found Contact AIRBUS for repair instruction Before next flight If no cracks are found Do a Special Detailed Inspection of the LH and RH wing skin top panels 1 and 2 for cracks 17300 FC / 48400 FH (whichever occurs first) 2000 FC / 5600 FH (whichever occurs first)
If cracks are found Contact AIRBUS for repair instruction Before next flight If no cracks are found Repeat the inspection 2000 FC / 5600 FH (whichever occurs first) 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. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 7 7

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

# @A310 SERVICE BULLETIN 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 Aviation Safety Agency (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 004 NOTE: Unless specified otherwise, the Flight Cycles (FC) and Flight Hours (FH) are from aircraft first flight. Table 01: Detailed Inspection (DI) and Special Detailed Inspection (SDI) of the LH and RH wing skin top panel 1 and 2 at Rib 2 and Rib 3 COMPLIANCE TIME CONDITION ACTION THRESHOLD REPETITIVE INTERVAL NOT TO EXCEED For A310-300 (LR) aircraft that are below 12800 FC / 64300 FH Do a Detailed Inspection of the LH and RH wing skin top panels 1 and 2 for cracks 12800 FC / 64300 FH (whichever occurs first) 1500 FC / 7500 FH (whichever occurs first)
If cracks are found Contact AIRBUS for repair instruction Before next flight If no cracks are found Do a Special Detailed Inspection of the LH and RH wing skin top panels 1 and 2 for cracks 12800 FC / 64300 FH (whichever occurs first) 1500 FC / 7500 FH (whichever occurs first)
If cracks are found Contact AIRBUS for repair instruction Before next flight If no cracks are found Repeat the inspection 1500 FC / 7500 FH (whichever occurs first) 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. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 8 7

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

# @A310 SERVICE BULLETIN 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 Aviation Safety Agency (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 ALL F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. **CONF 001 Task 572096-832-895-001: Inspection Get Access 0.50 On Aircraft 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.: 03 - Jun 30/15 Page: 9 7

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

# @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 Close-Up 0.50 TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 8.00 **CONF 002 Task 572096-832-895-001: Inspection Get Access 0.50 On Aircraft 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 Close-Up 0.50 TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 8.00 **CONF 003 Task 572096-832-895-001: Inspection Get Access 0.50 On Aircraft 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
DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 10 7

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

# @A310 SERVICE BULLETIN
Task 572096-832-895-001: Inspection 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 Close-Up 0.50 TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 8.00 **CONF 004 Task 572096-832-895-001: Inspection Get Access 0.50 On Aircraft 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 Close-Up 0.50 TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 8.00 **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 11 7

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

# @A310 SERVICE BULLETIN
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 **CONF 004 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 ALL K. PUBLICATION AFFECTED

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.: 03 - Jun 30/15 Page: 12 7

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

# @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.: 03 - Jun 30/15 Page: 13 7

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

# @A310 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 14 7

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

# @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 flow charts 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.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 15 7

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

# @A310 SERVICE BULLETIN
Task Associated Data **CONF 001 Zone 210 510 610 Manpower TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 8.00 **CONF 002 Zone 210 510 610 Manpower TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 8.00 **CONF 003 Zone 210 510 610 Manpower TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 8.00 **CONF 004 Zone 210 510 610 Manpower TOTAL MANHOURS 8.00 ELAPSED TIME (HOURS) 8.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 572096-910-401-001 - 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) DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 16 7

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

# @A310 SERVICE BULLETIN

References 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 572096-839-401-001 - 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 572096-910-401-001 - 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 572096-839-401-001 - Administrative Manpower Resources Skills NON SPECIFIC DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 17 7

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

# @A310 SERVICE BULLETIN Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 003 (1) Subtask 572096-910-401-001 - 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 572096-839-401-001 - 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 004 (1) Subtask 572096-910-401-001 - 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). DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 18 7

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

# @A310 SERVICE BULLETIN (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 572096-839-401-001 - 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 572096-941-405-001 - 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 systems depressurized DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 19 7

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

# @A310 SERVICE BULLETIN - 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 572096-865-402-001 - 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 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 572096-941-405-001 - 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 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 20 7

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

# @A310 SERVICE BULLETIN
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 systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position. (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 572096-865-402-002 - 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
DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 21 7

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

# @A310 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 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 572096-941-405-001 - 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 systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 22 7

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

# @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 572096-865-402-002 - 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 004 (1) Subtask 572096-941-405-001 - 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.: 03 - Jun 30/15 Page: 23 7

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

# @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 systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position. (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 572096-865-402-002 - 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.: 03 - Jun 30/15 Page: 24 7

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

# @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 572096-832-403-001 - Detailed Inspection (DI) 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 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 NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 25 7

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

# @A310 SERVICE BULLETIN Design Approval Sheet. However the Rib 2 area not covered by the repair must be inspected in accordance with 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: 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. AURAAA Sheet 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 572096-832-404 001 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-URAAA Sheet 01 and return it to AIRBUS. (2) Subtask 572096-832-405-001 - Detailed Inspection (DI) 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

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 26 7

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

# @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 NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 area not covered by the repair must be inspected in accordance with 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

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 27 7

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

# @A310 SERVICE BULLETIN

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. AURAAA Sheet 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 572096-832-406 001 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-URAAA Sheet 01 and return it to AIRBUS.(3) Subtask 572096-832-404-001 - Special Detailed Inspection (SDI) of the LH Wingskin 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 Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 area not covered by the repair must be inspected in accordance with this Service Bulletin. Refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02

.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 28 7

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

# @A310 SERVICE BULLETIN (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. AURAAA Sheet 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 572096-832-409 001 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-URAAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’.(4) Subtask 572096-832-406-001 - Special Detailed Inspection (SDI) of the RH Wingskin 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 Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 area not covered by the repair must be inspected in accordance with this Service Bulletin. Refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02

.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 29 7

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

# @A310 SERVICE BULLETIN (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. AURAAA Sheet 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 572096-832-410 001 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-URAAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’. (5) Subtask 572096-832-409-001 - Detailed Inspection (DI) 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 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 NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URBAA Inspection report sheet Sheet 01
NOTE: 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 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 30 7

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

# @A310 SERVICE BULLETIN Design Approval Sheet. However the Rib 3 area not covered by the repair must be inspected in accordance with 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: 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. AURBAA Sheet 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 572096-832-410 001 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-URBAA Sheet 01 and return it to AIRBUS. (6) Subtask 572096-832-410-001 - Detailed Inspection (DI) 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

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 31 7

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

# @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 NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URBAA Inspection report sheet Sheet 01
NOTE: 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 3 area not covered by the repair must be inspected in accordance with 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

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 32 7

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

# @A310 SERVICE BULLETIN

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. AURBAA Sheet 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 572096-832-407 001 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-URBAA Sheet 01 and return it to AIRBUS.(7) Subtask 572096-832-408-002 - Special Detailed Inspection (SDI) of the LH Wingskin 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 Sheet 01 Sheet 02 Fig. A-URBAA Inspection report sheet Sheet 01 (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. AURBAA Sheet 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.: 03 - Jun 30/15 Page: 33 7

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

# @A310 SERVICE BULLETIN

2 If no cracks are found, restore the paint finish as necessary and go to SUBTASK 572096-942-402 001 Close-up

. Report the nil findings on the Inspection Report Sheet, Fig. A-URBAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’.(8) Subtask 572096-832-407-001 - Special Detailed Inspection (SDI) of the RH Wingskin 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 Sheet 01 Sheet 02 Fig. A-URBAA Inspection report sheet Sheet 01
NOTE: 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 3 area not covered by the repair must be inspected in accordance with 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. AURBAA Sheet 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.: 03 - Jun 30/15 Page: 34 7

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

# @A310 SERVICE BULLETIN

2 If no cracks are found, restore the paint finish as necessary and go to SUBTASK 572096-942-402 001 Close-up

. Report the nil findings on the Inspection Report Sheet, Fig. A-URBAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’. **CONF 002 (1) Subtask 572096-832-403-001 - Detailed Inspection (DI) 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 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 NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 area not covered by the repair must be inspected in accordance with this Service Bulletin. Refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02

.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 35 7

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

# @A310 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. 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. AURAAA Sheet 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 572096-832-404 001 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-URAAA Sheet 01 and return it to AIRBUS. (2) Subtask 572096-832-405-001 - Detailed Inspection (DI) 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 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.: 03 - Jun 30/15 Page: 36 7

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

# @A310 SERVICE BULLETIN
Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 area not covered by the repair must be inspected in accordance with 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.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 37 7

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

# @A310 SERVICE BULLETIN
3 If cracks are found, record all findings on the Inspection Report Sheet, Fig. AURAAA Sheet 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 572096-832-406 001 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-URAAA Sheet 01 and return it to AIRBUS.(3) Subtask 572096-832-404-001 - Special Detailed Inspection (SDI) of the LH Wingskin 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 Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 area not covered by the repair must be inspected in accordance with 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. AURAAA Sheet 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.: 03 - Jun 30/15 Page: 38 7

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

# @A310 SERVICE BULLETIN

2 If no cracks are found, restore the paint finish as necessary and go to SUBTASK 572096-832-409 001 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-URAAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’.(4) Subtask 572096-832-406-001 - Special Detailed Inspection (SDI) of the RH Wingskin 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 Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 area not covered by the repair must be inspected in accordance with 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. AURAAA Sheet 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.: 03 - Jun 30/15 Page: 39 7

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

# @A310 SERVICE BULLETIN

2 If no cracks are found, restore the paint finish as necessary and go to SUBTASK 572096-832-410 001 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-URAAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’. (5) Subtask 572096-832-409-001 - Detailed Inspection (DI) 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 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 NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URBAA Inspection report sheet Sheet 01
NOTE: 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 3 area not covered by the repair must be inspected in accordance with this Service Bulletin. Refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02

.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 40 7

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

# @A310 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. 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. AURBAA Sheet 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 572096-832-410 001 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-URBAA Sheet 01 and return it to AIRBUS. (6) Subtask 572096-832-410-001 - Detailed Inspection (DI) 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 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.: 03 - Jun 30/15 Page: 41 7

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

# @A310 SERVICE BULLETIN
Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URBAA Inspection report sheet Sheet 01
NOTE: 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 3 area not covered by the repair must be inspected in accordance with 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.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 42 7

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

# @A310 SERVICE BULLETIN
3 If cracks are found, record all findings on the Inspection Report Sheet, Fig. AURBAA Sheet 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 572096-832-407 001 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-URBAA Sheet 01 and return it to AIRBUS.(7) Subtask 572096-832-408-002 - Special Detailed Inspection (SDI) of the LH Wingskin 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 Sheet 01 Sheet 02 Fig. A-URBAA Inspection report sheet Sheet 01 (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. AURBAA Sheet 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 572096-942-402 001 Close-up

. Report the nil findings on the Inspection Report Sheet, Fig. A-URBAA 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.: 03 - Jun 30/15 Page: 43 7

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

# @A310 SERVICE BULLETIN(8) Subtask 572096-832-407-001 - Special Detailed Inspection (SDI) of the RH Wingskin 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 Sheet 01 Sheet 02 Fig. A-URBAA Inspection report sheet Sheet 01
NOTE: 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 3 area not covered by the repair must be inspected in accordance with 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. AURBAA Sheet 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 572096-942-402 001 Close-up

. Report the nil findings on the Inspection Report Sheet, Fig. A-URBAA 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.: 03 - Jun 30/15 Page: 44 7

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

# @A310 SERVICE BULLETIN
**CONF 003 (1) Subtask 572096-832-403-001 - Detailed Inspection (DI) 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 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 NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 area not covered by the repair must be inspected in accordance with 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:

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 45 7

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

# @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. AURAAA Sheet 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 572096-832-404 001 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-URAAA Sheet 01 and return it to AIRBUS. (2) Subtask 572096-832-405-001 - Detailed Inspection (DI) 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 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 NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 46 7

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

# @A310 SERVICE BULLETIN

References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 area not covered by the repair must be inspected in accordance with 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. AURAAA Sheet 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 572096-832-406 001 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-URAAA Sheet 01 and return it to AIRBUS.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 47 7

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

# @A310 SERVICE BULLETIN(3) Subtask 572096-832-404-001 - Special Detailed Inspection (SDI) of the LH Wingskin 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 Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 area not covered by the repair must be inspected in accordance with 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. AURAAA Sheet 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 572096-832-409 001 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-URAAA 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.: 03 - Jun 30/15 Page: 48 7

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

# @A310 SERVICE BULLETIN(4) Subtask 572096-832-406-001 - Special Detailed Inspection (SDI) of the RH Wingskin 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 Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 area not covered by the repair must be inspected in accordance with 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. AURAAA Sheet 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 572096-832-410 001 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-URAAA 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.: 03 - Jun 30/15 Page: 49 7

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

# @A310 SERVICE BULLETIN (5) Subtask 572096-832-409-001 - Detailed Inspection (DI) 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 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 NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URBAA Inspection report sheet Sheet 01
NOTE: 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 3 area not covered by the repair must be inspected in accordance with 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: Textile-Lint Free Cotton 14SBA1 As required

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 50 7

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

# @A310 SERVICE BULLETIN
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. AURBAA Sheet 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 572096-832-410 001 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-URBAA Sheet 01 and return it to AIRBUS. (6) Subtask 572096-832-410-001 - Detailed Inspection (DI) 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 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 NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02
DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 51 7

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

# @A310 SERVICE BULLETIN

References Fig. A-URBAA Inspection report sheet Sheet 01
NOTE: 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 3 area not covered by the repair must be inspected in accordance with 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. AURBAA Sheet 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 572096-832-407 001 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-URBAA Sheet 01 and return it to AIRBUS.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 52 7

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

# @A310 SERVICE BULLETIN(7) Subtask 572096-832-408-002 - Special Detailed Inspection (SDI) of the LH Wingskin 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 Sheet 01 Sheet 02 Fig. A-URBAA Inspection report sheet Sheet 01 (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. AURBAA Sheet 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 572096-942-402 001 Close-up

. Report the nil findings on the Inspection Report Sheet, Fig. A-URBAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’.(8) Subtask 572096-832-407-001 - Special Detailed Inspection (SDI) of the RH Wingskin Top Panels 1 and 2 at Rib 3 Work Zones and Access Panels Zone Access/Work location 610 Work location Rib 3

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 53 7

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

# @A310 SERVICE BULLETIN
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 Sheet 01 Sheet 02 Fig. A-URBAA Inspection report sheet Sheet 01
NOTE: 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 3 area not covered by the repair must be inspected in accordance with 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. AURBAA Sheet 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 572096-942-402 001 Close-up

. Report the nil findings on the Inspection Report Sheet, Fig. A-URBAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’. **CONF 004 (1) Subtask 572096-832-403-001 - Detailed Inspection (DI) 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

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 54 7

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

# @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 NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 area not covered by the repair must be inspected in accordance with 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: Non Aqueous Cleaner-General 08BAA9 As required

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 55 7

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

# @A310 SERVICE BULLETIN

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. AURAAA Sheet 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 572096-832-404 001 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-URAAA Sheet 01 and return it to AIRBUS. (2) Subtask 572096-832-405-001 - Detailed Inspection (DI) 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 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 NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 56 7

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

# @A310 SERVICE BULLETIN Design Approval Sheet. However the Rib 2 area not covered by the repair must be inspected in accordance with 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. AURAAA Sheet 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 572096-832-406 001 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-URAAA Sheet 01 and return it to AIRBUS.(3) Subtask 572096-832-404-001 - Special Detailed Inspection (SDI) of the LH Wingskin Top Panels 1 and 2 at Rib 2 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.: 03 - Jun 30/15 Page: 57 7

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

# @A310 SERVICE BULLETIN
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 Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 area not covered by the repair must be inspected in accordance with 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. AURAAA Sheet 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 572096-832-409 001 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-URAAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’.(4) Subtask 572096-832-406-001 - Special Detailed Inspection (SDI) of the RH Wingskin Top Panels 1 and 2 at Rib 2 Work Zones and Access Panels Zone Access/Work location 610 Work location Rib 2

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 58 7

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

# @A310 SERVICE BULLETIN
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 Sheet 01 Sheet 02 Fig. A-URAAA Inspection report sheet Sheet 01
NOTE: 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 area not covered by the repair must be inspected in accordance with 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. AURAAA Sheet 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 572096-832-410 001 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-URAAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’. (5) Subtask 572096-832-409-001 - Detailed Inspection (DI) 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

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 59 7

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

# @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 NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URBAA Inspection report sheet Sheet 01
NOTE: 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 3 area not covered by the repair must be inspected in accordance with 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: Textile-Lint Free Cotton 14SBA1 As required
made moist with: Non Aqueous Cleaner-General 08BAA9 As required

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 60 7

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

# @A310 SERVICE BULLETIN

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. AURBAA Sheet 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 572096-832-410 001 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-URBAA Sheet 01 and return it to AIRBUS. (6) Subtask 572096-832-410-001 - Detailed Inspection (DI) 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 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 NOTESNon Aqueous CleanerGeneral 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URBAA Inspection report sheet Sheet 01
NOTE: 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 DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 61 7

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

# @A310 SERVICE BULLETIN Design Approval Sheet. However the Rib 3 area not covered by the repair must be inspected in accordance with 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. AURBAA Sheet 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 572096-832-407 001 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-URBAA Sheet 01 and return it to AIRBUS.(7) Subtask 572096-832-408-002 - Special Detailed Inspection (SDI) of the LH Wingskin Top Panels 1 and 2 at Rib 3 Work Zones and Access Panels Zone Access/Work location 510 Work location Rib 3

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 62 7

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

# @A310 SERVICE BULLETIN
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 Sheet 01 Sheet 02 Fig. A-URBAA Inspection report sheet Sheet 01 (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. AURBAA Sheet 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 572096-942-402 001 Close-up

. Report the nil findings on the Inspection Report Sheet, Fig. A-URBAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’.(8) Subtask 572096-832-407-001 - Special Detailed Inspection (SDI) of the RH Wingskin 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

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 63 7

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

# @A310 SERVICE BULLETIN

References Fig. A-UBAAA Inspection area Sheet 01 Sheet 02 Fig. A-URBAA Inspection report sheet Sheet 01
NOTE: 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 3 area not covered by the repair must be inspected in accordance with 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. AURBAA Sheet 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 572096-942-402 001 Close-up

. Report the nil findings on the Inspection Report Sheet, Fig. A-URBAA Sheet 01 and return it to AIRBUS. (b) Repeat the inspection at the interval given in Paragraph 1.E.(2) ’Accomplishment Timescale’. **CONF ALL D. TEST **CONF 001 None **CONF 002 None **CONF 003 None **CONF 004 None

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 64 7

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

# @A310 SERVICE BULLETIN
**CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 572096-865-401-001 - C/B Closing Work Zones and Access Panels Zone Access/Work location 210 Work location Circuit Breaker Panel 127-VU Manpower Resources Skills ELECTRICAL (a) Close this/these circuit breakers: 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 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
(2) Subtask 572096-942-402-001 - Close-up Work Zones and Access Panels Zone Access/Work location 510 Work location from Rib 2 to Rib 3 610 Work location from Rib 2 to Rib 3 Manpower Resources Skills NON SPECIFIC (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Remove the access platforms clear of the aircraft. (c) Remove the warning notices. (d) Put the aircraft back to its initial configuration. DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 65 7

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

# @A310 SERVICE BULLETIN
**CONF 002 (1) Subtask 572096-865-401-002 - C/B Closing Work Zones and Access Panels Zone Access/Work location 210 Work location Circuit Breaker Panel 133-VU Manpower Resources Skills ELECTRICAL (a) Close this/these circuit breakers: 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
(2) Subtask 572096-942-402-001 - Close-up Work Zones and Access Panels Zone Access/Work location 510 Work location from Rib 2 to Rib 3 610 Work location from Rib 2 to Rib 3 Manpower Resources Skills NON SPECIFIC (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Remove the access platforms clear of the aircraft. (c) Remove the warning notices. (d) Put the aircraft back to its initial configuration.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 66 7

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

# @A310 SERVICE BULLETIN
**CONF 003 (1) Subtask 572096-865-401-002 - C/B Closing Work Zones and Access Panels Zone Access/Work location 210 Work location Circuit Breaker Panel 133-VU Manpower Resources Skills ELECTRICAL (a) Close this/these circuit breakers: 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
(2) Subtask 572096-942-402-001 - Close-up Work Zones and Access Panels Zone Access/Work location 510 Work location from Rib 2 to Rib 3 610 Work location from Rib 2 to Rib 3 Manpower Resources Skills NON SPECIFIC (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Remove the access platforms clear of the aircraft. (c) Remove the warning notices. (d) Put the aircraft back to its initial configuration.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 67 7

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

# @A310 SERVICE BULLETIN
**CONF 004 (1) Subtask 572096-865-401-002 - C/B Closing Work Zones and Access Panels Zone Access/Work location 210 Work location Circuit Breaker Panel 133-VU Manpower Resources Skills ELECTRICAL (a) Close this/these circuit breakers: 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
(2) Subtask 572096-942-402-001 - Close-up Work Zones and Access Panels Zone Access/Work location 510 Work location from Rib 2 to Rib 3 610 Work location from Rib 2 to Rib 3 Manpower Resources Skills NON SPECIFIC (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Remove the access platforms clear of the aircraft. (c) Remove the warning notices. (d) Put the aircraft back to its initial configuration.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 68 7

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

# @A310 SERVICE BULLETIN

**CONF ALL


### A A

LH SHOWN RH SIMILAR 

## A FRONT SPAR

REAR SPAR Z500 Z600

TOP SKIN PANEL 1

TOP SKIN PANEL 2

TOP SKIN PANEL 3 RIB3 RIB2


### B

B_SB_572096_7_BAAA_01_01 Figure A-UBAAA - Sheet 01 Inspection area DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 69 7

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

# @A310 SERVICE BULLETIN

**CONF ALL

AREA TO BE INSPECTED BY SDI. FASTENERS TO BE INSPECTED BY SDI. 01REAR SPAR DATUM

TYPICAL STRINGER/RIB FASTENER ARRANGEMENT RIB1 DATUM RIB2

STGR2 STGR3 STGR4 STGR5 STGR6 STGR7 STGR8
STGR9 STGR10 STGR11 STGR12 STGR13 STGR14 STGR15 STGR16 STGR17 

### C

TYPICAL CRACK 01

01 F W D INBD 

## B RIB3 FRONT SPAR DATUM

SKIN PANEL 1

SKIN PANEL 2



## C C

AREA TO BE INSPECTED BY DI. NOTE:

B_SB_572096_7_BAAA_02_02 Figure A-UBAAA - Sheet 02 Inspection area DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 70 7

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

# @A310 SERVICE BULLETIN

**CONF 001 thru 002

CRACK FOUND ON WING

TOP SKIN AT RIB 2

DO AN SDI WITHIN THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

CRACK FOUND ON WING

TOP SKIN AT RIB 2

REPEAT THE DI AND THE SDI BEFORE THE COMPLIANCE CONTACT AIRBUS FOR REPAIR INSTRUCTIONS TIMES GIVEN IN PARA 1.E (2) BEFORE NEXT FLIGHT

QUESTION ACTION FINDING NO YES NO YES

NOTE: THE PURPOSE OF FLOW CHARTS 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. ALL A310

−200 AIRCRAFT

DO A DI WITHIN THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

B_SB_572096_7_FAAA_01_03 Figure A-UFAAA - Sheet 01 Flowchart DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 71 7

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

# @A310 SERVICE BULLETIN

**CONF 003

QUESTION ACTION FINDING NOTE: THE PURPOSE OF FLOW CHARTS 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. ALL A310

−300 SHORT RANGE AIRCRAFT

CRACK FOUND ON WING

TOP SKIN AT RIB 2

DO AN SDI WITHIN THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

CRACK FOUND ON WING

TOP SKIN AT RIB 2

CONTACT AIRBUS FOR REPAIR INSTRUCTIONS BEFORE NEXT FLIGHT NO YES NO YES DO A DI WITHIN THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

REPEAT THE DI AND THE SDI BEFORE THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

B_SB_572096_7_FAAB_01_03 Figure A-UFAAB - Sheet 01 Flowchart DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 72 7

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

# @A310 SERVICE BULLETIN

**CONF 004

QUESTION ACTION FINDING NOTE: THE PURPOSE OF FLOW CHARTS 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. ALL A310

−300 LONG RANGE AIRCRAFT

CRACK FOUND ON WING

TOP SKIN AT RIB 2

DO AN SDI WITHIN THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

CRACK FOUND ON WING

TOP SKIN AT RIB 2

CONTACT AIRBUS FOR REPAIR INSTRUCTIONS BEFORE NEXT FLIGHT NO YES NO YES DO A DI WITHIN THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

REPEAT THE DI AND THE SDI BEFORE THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

B_SB_572096_7_FAAC_01_03 Figure A-UFAAC - Sheet 01 Flowchart DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 73 7

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

# @A310 SERVICE BULLETIN

**CONF 001 thru 002

CRACK FOUND ON WING

TOP SKIN AT RIB 3

DO AN SDI WITHIN THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

CRACK FOUND ON WING

TOP SKIN AT RIB 3

REPEAT THE DI AND THE SDI BEFORE THE COMPLIANCE CONTACT AIRBUS FOR REPAIR INSTRUCTIONS TIMES GIVEN IN PARA 1.E (2) BEFORE NEXT FLIGHT NO YES NO YES

NOTE: THE PURPOSE OF FLOW CHARTS 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. ALL A310

−200 AIRCRAFT

DO A DI WITHIN THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

B_SB_572096_7_FBAA_01_00 Figure A-UFBAA - Sheet 01 Flowchart DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 74 7

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

# @A310 SERVICE BULLETIN

**CONF 003

NOTE: THE PURPOSE OF FLOW CHARTS 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. ALL A310

−300 SHORT RANGE AIRCRAFT

CRACK FOUND ON WING

TOP SKIN AT RIB 3

DO AN SDI WITHIN THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

CRACK FOUND ON WING

TOP SKIN AT RIB 3

CONTACT AIRBUS FOR REPAIR INSTRUCTIONS BEFORE NEXT FLIGHT NO YES NO YES DO A DI WITHIN THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

REPEAT THE DI AND THE SDI BEFORE THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

B_SB_572096_7_FBAB_01_00 Figure A-UFBAB - Sheet 01 Flowchart DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 75 7

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

# @A310 SERVICE BULLETIN

**CONF 004

NOTE: THE PURPOSE OF FLOW CHARTS 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. ALL A310

−300 LONG RANGE AIRCRAFT

CRACK FOUND ON WING

TOP SKIN AT RIB 3

DO AN SDI WITHIN THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

CRACK FOUND ON WING

TOP SKIN AT RIB 3

CONTACT AIRBUS FOR REPAIR INSTRUCTIONS BEFORE NEXT FLIGHT NO YES NO YES DO A DI WITHIN THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

REPEAT THE DI AND THE SDI BEFORE THE COMPLIANCE TIMES GIVEN IN PARA 1.E (2)

B_SB_572096_7_FBAC_01_00 Figure A-UFBAC - Sheet 01 Flowchart DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 76 7

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

# @A310 SERVICE BULLETIN

**CONF ALL 

## INSPECTION REPORT SERVICE BULLETIN No: DATE OF INSPECTION: AIRCRAFT MSN: FLIGHT CYCLES (FC): RETURN TO: AIRBUS

1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE CUSTOMER SERVICES ENGINEERING

−SEES2

FAX +33 (0)5 61 93 36 14 Email: A310

−57

−2096

FLIGHT HOURS (FH):

DETAILED INSPECTION (VISUAL) AND SPECIAL DETAILED INSPECTION (ULTRASONIC PHASE ARRAY) OF LH AND RH WING TOP SKIN PANELS 1 AND 2 AT RIB 2 FOR CRACKS

B_SB_572096_7_RAAA_01_00 WING FIX STRUCTURE

INSPECTION METHOD:

NOTE:

01 USE THE REPAIR DRAWING, WING SKIN BOLT LOCATION DIAGRAM R57140308, SHEETS 2 AND 4 TO IDENTIFY FASTENER POSITIONS WHEN REPORTING WING SKIN CRACKS. LH OR RH CRACK FINDINGS (DI) Y/N CRACK FINDINGS (SDI) Y/N FASTENER POSITION (R57140308) LENGTH OF CRACK mm (in) 01 DETAILED INSPECTION SPECIAL DETAILED INSPECTION structure.sbinspectionresult@airbus.com

Figure A-URAAA - Sheet 01 Inspection report sheet DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 77 7

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

# @A310 SERVICE BULLETIN

**CONF ALL 

## INSPECTION REPORT SERVICE BULLETIN No: DATE OF INSPECTION: AIRCRAFT MSN: FLIGHT CYCLES (FC): RETURN TO: AIRBUS

1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE CUSTOMER SERVICES ENGINEERING

−SEES2

FAX +33 (0)5 61 93 36 14 Email: A310

−57

−2096

FLIGHT HOURS (FH):

DETAILED INSPECTION (VISUAL) AND SPECIAL DETAILED INSPECTION (ULTRASONIC PHASE ARRAY) OF LH AND RH WING TOP SKIN PANELS 1 AND 2 AT RIB 3 FOR CRACKS WING FIX STRUCTURE

INSPECTION METHOD:

NOTE:

01 USE THE REPAIR DRAWING, WING SKIN BOLT LOCATION DIAGRAM R57140308, SHEETS 2 AND 4 TO IDENTIFY FASTENER POSITIONS WHEN REPORTING WING SKIN CRACKS. LH OR RH CRACK FINDINGS (DI) Y/N CRACK FINDINGS (SDI) Y/N FASTENER POSITION (R57140308) LENGTH OF CRACK mm (in) 01 DETAILED INSPECTION SPECIAL DETAILED INSPECTION structure.sbinspectionresult@airbus.com

B_SB_572096_7_RBAA_01_00 Figure A-URBAA - Sheet 01 Inspection report sheet DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 78 7

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

# @A310 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS - INSPECTION OF WING TOP SKIN PANEL 1 AND 2 AT RIB 2 AND RIB 3 MODIFICATION No.: None Please complete the appropriate item (A or B): A - SB WILL BE embodied YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:

B - SB HAS BEEN embodied on aircraft: Operator comments:
From Airline: Name/Title: Signature: Date: If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either: Modification Operational Impact (MOI), if available YES/NO Or : Intermediate revision YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - Updating of maintenance documentation to show pre and post SB data. - Updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. Please return this completed sheet to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: SDC32 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 1 7

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

# @A310 SERVICE BULLETIN QUALITY PERCEPTION FORM Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4321 - Quality rating of the Accomplishment Instructions 4321 - Quality rating of the Illustrations 4321 - Is this SB easy to understand ? Y/N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials Operator Supplied X Mod/Inspection X Manpower X Industry support X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments:

Operator: Date: Name/Title: Please return this form to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096 REVISION No.: 03 - Jun 30/15 Page: 1 7

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