A310

A310

REVISION No. : 

7 -2046

07

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS INDUSTRIE

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice BELLONTE

31707 BLAGNAC CEDEX FRANCE

Tel: (33) 5 61-93-33-33

Telex: AIRBU 530526 F

TITLE : WINGS - INSPECTION OF REAR SPAR AT SELECTED BOLT LOCATIONS FOR

ATTACHMENT OF MLG FORWARD PICK-UP FITTING.

MODIFICATION No. : NONE ATA SYSTEM : 57

This page transmits Revision No. 07 of Service Bulletin No. A310-57-2046.

ADDITIONAL WORK

No additional inspection/work is necessary to do this revision.

REASON

Investigations have established that for aircraft with Modification No.

07601H1085 embodied (Provide Cold Expansion of Attachment Holes) the

inspection requirement of this Service Bulletin is not required.

Therefore the inspection requirement of this Service Bulletin for these

aircraft is cancelled (aircraft MSN 547 and subsequent).

This revision has been issued to remove post Mod. No. 07601H1085 aircraft

from the effectivity of this Service Bulletin.

A paragraph has also has been added to state that if Modification No.

11578H5436 (Service Bulletin A310-57-2074) is embodied after 3,800 FC for

A310-200 aircraft and after 4,600 FC for A310-300 aircraft then the

inspection requirements of this Service Bulletin are cancelled.

CHANGES

Summary:

- aircraft EFFECTIVITY updated.

Service Bulletin:

Planning information

- Para. 1. A. (2) - aircraft EFFECTIVITY updated and NOTE added.

- Para. 1. B. (5) (c) - statement re-worded.

- Para. 1. B. (5) (h) - new statement added.

Layout changes due to the computerization of this Service Bulletin are not

identified.

FILING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as

a complete document. Replace the complete Service Bulletin.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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REVISION No. : 

-2046

0707

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This is only applicable to Revision No. 02 and subsequent. If

information is required for Revisions issued previous to this,

please check your copies of Revision Transmittal Sheets or contact

Airbus Industrie.

- Revision No. 02 was issued to include new inspection requirements

and to incorporate Change Notice No. 1A.

- Revision No. 03 was issued to ammend the effectivity and the

jacking points.

- Revision No. 04 was issued to change the inspection method from

HFEC to Ultrasonic.

- Revision No. 05 was issued to simplify the instructions with

regard to the HFEC inspections and the embodiment of Modification

No. 07925H1113.

- Revision No. 06 was issued to state that Modification No.

11578H5436 (SB A310-57-2074) only takes the aircraft to Design Life

Goal (DLG) if it is embodied after 3800 flight cycles (FC) for

A310-200 aircraft, or after 4600 FC for A310-300 aircraft. The

content of Change Notice 4A, which corrects the AMM reference and

the access doors for gaining access to the inboard fuel tanks was

also included.

REVISION SEQUENCE

ORIGINAL : MAR 05/90

REVISION No. : 01 - MAY 24/93

REVISION No. : 02 - MAR 22/95

REVISION No. : 03 - OCT 17/95

REVISION No. : 04 - OCT 16/96

REVISION No. : 05 - MAR 18/98

REVISION No. : 06 - JUN 19/98

REVISION No. : 07 - Apr 02/99

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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REVISION No. : 

7 -2046

0707

SERVICE BULLETIN

SUMMARY

AIRBUS INDUSTRIE

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice BELLONTE

31707 BLAGNAC CEDEX FRANCE

Tel: (33) 5 61-93-33-33

Telex: AIRBU 530526 F

This summary is for information only

and is not approved for modification of the aircraft

TITLE : WINGS - INSPECTION OF REAR SPAR AT SELECTED BOLT LOCATIONS FOR

ATTACHMENT OF MLG FORWARD PICK-UP FITTING.

MODIFICATION No. : NONE ATA SYSTEM : 57

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During full-scale fatigue testing, at approximately 90000 simulated

flights, cracks were discovered in the rear spar starting from certain

bolt holes at the attachment of the MLG forward pick-up fitting.

There is a possibility of similar cracks appearing on aircraft in service

which, if allowed to continue beyond repairable limits, may require

extensive and costly repairs.

The initial issue and Revisions 1 thru 03 of this Service Bulletin

required mandatory High Frequency Eddy Current (HFEC) inspections of

certain bolt holes where the MLG forward pick-up fittings are attached to

the rear spar. This required the fasteners to be removed. Revision 04 of

this Service Bulletin replaced the HFEC inspection with an ultrasonic

(US) inspection which does not require the fasteners to be removed.

Mandatory US inspections are required at certain bolt holes where the MLG

forward pick-up fittings are attached to the rear spar. The inspections

are to be done in accordance with the time scales that follow :

- Pre Mod. 07925H1113, A310-200 Aircraft have an inspection threshold of

12000 FC and an inspection interval of 3500 FC.

- Pre Mod. 07925H1113, A310-300 Aircraft have an inspection threshold of

9000 FC and an inspection interval of 3100 FC.

EFFECTIVITY

This Service Bulletin is applicable to these customers :

AFR, AIB, AIC, ANG, AUA, BAF, CCA, CFC, CYP, DAH, DGA, DLH, DYA, FDX, 

GAF, HLF, KQA, NGA, RJA, SAB, SIA, SWR, TAP, THA, THY, UAE, WDA, XB, XC,

XF, ZB. 

NOTE : This Service Bulletin is not applicable to post Mod. No.

07601H1085 aircraft (aircraft MSN 547 and subsequent).

SERVICE BULLETIN TO BE ACCOMPLISHED 

PREVIOUSLY OR SIMULTANEOUSLY

None

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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REVISION No. : 

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SERVICE BULLETIN

SUMMARY

REFERENCES/REPERCUSSIONS

TFU : None

OEB : None

AOT : None

SIL : None

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

OTHER : None

NATURE OF THE WORK

AIRCRAFT : Yes.

EQUIPMENT : No.

HARD : No.

SOFT : No.

OBRM : No.

COMPLIANCE

Mandatory.

MANPOWER

Manhours

TOTAL MANHOURS 26.0

ELAPSED TIME (HOURS) 14.0

MATERIAL INFORMATION

AIRCRAFT DATA

None

EQUIPMENT DATA

None

APPENDICES

None

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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Printed in France
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A310

REVISION No. : 

7 -2046

0707

SERVICE BULLETIN

AIRBUS INDUSTRIE

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice BELLONTE

31707 BLAGNAC CEDEX FRANCE

Tel: (33) 5 61-93-33-33

Telex: AIRBU 530526 F

TITLE : WINGS - INSPECTION OF REAR SPAR AT SELECTED BOLT LOCATIONS FOR

ATTACHMENT OF MLG FORWARD PICK-UP FITTING.

MODIFICATION No. : NONE ATA SYSTEM : 57

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Aircraft models : A310-203, A310-204, A310-221, A310-222,

A310-304, A310-308, A310-322, A310-324,

A310-325

(2) Aircraft

Customer and

Fleet No.

MSN Kit No. Qty

of kits

Config

572046 No.

AFR001-005 316,326,335,355,369

051 454

061-062 502,504

AIB001-009 439,442,449,452,453,456,

457,458,467

101-105 267,276,278,318,331

AIC301-308 392,406,407,413,428,429,

538,544

ANG001-002 378,549

AUA401-402 489,492

BAF001-002 367,372

CCA031-032 435,440

CFC001-005 446,482,425,444,441

CYP001-003 300,309,352

051 486

DAH001-004 291,293,295,306

DGA001-002 421,422

DLH553-559 485,488,522,524,526,527

557-559 524,526,527

DYA001 473

FDX401-405 191,201,230,233,237

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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REVISION No. : 

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SERVICE BULLETIN

Customer and

Fleet No.

MSN Kit No. Qty

of kits

Config

572046 No.

407-430 254,257,273,356,359,360,

397,400,349,288,333,343,

345,339,342,346,281,241,

264,245,362,248,364,394

442-443 353,283

445-450 297,224,251,260,217,162

GAF001-006 498,499,503,434,484,523

HLF401-404 427,430,468,487

451-452 520,528

KQA001-003 416,426,519

NGA001-004 270,285,329,340

RJA003-006 445,490,491,531

SAB401-402 303,313

451 437

SIA101-104 347,350,357,363

121-126 433,443,493,500,501,534

SWR226-229 399,404,409,410

251 412

TAP501-504 483,494,495,541

THA001-002 415,424

THY001-008 338,375,379,386,370,389,

390,172

021-026 476,478,480,496,497,537

UAE001-003 432,436,545

WDA801 418

807-811 447,448,472,475,481

XB001 431

XC001-002 311,320

021 419

XF601 535

ZB052-053 451,455

101-102 539,542

NOTE : This Service Bulletin is not applicable to post Mod. No.

07601H1085 aircraft (aircraft MSN 547 and subsequent).

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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A310

REVISION No. : 

-2046

0707

SERVICE BULLETIN

This document contains Airbus Industrie PROPRIETARY INFORMATION and

shall at all times remain the property of Airbus Industrie; no

intellectual property right or licence is granted by Airbus

Industrie 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 for performing the tasks described hereunder and provided

that any recipient of such document shall comply with the

conditions herein), without Airbus Industrie’s prior written

consent.

(3) Spares

None

B. REASON

(1) History

During full-scale fatigue testing, at approximately 90000 simulated

flights, cracks were discovered in the rear spar starting from

certain bolt holes at the attachment of the MLG forward pick-up

fitting. There is a possibility of similar cracks appearing on

aircraft in service.

Modification No. 07925H1113 (Service Bulletin A310-57-2049) was

introduced to cold expand the bolt holes covered by this inspection

and to install oversize studs. However, this did not take the

aircraft to its Design Life Goal (DLG).

Modification 07925H1113 has been superseded by Modification No.

11578H5436 (SB A310-57-2074). Embodiment of Modification No.

11578H5436 (SB A310-57-2074) after 3800 flight cycles (FC) for

A310-200 aircraft, or after 4600 FC for A310-300 aircraft will take

the aircraft to the DLG and cancel the inspection requirements of

this Service Bulletin.

Modification No. 11578H5436 (SB A310-57-2074) is recommended for

embodiment at 12000 flight cycles (FC) on A310-200 aircraft and at

9000 FC on A310-300 aircraft.

Production Modification 07601H1085 introduced cold working of all

attachment holes through the rear spar for the undercarriage

support rib and forward MLG pick-up fitting on A310-300 aircraft.

The cold working gave an improvement over the original basic

fatigue life but did not take the aircraft to DLG. The modification

is embodied on MSN 547 and subsequent. The inspection requirements

for the post Mod. 07601H1085 aircraft are detailed in the

Maintenance Review Board Document, SSI 57.21.16.

Revision 4 of this Service Bulletin was issued to change the

inspection method from HFEC to US. The US inspection does not

require bolt removal or jacking of the aircraft. However, the

inspection intervals are reduced.

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

- Apr 02/99 PAGE : 3

Printed in France
Aircraft

Inspection Threshold

(FC) Inspection Interval (FC)

A310-200 Pre Mod. 07925H1113 12000 3500

A310-300 Pre Mod. 07925H1113 9000 3100

Aircraft

Inspection Threshold

(FC)

Inspection Interval

(FC)

A310-200 Post Mod. 07925H1113 18000 11600

A310-300 Post Mod. 07925H1113 15000 6300

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REVISION No. : 

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(2) Objective/Action

Mandatory Ultrasonic (US) inspections are required at certain bolt

holes where the MLG forward pick-up fittings are attached to the

rear spar.

(3) Advantages

Early detection of cracks is beneficial as significant cracking in

this area would require very extensive and costly repairs.

(4) Operational/Maintenance Consequences

None

(5) Accomplishment Timescale

(a) The accomplishment of this Service Bulletin is rendered

Mandatory by Airworthiness Directive (Consigne de Navigabilite)

No. 92-106-132B.

(b) Mandatory Ultrasonic (US) inspections are required at certain

bolt holes where the MLG forward pick-up fitting is attached to

the rear spar not later than the following.

(c) If the spar is reworked, by embodiment of Modification

07925H1113 (SB A310-57-2049), the subsequent mandatory US

inspections are required after embodiment of the modification:

(d) Where cracks are found at the first inspection, the repeat

inspection interval will be dependent on the extent of the

damage and the repairs that have been done.

(e) Where HFEC inspections have already been done in accordance

with Revision 0 to 03 of this Service Bulletin and: (1) No

cracks were found and (2) Modification 07925H1113 (SB

A310-57-2049) has not been done.

Mandatory US inspections are required as follows :

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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Printed in France
Aircraft Model Next Inspection Interval (FC)

Subsequent Repeat Inspections

(FC)

A310-200 5000 * 3500

A310-300 4300 * 3100

Aircraft Model Inspection Threshold (FC) Inspection Interval (FC)

A310-200 18000 11600

A310-300 15000 6300

Aircraft Model Inspection Threshold (FC) Inspection Interval (FC)

A310-200 12000 11600

A310-300 9500 6300

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REVISION No. : 

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SERVICE BULLETIN

* Next inspection interval taken from time of last HFEC

inspection.

(f) Where an HFEC inspection has already been done in accordance

with Revision 0 to 03 of this Service Bulletin and: (1) No

cracks were found and (2) Modification 07925H1113 (SB

A310-57-2049) has subsequently been embodied at or before 12000

FC for A310-200 aircraft and at or before 9000 FC for A310-300

aircraft.

The following mandatory US inspections are required after

embodiment of the modification:

(g) Where HFEC inspections have already been done in accordance

with Revision 0 to 03 of this Service Bulletin and: (1) No

cracks were found and (2) Modification 07925H1113 (SB

A310-57-2049) has subsequently been embodied after 12000 FC for

A310-200 aircraft and after 9000 FC for A310-300 aircraft.

The subsequent mandatory US inspections are required after the

embodiment of the modification:

NOTE : Repair Instruction R571-49305, where no holes have

been bushed, is equivalent to Service Bulletin

A310-57-2049 for the purposes of paragraphs (f) and

(g).

(h) If Modification No. 11578H5436 (Service Bulletin A310-57-2074)

is embodied after 3,800 FC for A310-200 aircraft and after

4,600 FC for A310-300 aircraft then the inspection requirements

of this Service Bulletin are cancelled.

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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REVISION No. : 

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SERVICE BULLETIN

C. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

(1) Defuel the aircraft.

(2) Get access to the inboard fuel tanks.

(3) Identify the selected bolts/studs at the MLG forward pick-up

fitting.

(4) Do a US inspection of the selected bolt/stud holes of the MLG

forward pick-up fitting.

(5) Do approved repairs if cracks are found.

(6) Close-up.

D. APPROVAL

This Service Bulletin is approved by the Direction Generale de

l’Aviation Civile France (DGAC).

E. MANPOWER

This Service Bulletin is written for an aircraft in a maintenance

condition. The manhours/elapsed time estimates do not include the time

to prepare for the inspection, non-productive elapsed time or

administration.

Manhours

Get access 5.0

Inspection 16.0

Close-up 5.0

TOTAL MANHOURS 26.0

ELAPSED TIME (HOURS) 14.0

F. MATERIAL - COST AND AVAILABILITY

None

G. TOOLING - PRICE AND AVAILABILITY

None

H. WEIGHT AND BALANCE

No change

I. REFERENCES

Aircraft Maintenance Manual (AMM) : 28-00-00, 28-25-00, 28-11-23

Nondestructive Testing Manual (NTM) : Part 4 57-21-24

Structural Repair Manual (SRM) : 51-10-13, 51-76-20

Service Bulletins (SB) : A310-57-2049, A310-57-2074

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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REVISION No. : 

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SERVICE BULLETIN

Maintenance Review Board Document (MRBD) : SSI 57.21.16

Consumable Materials List (CML) :

J. PUBLICATIONS AFFECTED

None

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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REVISION No. : 

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SERVICE BULLETIN

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REVISION No. : 

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2. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL

WARNING : LANDING GEAR - MAKE SURE THAT THE GROUND SAFETIES ARE IN

POSITION.

FLIGHT CONTROLS - MAKE SURE THAT THE GROUND SAFETIES AND

NOTICES ARE IN POSITION.

WARNING : OBEY THE SAFETY PRECAUTIONS LISTED IN AMM 28-00-00, PAGE

BLOCK 301.

WARNING : OBEY ALL THE WARNINGS AND ALL THE CAUTIONS LISTED IN THE

REFERENCED PROCEDURES.

NOTE : These instructions are applicable to both LH and RH wings unless

stated otherwise.

(1) Preparation

(a) Drain the fuel tanks (Refer to AMM: 28-00-00,, P. Block 301 and

AMM: 28-25-00, P. Block 301).

(b) Get access to the inboard fuel tanks via the access doors

540/640 CB (Refer to AMM: 28-11-23,, P. Block 401).

(c) Remove the sealant from the area to be inspected in the fuel

tank (Refer to Refer to Figure 1 ).

(2) Standard Practices

None

B. INSPECTION

Refer to Refer to Figure 1 

(1) Do a US inspection of the bolt/stud holes (Refer to NTM: Part 4,

57-21-24).

(a) Where no cracks are found, refer to paragraph 2.E. and

close-up.

NOTE : If it is desired and if the aircraft has not been

modified in accordance with Service Bulletin

A310-57-2049, the selected fastener holes may be cold

expanded in accordance with Service Bulletin

A310-57-2074.

(b) If cracks are found, refer to paragraph 2.C. and do a repair as

necessary.

(c) Report all crack findings, including no findings, to AI/SE-A

(Refer to SRM: 51-10-13,, P. Block 1).

C. REPAIR

If any cracks are indicated, report the details to AI/SE-A (Refer to SRM:

51-10-13,, P. Block 1) and do an approved repair before the next flight.

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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REVISION No. : 

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SERVICE BULLETIN

D. TEST

None

E. CLOSE-UP

(1) Apply sealant to the inspection area in the fuel tank (Refer to SRM:

51-76-20).

(2) Make sure that the inspection/repair areas are clean and clear of

tools and other items of equipment.

(3) Close the access doors 540/640 CB (Refer to AMM: 28-11-22,, P. Block

401).

F. DOCUMENTATION

Write in the applicable aircraft technical records that you have done all

the work given in this Service Bulletin.

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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Figure 1 Sheet 1

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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Hole Positions to be Inspected.
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REVISION No. : 

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DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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3. MATERIAL INFORMATION

None

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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REVISION No. : 

7 -2046

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SERVICE BULLETIN

ACCEPTANCE/REJECTION SHEET

AIRBUS INDUSTRIE

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice BELLONTE

31707 BLAGNAC CEDEX FRANCE

Tel: (33) 5 61-93-33-33

Telex: AIRBU 530526 F

TITLE : WINGS - INSPECTION OF REAR SPAR AT SELECTED BOLT LOCATIONS FOR

ATTACHMENT OF MLG FORWARD PICK-UP FITTING.

MODIFICATION No. : NONE ATA SYSTEM : 57

IS BEING HEREWITH SUBMITTED TO YOU FOR REVIEW

Please fill : ...REJECTED

...WILL BE EMBODIED

...EFFECTIVITY

This SB can only be incorporated in your "customized"

documentation within the agreed time schedule in so far as this

sheet returned to us on purchase date and signed by a duly

authorized and empowered officer or representative.

FROM :

AIRLINE :

NAME :

DATE :

Please return to :

AIRBUS INDUSTRIE

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : AI/SE-D32 Technical Data

and Documentation Services

FAX : (+33) 5 61 93 28 06

DATE : MAR 05/90 SERVICE BULLETIN No. : -57

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