@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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - INSPECTION OF WING TOP SKIN PANEL 1 AND 2 AT RIB 2

AND RIB 3

MODIFICATION No.: None

This page transmits Revision No.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

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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

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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

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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

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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.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - INSPECTION OF WING TOP SKIN PANEL 1 AND 2 AT RIB 2

AND RIB 3

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Following scheduled maintenance, an operator reported cracks around fastener holes in the wing top

skin panels 1 and 2 at Rib 2 on a number of A310 aircraft.

Following Widespread Fatigue Damage (WFD) analysis the inspection programme is extended to cover

wing top skin panels at both Rib 2 and Rib 3 attachments.

The first crack was found during the refuelling of an aircraft in February 2006 when a visible fuel stain

occurred at the crack. During the subsequent repair procedure further cracks were found by rotary eddy

current inspection. All the cracks were in the Rib 2 area. The Operator carried out a fleet check and a

further five aircraft were found to have cracks around fastener holes in the Rib 2 area.

All the cracks were located at Rib 2 (LH and RH) between Stringers 2 and 14 and emanated from the

fastener holes, generally in a forward and aft direction. The crack lengths varied from between 2.50 mm

(0.098in.) to 25 mm (0.98in.) and were found on aircraft having accumulated between approximately

19300 Flight Cycles (FC) and 24800 FC.

This Service Bulletin revision requires repeat inspection of the top skin panels 1 and 2 at Rib 2 and Rib

3. Detailed Inspections (DI) are required between the front and rear spars. Special Detailed Inspections

(SDI) using an ultrasonic phased array technique are required to detect cracks around the fastener

holes between stringers 2 and 10. The SDI will enable earlier detection of cracks with a length from

1.50 mm (0.059 in.). Early detection of damage will reduce the scope of potential repair action.

For those aircraft that have already been repaired, then the inspection requirements of this Service

Bulletin are not applicable to the repaired area. The repaired area must be inspected in accordance

with the Repair Design Approval Sheet. However the Rib 2 and Rib 3 area not covered by the repair

must be inspected in accordance with this Service Bulletin.

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096

REVISION No.: 03 - Jun 30/15 Page: 1

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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

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@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

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@A310

SERVICE BULLETIN

SUMMARY

**CONF ALL

Z500

Z600

NOTE:

INSPECTION AREA.

LH SHOWN

RH SIMILAR

A

FRONT SPAR

TOP SKIN PANEL 1 REAR SPAR

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

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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

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - INSPECTION OF WING TOP SKIN PANEL 1 AND 2 AT RIB 2

AND RIB 3

MODIFICATION No.: None

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

310-203 310-221 310-222 310-304 310-308 310-322 310-324 310-325

(2) Effectivity by MSN

0162 0230 0245 0248 0267 0278 0281 0283 0331 0356 0362 0364 0369 0378 0394

0399 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

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@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

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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

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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

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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

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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

CONDITION ACTION COMPLIANCE TIME

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

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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

CONDITION ACTION COMPLIANCE TIME

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

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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

CONDITION ACTION COMPLIANCE TIME

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

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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

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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

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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

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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

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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

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This Page Intentionally Left Blank

DATE: May 06/08 SERVICE BULLETIN No.: A310-57-2096

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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

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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)

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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

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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).

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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

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- 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

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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

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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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

NOTES

Non Aqueous CleanerGeneral08BAA9 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

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@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

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@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

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@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

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@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.

01 FASTENERS TO BE INSPECTED BY SDI.

REAR 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 B INBD

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

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@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

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@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

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@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

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@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

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