@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 - MAIN LANDING GEAR ATTACHMENT - INTRODUCTION OF

BUSHES WITH INCREASED INTERFERENCE FIT INTO AFT BEARING

FORWARD LUG OF GEAR RIB 5

MODIFICATION No.: 13329H5686

This page transmits Revision No.03 of Service Bulletin No.A310-57-2090

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 introduce new Repair Instruction R57249389, a new flowchart and new

Accomplishment Instructions (including changes to instructions for bush installation and paint/sealing

process). The opportunity is taken to produce this Service Bulletin in the latest format.

CHANGES

Layout changes due to computerization of this revision are not identified.

SUMMARY

MODIFICATIONS Minor editorial or document structure change N

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

Minor editorial or document structure change N

GENERAL EVALUATION Minor editorial or document structure change N

MATERIAL PRICE INFORMATION Minor editorial or document structure change N

EFFECTIVITY Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REFERENCES / REPERCUSSIONS Minor editorial or document structure change N

NATURE OF THE WORK Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

APPENDICES Minor editorial or document structure change N

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Fig. A-USAAA Minor editorial or document structure change N

Fig. A-USAAA Sheet 01 Minor editorial or document structure change N

PLANNING INFORMATION

EFFECTIVITY Minor editorial or document structure change N

Configuration definition Minor editorial or document structure change N

CONF 001 Minor editorial or document structure change N

Material Effectivity Minor editorial or document structure change N

Minor editorial or document structure change N

CONCURRENT REQUIREMENTS Minor editorial or document structure change N

REASON Minor editorial or document structure change N

History Minor editorial or document structure change N

Objective/Action Minor editorial or document structure change N

Advantages Minor editorial or document structure change N

Operational/Maintenance

Consequences

Minor editorial or document structure change N

DESCRIPTION Minor editorial or document structure change N

COMPLIANCE Minor editorial or document structure change N

Classification Minor editorial or document structure change N

Accomplishment Timescale Minor editorial or document structure change N

APPROVAL Minor editorial or document structure change N

Minor editorial or document structure change N

MANPOWER Minor editorial or document structure change N

Minor editorial or document structure change N

WEIGHT AND BALANCE Minor editorial or document structure change N

ELECTRICAL LOAD DATA Minor editorial or document structure change N

REFERENCES Minor editorial or document structure change N

Minor editorial or document structure change N

PUBLICATION AFFECTED Minor editorial or document structure change N

Minor editorial or document structure change N

INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N

SPARES Minor editorial or document structure change N

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY Minor editorial or document structure change N

Procurement Addresses Minor editorial or document structure change N

Price and Availability Minor editorial or document structure change N

INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N

LIST OF COMPONENTS Minor editorial or document structure change N

Kit 572090B01R02 Minor editorial or document structure change N

LIST OF MATERIALS - OPERATOR

SUPPLIED

Minor editorial or document structure change N

Consumable Materials Minor editorial or document structure change N

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 2

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Consumable CMLB01 Minor editorial or document structure change N

Components Minor editorial or document structure change N

Equipment Minor editorial or document structure change N

PARTS TO BE RE-IDENTIFIED BY

OPERATOR

Minor editorial or document structure change N

TOOLING Minor editorial or document structure change N

Tooling - Price and Availability Minor editorial or document structure change N

Tools Minor editorial or document structure change N

Standard tool TOOLB01 Minor editorial or document structure change N

Special Tools Minor editorial or document structure change N

ACCOMPLISHMENT INSTRUCTIONS

TASK 572090- 831-895-001-

MODIFICATION

Minor editorial or document structure change N

Task associated data - 001 Minor editorial or document structure change N

Subtask 572090-910-401-002 Minor editorial or document structure change N

Subtask 572090-839-401-001 Minor editorial or document structure change N

Subtask 572090-941-401-002 Minor editorial or document structure change N

Subtask 572090-020-401-001 Minor editorial or document structure change N

Subtask 572090-020-402-001 Minor editorial or document structure change N

Subtask 572090-832-401-001 Minor editorial or document structure change N

Subtask 572090-410-402-001 Minor editorial or document structure change N

Subtask 572090-914-401-001 Minor editorial or document structure change N

Subtask 572090-410-401-001 Minor editorial or document structure change N

Subtask 572090-930-401-001 Minor editorial or document structure change N

Subtask 572090-710-401-001 Minor editorial or document structure change N

Subtask 572090-942-401-001 Minor editorial or document structure change N

Fig. A-UFAAA Minor editorial or document structure change N

Fig. A-UFAAA Sheet 01 Minor editorial or document structure change N

Fig. A-UBAAA Minor editorial or document structure change N

Fig. A-UBAAA Sheet 01 Minor editorial or document structure change N

Fig. A-UBAAA Sheet 02 Minor editorial or document structure change N

Fig. A-UBAAA Sheet 03 Minor editorial or document structure change N

Fig. A-UCAAA Minor editorial or document structure change N

Fig. A-UCAAA Sheet 01 Minor editorial or document structure change N

Fig. A-UCAAA Sheet 02 Minor editorial or document structure change N

Fig. A-UDAAA Minor editorial or document structure change N

Fig. A-UDAAA Sheet 01 Minor editorial or document structure change N

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 3

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

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

HISTORY OF PREVIOUS REVISIONS

Revision 01 was issue to update the sales price information given in the Industry Support Information

and correct the surface finish units. The opportunity was taken to make minor corrections and update

the effectivity.

Revision No. 02

This revision has been issued to change the Compliance from Recommended to Mandatory. The part

number of the honing tool has been updated.

REVISION SEQUENCE

ORIGINAL: May 22/07

REVISION No.: 02 - Jun 18/10

REVISION No. : 03 - Jan 23/12

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 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 - MAIN LANDING GEAR ATTACHMENT - INTRODUCTION OF

BUSHES WITH INCREASED INTERFERENCE FIT INTO AFT BEARING

FORWARD LUG OF GEAR RIB 5

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 13329H5686

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the

mass, balance, structural strength, reliability, operational characteristics affecting the

airworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During routine maintenance, a crack has been found visually in MLG Rib 5 on two A310 in-service

aircraft. The crack was found in the forward lug of the MLG Rib 5 aft bearing attachment lug. The

concerned aircraft had accumulated 24,000 Flight Cycles (FC) and 27,000 FC at the time of finding,

refer to OIT 999.0115/06.

In both cases the cracks extended through the entire thickness of the forward lug. Inspection of the

MLG Rib 5 forward lug on the opposite wings was performed after removal of the bushes on the

concerned aircraft. The inspection revealed medium to heavy corrosion in the forward lug holes. A

laboratory examination of the two cracked ribs confirmed that the origin of the cracks was due to pitting

corrosion.

This Service Bulletin introduces new bushes with an increased interference fit in the aft bearing forward

lugs. The aft lug of the aft bearing attachment is not affected as the bush is already installed during

production with an increased interference fit. After removal of the old bushes, a dye penetrant flaw

detection inspection is carried out on the lug bores and faces before installation of the new bushes to

make sure that the lugs are free of corrosion/damage.

Accomplishment of this Service Bulletin terminates the mandatory inspection requirements of Inspection

Service Bulletin (ISB) A3010-57-2091.

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 1

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@A310

SERVICE BULLETIN

SUMMARY

Aircraft that have applied this Service Bulletin at a previous revision will be required to re-inspect gear

rib lugs as per Inspection Service Bulletin (ISB) A310-57-2101. If oversized interference fit bushes have

already been installed in a MLG Rib 5 aft bearing forward lug position as per the Repair Instruction

R57249389, the intent of this modification can be considered as embodied in those position(s).

Accomplishment of this Service Bulletin will significantly reduce the likelihood of corrosion and any

subsequent cracks in the forward lug of the MLG Rib 5 aft bearing attachment.

Accomplishment of this Service Bulletin at Revision No. 03 will cancel the inspection requirements of

Service Bulletins A310-57A2088 and A310-57-2091.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB YES

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NORMAL JACKING YES

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 572090B01R02 2 9,720.00 Bush

Standard tool TOOLB01 1 See SB Tools

EFFECTIVITY

This Service Bulletin is applicable to this (these) operator(s) :

18T 19U 46T 52X 58X 82Z 83V 85W 85Z 99Y AFG AIB AIC

BAF BBC CFC DGA F2I FDX G2X G8E GAF HFY IRA IRM IYE

JAB JAV K1P KAC KZU MGL PCA PIA QAF R1T RJA ROT RZO

SBI SGX THY TSC UBD UZB WHT WTJ

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU 57.51.34.004

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 2

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@A310

SERVICE BULLETIN

SUMMARY

OTHERS OIT SE 999.0115/06 and OIT SE 999.0062/11

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 572090-831-895-001: MODIFICATION

TOTAL MANHOURS 45.00

ELAPSED TIME (HOURS) 24.50

APPENDICES

None

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 3

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@A310

SERVICE BULLETIN

SUMMARY

**CONF ALL

FORWARD

LUG OF AFT

BEARING

FORWARD

PINTLE

FITTING

B_SB_572090_7_SAAA_01_00

A

GEAR

SUPPORT

RIB

A

LH SHOWN

RH SIMILAR

Figure A-USAAA - Sheet 01

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 4

7

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A310

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - MAIN LANDING GEAR ATTACHMENT - INTRODUCTION OF

BUSHES WITH INCREASED INTERFERENCE FIT INTO AFT BEARING

FORWARD LUG OF GEAR RIB 5

MODIFICATION No.: 13329H5686

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

310-203 310-204 310-221 310-222 310-304 310-308 310-322 310-324

310-325

(2) Effectivity by MSN

0162 0191 0201 0217 0224 0230 0233 0237 0245 0248 0251 0254 0257 0260 0264

0267 0273 0278 0281 0283 0288 0297 0303 0316 0318 0320 0326 0331 0333 0335

0342-0343 0345-0346 0356-0357 0359-0360 0362 0364 0367 0369-0370 0372 0378

0389 0392 0394 0397 0399-0400 0406-0407 0410 0413 0418-0419 0421-0422 0425

0427-0429 0431 0434 0436 0439 0441 0444-0449 0452 0454 0456-0458 0467

0472-0473 0475-0476 0478 0480-0485 0487-0492 0494-0500 0502-0503 0519-0520

0522-0524 0526-0527 0531 0534 0537-0539 0541-0542 0544-0545 0547 0549-0552

0562 0564-0565 0567-0568 0571 0573-0574 0576 0585-0588 0590-0595 0597

0599-0600 0620 0622 0624 0636 0638 0642 0644 0646-0651 0653 0656 0658

0660-0661 0663 0667 0669 0671-0672 0674 0676 0678 0682 0684 0687 0689 0691

0693 0697 0700 0702 0704 0706

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 1

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SERVICE BULLETIN

(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.

OPERATOR MSN

18T 0473

19U 0399

46T 0413

52X 0410

58X 0431

82Z 0550 0551

83V 0427

85W 0684 0693 0697

85Z 0547

99Y 0489

AFG 0496 0497

AIB 0650 0674

AIC 0392 0406 0407 0428 0429 0538 0544 0669

BAF 0367 0372

BBC 0594 0642 0700

CFC 0425 0441 0444 0446 0482

DGA 0418 0421 0422

F2I 0487

FDX 0162 0191 0201 0217 0224 0230 0233 0237 0245 0248 0251 0254

0257 0260 0264 0267 0273 0278 0281 0283 0288 0297 0303 0316

0318 0326 0331 0333 0335 0342 0343 0345 0346 0356 0359 0360

0362 0364 0369 0378 0394 0397 0400 0439 0449 0452 0454 0456

0457 0458 0467 0492 0500 0534 0539 0542 0549 0552 0593 0638

G2X 0573

G8E 0475

GAF 0434 0484 0498 0499 0503 0522 0523

HFY 0495 0565

IRA 0370 0389 0436 0671

IRM 0488 0524 0537 0564 0567 0586 0595 0620

IYE 0568 0702 0704

JAB 0320

JAV 0357 0481

K1P 0648

KAC 0647 0649 0663

KZU 0592 0622 0646

MGL 0526

PCA 0419

PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691

QAF 0667

R1T 0591

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 2

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@A310

SERVICE BULLETIN

OPERATOR MSN

RJA 0445 0490 0491 0531

ROT 0636 0644

RZO 0571 0624 0651 0661

SBI 0520

SGX 0519 0562

THY 0476 0478 0480 0502

TSC 0447 0472 0483 0485 0527 0541 0545 0588 0597 0599 0600 0658

UBD 0672

UZB 0574 0576 0706

WHT 0448

WTJ 0494

(4) Configuration by MSN

MSN CONFIGURATION

0162 0191 0201 0217 0224 0230 0233 0237 0245 0248 0251

0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0297

0303 0316 0318 0320 0326 0331 0333 0335 0342 0343 0345

0346 0356 0357 0359 0360 0362 0364 0367 0369 0370 0372

0378 0389 0392 0394 0397 0399 0400 0406 0407 0410 0413

0418 0419 0421 0422 0425 0427 0428 0429 0431 0434 0436

0439 0441 0444 0445 0446 0447 0448 0449 0452 0454 0456

0457 0458 0467 0472 0473 0475 0476 0478 0480 0481 0482

0483 0484 0485 0487 0488 0489 0490 0491 0492 0494 0495

0496 0497 0498 0499 0500 0502 0503 0519 0520 0522 0523

0524 0526 0527 0531 0534 0537 0538 0539 0541 0542 0544

0545 0547 0549 0550 0551 0552 0562 0564 0565 0567 0568

0571 0573 0574 0576 0585 0586 0587 0588 0590 0591 0592

0593 0594 0595 0597 0599 0600 0620 0622 0624 0636 0638

0642 0644 0646 0647 0648 0649 0650 0651 0653 0656 0658

0660 0661 0663 0667 0669 0671 0672 0674 0676 0678 0682

0684 0687 0689 0691 0693 0697 0700 0702 0704 0706

001

(5) Configuration definition

**CONF 001

Config. 001 is valid for all aircraft that have not had oversized interference fit bushes

installed by Repair Instruction R57249389. If oversized interference fit bushes are found

to have been installed by Repair Instruction R57249389 on one wing only, then only 1

Kit 572090B01R02 will be necessary.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Kit 572090B01R02 2

Consumable CMLB01 As required

Standard tool TOOLB01 1

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 3

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SERVICE BULLETIN

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During routine maintenance, a crack has been found visually in MLG Rib 5 on two A310

in-service aircraft. The crack was found in the forward lug of the MLG Rib 5 aft bearing

attachment lug. The concerned aircraft had accumulated 24,000 Flight Cycles (FC) and

27,000 FC at the time of finding, refer to OIT 999.0115/06.

In both cases the cracks extended through the entire thickness of the forward lug.

Inspection of the MLG Rib 5 forward lug on the opposite wings was performed after

removal of the bushes on the concerned aircraft. The inspection revealed medium to

heavy corrosion in the forward lug holes. A laboratory examination of the two cracked

ribs confirmed that the origin of the cracks was due to pitting corrosion.

(2) Objective/Action

This Service Bulletin introduces new bushes with an increased interference fit in the aft

bearing forward lugs. The aft lug of the aft bearing attachment is not affected as

the bush is already installed during production with an increased interference fit. After

removal of the old bushes, a dye penetrant flaw detection inspection is carried out on

the lug bores and faces before installation of the new bushes to make sure that the lugs

are free of corrosion/damage.

Accomplishment of this Service Bulletin terminates the mandatory inspection

requirements of Inspection Service Bulletin (ISB) A3010-57-2091.

Aircraft that have applied this Service Bulletin at a previous revision will be required

to re-inspect gear rib lugs as per Inspection Service Bulletin (ISB) A310-57-2101. If

oversized interference fit bushes have already been installed in a MLG Rib 5 aft bearing

forward lug position as per the Repair Instruction R57249389, the intent of this

modification can be considered as embodied in those position(s).

(3) Advantages

Accomplishment of this Service Bulletin will significantly reduce the likelihood of

corrosion and any subsequent cracks in the forward lug of the MLG Rib 5 aft bearing

attachment.

Accomplishment of this Service Bulletin at Revision No. 03 will cancel the inspection

requirements of Service Bulletins A310-57A2088 and A310-57-2091.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 4

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SERVICE BULLETIN

Task 572090-831-895-001: MODIFICATION

(1) Remove LH/RH MLG Components

(2) Removal of Bushes

(3) Inspection of Lug Faces and Bores

(4) Installation of Bushes

(5) Permanent Seal of Bush/Lug Interface

(6) Install LH/RH MLG Components

(7) Re-identification

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin at Revision No. 03 will be rendered mandatory

by the issue of an Airworthiness Directive (AD) published by the European Aviation

Safety Agency (EASA). The AD must be used as the reference document for the

mandatory accomplishment timescale.

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organisation Approval No. EASA.21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

Task 572090-831-895-001: MODIFICATION

Get Access 1.00

On Aircraft

Remove LH/RH MLG Components 10.00

Removal of Bushes 3.00

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 5

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SERVICE BULLETIN

Task 572090-831-895-001: MODIFICATION

Inspection of Lug Faces and Bores 2.00

Installation of Bushes 6.00

Permanent Seal of Bush/Lug Interface 5.00

Install LH/RH MLG Components 10.00

Re-identification 1.00

Tests 6.00

Close-Up 1.00

TOTAL MANHOURS 45.00

ELAPSED TIME (HOURS) 24.50

NOTE: If the Repair Instruction R57249389, "Removal of Corrosion from the Gear

Rib 5 Lugs and the Installation of Oversized Bushes" is necessary, then

approximately 56.00 manhours for each wing will need to be added for

Modification.

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 07-11-00 32-11-11 32-12-13

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-02 51-90-00

Structural Repair Manual (SRM) 51-10-50 51-40-12 51-40-20

51-40-21

K. PUBLICATION AFFECTED

Aircraft Maintenance Manual (AMM) 57-51-34

Illustrated Parts Catalog (IPC) 57-51-34

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 6

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Customers with aircraft shown in the effectivity of this Service Bulletin should send a

purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:

AIRBUS

Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet: http://spares.airbus.com

For ordering by fax: +49 40 50 76 25 90

For ordering by E-mail: airbus.kit@airbus.com

(2) Price and Availability

Kit 572090B01R02

Cost 4,860.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchase

order. If you require the Kit(s) before this time, please include a retrofit planning

schedule with your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions

at the issue date of the Service Bulletin.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will provide a 50 percent reduction to the applicable sales prices given in paragraph

2A(2) for orders placed before 31 December 2013.

C. LIST OF COMPONENTS

Kit 572090B01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

1 A5724244220200 1 Bush (1) A5724244220000

2 A5724244120200 1 Bush (2) A5724244120000

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 7

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SERVICE BULLETIN

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Honing Fluid 06-010 As required

Varnish 07-018 As required (1)

Sealant, Anaerobic 08-003 As required

Fuel Tank Sealant Polysulfide 09-002 As required

Low Adhesion Polysulfide Sealant 09-019C As required

Adhesion Promoter For Polysulfide

Sealant

09-028 As required

Solvent General Purpose 11-026 As required

Chemical Conversion Coating

Yellow Aluminum

13-002 As required

Anti-Corrosion Primer 16-006 As required

External Top Coat (polyurethane) 16-018 As required

Polyurethane Gloss Finish (Clear

Basecoat)

16-021B As required

Lint-Free Cotton Cloth 19-003 As required

Marker Pen 8404 As required (2)

NOTE (1): Mat. No. 07-018 is an alternative to Mat. No. 16-021B when used to

protect written part numbers.

NOTE (2): The Marker pen 8404 can be procured from:

- Edding (UK) Ltd.

- Merlin Centre

- Acrewood Way

- St. Albans

- Herts.

- England

(2) Components

None

(3) Equipment

None

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 8

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SERVICE BULLETIN

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

Reidentify Gear Rib by marking the SB Number "SB A310-57-2090 R03" adjacent to the old

part number.

F. TOOLING

(1) Tooling - Price and Availability

Gear Rib 5 Toolkit 0044A411058D

(2) Tools

Gear Rib 5 Toolkit 0044A411058D

NOTE: The tool kit contains the following items for the removal of the bushes,

Items (1) and (2):

- Qty 1 0044A411058D-34 Split Location Ring

- Qty 1 0044A411058D-35 Bolt

- Qty 1 0044A411058D-43 Enerpac Cylinder

- Qty 1 0044A411058D-44 Enerpac Hand Pump

- Qty 1 0044A411058D-45 Enerpac Connector Hose

- Qty 1 0044A411058D-46 Spherical Washer

- Qty 1 0044A411058D-47 Location Block

- Qty 4 0044A411058D-48 Bolt (for Item 47)

- Qty 1 0044A411058D-49 Thrust Washer

- Qty 2 0044A411058D-50 Nut

- Qty 1 0044A411058D-51 Reaction Block (Aft Bush Item (1))

- Qty 1 0044A411058D-86 Captive Washer

- Qty 1 0044A411058D-87 Shoulder Screw (for item 86)

- Qty 1 0044A411058D-89 Reaction Clamp (Fwd Bush Item (2))

The tool kit contains the following items for the installation of the bushes,

Items 1 and 2:

- Qty 1 0044A411058D-35 Bolt

- Qty 1 0044A411058D-39 Installation Block

- Qty 1 0044A411058D-43 Enerpac Cylinder

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 9

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SERVICE BULLETIN

- Qty 1 0044A411058D-44 Enerpac Hand Pump

- Qty 1 0044A411058D-45 Enerpac Connector Hose

- Qty 1 0044A411058D-46 Spherical Washer

- Qty 2 0044A411058D-50 Nut

- Qty 1 0044A411058D-51 Reaction Clamp (Fwd Bush Item 2)

- Qty 1 0044A411058D-86 Captive Washer

- Qty 1 0044A411058D-87 Shoulder Screw (for Item 86)

- Qty 1 0044A411058D-89 Reaction Clamp (Aft Bush Item 1)

The tool kit will contain an In-Line Honing Tool PN MT58133-195 to line

hone the bushes to the finished internal diameter after installation. Also

in the tool kit is a shorter In-Line Honing Tool PN MT58133-197 which

can be used as an alternative and an Alignment Tool (truing sleeve) PN

MT19048 to set up the In-Line Honing Tools.

Also included are additional tools required in case a repair is necessary.

Heaters (Optional).

Standard tool TOOLB01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

0044A411058D Gear Rib 5 Toolkit 1

(3) Special Tools

None

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 10

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 572090-831-895-001 - MODIFICATION

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

Task Associated Data

Zone

730 740

Manpower

TOTAL MANHOURS 45.00

ELAPSED TIME (HOURS) 24.50

A. GENERAL

(1) Subtask 572090-910-401-002 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Structural Repair Manual (SRM) 51-10-50

51-40-12

51-40-20

51-40-21

(a) For application of protective treatments, refer to SRM 51-40-12.

(b) For application of sealant, refer to SRM 51-40-20 or SRM 51-40-21.

(c) For removal and installation of bushes, refer to SRM 51-10-50.

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 11

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SERVICE BULLETIN

(2) Subtask 572090-839-401-001 - Administrative

(a) Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

B. PREPARATION

(1) Subtask 572090-941-401-002 - Job Set-Up

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 07-11-00, Page Block 001

(a) Lift the aircraft on jacks (Refer to AMM 07-11-00, Page Block 001).

(b) Put access platforms in position in Zones 730/740.

C. PROCEDURE

NOTE: The worksteps that follow are applicable to the LH and RH wings.

(1) Subtask 572090-020-401-001 - Remove LH/RH MLG Components

Work Zones and Access Panels

Zone Access/Work location

730

740

Manpower Resources

Manhours 10.00

Minimum number of person 2

Subtask elapsed time 5.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 32-11-11, Page Block 401

32-12-13, Page Block 401

(a) Remove the LH and RH MLG legs (Refer to AMM 32-11-11, Page Block 401).

(b) Remove the LH and RH MLG secondary doors (Refer to AMM 32-12-13, Page

Block 401).

(2) Subtask 572090-020-402-001 - Removal of Bushes

Work Zones and Access Panels

Zone Access/Work location

730

740

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 12

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SERVICE BULLETIN

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Standard tool TOOLB01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

0044A411058D Gear Rib 5 Toolkit 1

References

Fig. A-UFAAA

Process Flowchart

Sheet 01

Fig. A-UBAAA

Replacement of Gear Support Rib

Bushes

Sheet 01

Sheet 02

Sheet 03

Refer to Fig. A-UFAAA Sheet 01, Fig. A-UBAAA Sheet 01, Fig. A-UBAAA Sheet 02 and

Fig. A-UBAAA Sheet 03.

(a) Use the removal/installation tool from the MLG Rib 5 Toolkit:

0044A411058D Gear Rib 5 Toolkit 1

to remove these items:

1 Bush A5724244220000 Item (1) Discard

1 Bush A5724244120000 Item (2) Discard

(3) Subtask 572090-832-401-001 - Inspection of Lug Faces and Bores

Work Zones and Access Panels

Zone Access/Work location

730

740

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 13

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SERVICE BULLETIN

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

References

Non Destructive Test Manual (NTM) 51-10-02

51-90-00 (No etch)

Fig. A-UBAAA

Replacement of Gear Support Rib

Bushes

Sheet 01

Sheet 02

Sheet 03

Fig. A-UCAAA

Line Honing Details

Sheet 01

Sheet 02

Fig. A-UFAAA

Process Flowchart

Sheet 01

Refer to Fig. A-UFAAA Sheet 01, Fig. A-UBAAA Sheet 01, Fig. A-UBAAA Sheet 02, Fig.

A-UBAAA Sheet 03, Fig. A-UCAAA Sheet 01 and Fig. A-UCAAA Sheet 02.

(a) Visually inspect the gear rib forward lug bore to ensure no liner bushes are

installed. If there are, report the details to AIRBUS for further instructions.

(b) Clean the bores, spotfaces and chamfer of the forward lug with a plastic spatula

and

Solvent General

Purpose

11-026 As required

(c) Visually inspect the bore, spotfaces and chamfer of the forward lug to make sure

there is no corrosion and/or damage (Refer to NTM 51-10-02).

(d) Do a dye penetrant flaw detection test of the bore, spotfaces and chamfer of the

forward lug to make sure there is no corrosion and/or damage (Refer to NTM

51-90-00).

(e) Do a check to make sure that the forward lug thickness is greater than 57.33 to

57.40 mm (2.257 to 2.260 in.). If not, report all details to AIRBUS for further

instructions.

(f) Do a check to make sure that the diameter of the bore of the lug (dimension Y) is

within the tolerance of 121.389 to 121.425 mm (4.7791 to 4.7805 in.) and proceed

with standard bushes. If not, report all details to AIRBUS for further instructions.

(g) Check the bore for ovality; if ovality is found, report all findings to AIRBUS for

further instructions.

(h) If no damage and/or corrosion is found and dimension Y is within the tolerance go

to SUBTASK 572090-410-402 001 Installation of Bushes .

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 14

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SERVICE BULLETIN

(i) If there is damage and/or corrosion found, or if the lug thickness is below the given

tolerance, or dimension Y is more than the given tolerance, report the findings to

AIRBUS and wait for advice for Repair Instruction R57249389 and re-boring tool

044A411058D.

(4) Subtask 572090-410-402-001 - Installation of Bushes

Work Zones and Access Panels

Zone Access/Work location

730

740

Manpower Resources

Manhours 6.00

Minimum number of person 2

Subtask elapsed time 3.00

Skills AIRFRAME

Material necessary to do the job

Kit 572090B01R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 A5724244220200 1 Bush

2 A5724244120200 1 Bush

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Honing Fluid 06-010 As required

Sealant, Anaerobic 08-003 As required

Low Adhesion Polysulfide

Sealant

09-019C As required

Solvent General Purpose 11-026 As required

Chemical Conversion

Coating Yellow Aluminum

13-002 As required

Anti-Corrosion Primer 16-006 As required

Lint-Free Cotton Cloth 19-003 As required

References

Fig. A-UFAAA

Process Flowchart

Sheet 01

Fig. A-UBAAA

Replacement of Gear Support Rib

Bushes

Sheet 01

Sheet 02

Sheet 03

Fig. A-UCAAA

Line Honing Details

Sheet 01

Sheet 02

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 15

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SERVICE BULLETIN

Refer to Fig. A-UFAAA Sheet 01, Fig. A-UBAAA Sheet 01, Fig. A-UBAAA Sheet 02, Fig.

A-UBAAA Sheet 03, Fig. A-UCAAA Sheet 01 and Fig. A-UCAAA Sheet 02.

(a) Before installing the bushes check that the dimension Z is likely to be achieved.

This can be done by measuring the thickness of the lug and the thickness of the

flange on the two bushes and adding them together. Dimension Z should be

between 70.74 and 71.04 mm (2.785 and 2.797 in.). If the dimension Z is outside

the tolerance, contact AIRBUS.

(b) Re-protect surface finishes if there is visible damage to the surface protection or

the surface protection has been removed during inspection.

1 Apply:

Chemical

Conversion Coating

Yellow Aluminum

13-002 As required

to the chamfer and the spotfaces of the lug.

2 Wash off excess Chemicals and make sure sufficient drying time is allowed.

3 Apply:

Anti-Corrosion

Primer

16-006 As required

to the chamfer and spotfaces of the lug and the mating surface for the seat of

the bush flange. Leave until no longer tacky.

(c) Apply

Sealant, Anaerobic 08-003 As required

to the lug bore.

(d)

WARNING: LIQUID NITROGEN IS DANGEROUS. OBEY THE

MANUFACTURERS INSTRUCTIONS AND WEAR THE CORRECT

PROTECTIVE CLOTHING WHEN YOU USE LIQUID NITROGEN.

CAUTION: DO NOT PUT MORE THAN ONE BUSH AT A TIME INTO THE

LIQUID NITROGEN, USE CLEAN TONGS TO REMOVE THE

BUSH FROM THE LIQUID NITROGEN AND TO INSTALL IT IN

THE BORE OF THE LUG.

Install:

1 Bush A5724244220200 Item 1

1 Bush A5724244120200 Item 2

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 16

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SERVICE BULLETIN

1 To make sure that the bush remains cold enough so that the risk of the bush

interfering with the bore on installation is minimized, the bush and mandrel

(assembled) must be immersed in liquid nitrogen for at least 30 minutes

immediately prior to installation.

2 Freeze each bush in sequence in liquid nitrogen for not less than 30 minutes.

3 Use the Installation Block PN 0044A411058D-38, Reaction Clamp PN

0044A411058D-90 (for Item 1) and Reaction Clamp PN 0044A411058D-51

(for item 2) to install each bush in sequence in the applicable end of the bore

of the forward lug of the aft gear-rib bearing. Make sure that the bushes are

fully installed.

4 Clamp each bush firmly immediately after installation and then allow the

assembly to return to ambient temperature, allow the sealant to cure fully to

prevent any bush migration.

(e) Make sure that the dimension Z is within the tolerance of 70.74 to 71.04 mm (2.785

to 2.797 in.). If outside limits, contact AIRBUS and await instructions.

(f) Make sure that the clearance dimension between the bushes, Item 1 and Item 2 is

free of sealant.

(g) Prior to honing it is recommended that the permanent four stage sealing procedure

is applied, refer to SUBTASK 572090-914-401 001 Permanent Seal of Bush/Lug

Interface and the full cure time of the surface protection and sealants is allowed,

before proceeding further. However, it is acceptable to continue immediately with

the repair (honing the bushes) provided a temporary fillet seal is applied as follows:

1 Apply a temporary fillet seal around the bush heads. Use:

Low Adhesion

Polysulfide Sealant

09-019C As required

and leave until no longer tacky.

(h) Assemble the in-line honing tool.

(i) Use the alignment tool to set up the in-line honing tool.

(j) Use the in-line honing tool to finish the internal diameter (dimension X) of the

bushes, Item 1 and Item 2, within the tolerance of 114.999 to 115.034 mm (4.5275

to 4.5289 in.) and to a surface finish of 0.8 microns (32 micro inches). Use:

Honing Fluid 06-010 As required

(k) Thoroughly clean area before removal of the temporary seal from around the bush

heads. Use:

Lint-Free Cotton

Cloth

19-003 As required

made moist with:

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 17

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SERVICE BULLETIN

Solvent General

Purpose

11-026 As required

(5) Subtask 572090-914-401-001 - Permanent Seal of Bush/Lug Interface

Work Zones and Access Panels

Zone Access/Work location

730

740

Manpower Resources

Manhours 5.00

Minimum number of person 1

Subtask elapsed time 5.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Fuel Tank Sealant

Polysulfide

09-002 As required

Adhesion Promoter For

Polysulfide Sealant

09-028 As required

Solvent General Purpose 11-026 As required

External Top Coat

(polyurethane)

16-018 As required

Polyurethane Gloss Finish

(Clear Basecoat)

16-021B As required

Lint-Free Cotton Cloth 19-003 As required

References

Fig. A-UDAAA

Sealing Details

Sheet 01

Refer to Fig. A-UDAAA Sheet 01.

NOTE: The procedure below is a four stage procedure to make sure there is a

robust sealing of the bush to the lug. Deviation from this procedure can

allow the integrity of the seal to be compromized.

(a) Use:

Lint-Free Cotton

Cloth

19-003 As required

made moist with:

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 18

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SERVICE BULLETIN

Solvent General

Purpose

11-026 As required

to clean the area.

(b) Apply:

Adhesion Promoter

For Polysulfide

Sealant

09-028 As required

around the flanges of the bushes, Items 1 and 2 and the lug face.

(c) Apply a continuous bead of sealant around the edges of the bushes, Item 1 and

Item 2 to form a fillet seal, use:

Fuel Tank Sealant

Polysulfide

09-002 As required

leave until no longer tacky.

(d) Use:

Lint-Free Cotton

Cloth

19-003 As required

made moist with:

Solvent General

Purpose

11-026 As required

to remove any unwanted sealant.

(e) Apply:

External Top Coat

(polyurethane)

16-018 As required

to the fillet seals to protect the sealant from hydraulic fluid.

(f) Apply:

Polyurethane Gloss

Finish (Clear

Basecoat)

16-021B As required

to the fillet seals to protect the sealant from hydraulic fluid.

NOTE: To prevent contamination/damage to the sealant and coatings, it is

required that the assembly is left to fully cure. Heaters (optional)

may be used to reduce the sealant cure time.

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 19

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SERVICE BULLETIN

(6) Subtask 572090-410-401-001 - Install LH/RH MLG Components

Work Zones and Access Panels

Zone Access/Work location

730

740

Manpower Resources

Manhours 10.00

Minimum number of person 2

Subtask elapsed time 5.00

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 32-11-11, Page Block 401

32-12-13, Page Block 401

(a) Install the LH and RH MLG secondary doors (Refer to AMM 32-12-13, Page Block

401).

(b) Install the LH and RH MLG legs (Refer to AMM 32-11-11, Page Block 401).

(7) Subtask 572090-930-401-001 - Re-identification

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLB01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Varnish 07-018 As required (1)

Polyurethane Gloss Finish

(Clear Basecoat)

16-021B As required

Marker Pen 8404 As required (2)

NOTE (1): Mat. No. 07-018 is an alternative to Mat. No. 16-021B when used to

protect written part numbers.

NOTE (2): The Marker pen 8404 can be procured from:

- Edding (UK) Ltd.

- Merlin Centre

- Acrewood Way

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 20

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SERVICE BULLETIN

- St. Albans

- Herts.

- England

(a) Re-identify the gear Rib 5 by marking this SB No. and Revision No. (A310-57-2090

R03) adjacent to the PN.

Use:

Marker Pen 8404 As required

Apply:

Polyurethane Gloss

Finish (Clear

Basecoat)

16-021B As required

or

Varnish 07-018 As required

to protect the written SB No. from hydraulic fluid.

D. TEST

(1) Subtask 572090-710-401-001 - Test

Manpower Resources

Skills AIRFRAME

(a) The test procedure necessary for the LH and RH MLG is referenced in SUBTASK

572090-942-401 001 Close-Up .

E. CLOSE-UP

(1) Subtask 572090-942-401-001 - Close-Up

Work Zones and Access Panels

Zone Access/Work location

730

740

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) 07-11-00, Page Block 001

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 21

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SERVICE BULLETIN

(b) Remove the access platforms from zones 730/740.

(c) Lower the aircraft off jacks (Refer to AMM 07-11-00, Page Block 001).

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 22

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SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

BORE AND SPOTFACE

VISUALLY INSPECT

CLEAN BORE OF LUG

REMOVE BUSHES

FOUND?

CORROSION

OF TOLERANCE?

GEOMETRY OUT

INSPECTION OF

DO A DYE PENETRANT

BORE/CHAMFER/SPOTFACE

BORE GEOMETRY

CHECK LUG

FOUND?

CORROSION

YES

YES

YES

NO

INTERFERENCE FIT BUSHES

INSTALL HIGH

FOR REPAIR

CONTACT AIRBUS

INSTRUCTIONS

NO

NO

B_SB_572090_7_FAAA_01_00

Figure A-UFAAA - Sheet 01

Process Flowchart

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 23

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SERVICE BULLETIN

**CONF ALL

C

X

Z

Y

THIS SPACE TO BE

FREE OF SEALANT

A

GEAR

SUPPORT

RIB

(2) 2

(1) 1

D F E G

FWD

I

N

B

D

B

C

B_SB_572090_7_BAAA_01_00

A

LH SHOWN

RH SIMILAR

B

Figure A-UBAAA - Sheet 01

Replacement of Gear Support Rib Bushes

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 24

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SERVICE BULLETIN

**CONF ALL

46 86 51 47 49 43 50 35

50 43

49

47 86

46 35

90

87 48

44 45

48 87

44 45

NOTE: TOOL KIT IDENTS.

33

33

BUSH (ITEM (2)) REMOVAL

BUSH (ITEM (1)) REMOVAL

(2)

(1)

(2)

D

E

B_SB_572090_7_BAAA_02_00

Figure A-UBAAA - Sheet 02

Replacement of Gear Support Rib Bushes

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 25

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SERVICE BULLETIN

**CONF ALL

46

86

51

35

50

86 43

46

35

38 87 44 45

87 43 44 45

50

90

38

NOTE: TOOL KIT IDENTS.

BUSH (ITEM 2) INSTALLATION

1 2

1

BUSH (ITEM 1) INSTALLATION

F

G

B_SB_572090_7_BAAA_03_00

Figure A-UBAAA - Sheet 03

Replacement of Gear Support Rib Bushes

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 26

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SERVICE BULLETIN

**CONF ALL

STONE

DRIVE

FORK

STONE

ALUMINIUM

GUIDE

ADJUSTER

NUT

ALIGNMENT

HONE BODY

LOCK

COLLAR

PULL THE LOCK COLLAR TO REVEAL THE SPLINED SHAFT.

INSERT NYLON GUIDE SET INTO BODY AND RESET THE LOCK COLLAR.

NOTE: TO ASSEMBLE STONES AND GUIDES TO BODY:−

PIVOT DRIVE FORK THROUGH 90° AND WITHDRAW CENTER SPINDLE.

INSERT STONE AND ALUMINIUM GUIDE SET INTO BODY AND REPLACE CENTER SPINDLE.

NYLON

 GUIDE SET

SPLINED

 SHAFT

CENTER

SPINDLE

B_SB_572090_7_CAAA_01_00

Figure A-UCAAA - Sheet 01

Line Honing Details

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 27

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SERVICE BULLETIN

**CONF ALL

NOTE: USE OF ALIGNMENT TOOL TO ALIGN FACES OF THE

TWO STONES OF THE LINE − HONING TOOL.

ALIGNMENT

 TOOL

LINE − HONING

TOOL

HAND HELD

 POWER TOOL

B_SB_572090_7_CAAA_02_00

Figure A-UCAAA - Sheet 02

Line Honing Details

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 28

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SERVICE BULLETIN

**CONF ALL

A

BUSH

STEP 1

SPOTFACE AND CHAMFER−

ALODINE MAT NO. 13−002

AND PRIMER MAT NO. 16−006

STEP 2

FILLET SEAL MAT NO. 09−002 −

PROMOTER MAT NO. 09−028

USED ON GEAR RIB AND BUSH

STEP 3

PAINT MAT NO. 16−018

STEP 4

POLYURETHANE GLOSS

FINISH MAT NO. 16−021B

A

LUG

B_SB_572090_7_DAAA_01_00

Figure A-UDAAA - Sheet 01

Sealing Details

DATE: May 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 29

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SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - MAIN LANDING GEAR ATTACHMENT - INTRODUCTION OF

BUSHES WITH INCREASED INTERFERENCE FIT INTO AFT BEARING

FORWARD LUG OF GEAR RIB 5

MODIFICATION No.: 13329H5686

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 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 1

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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 22/07 SERVICE BULLETIN No.: A310-57-2090

REVISION No.: 03 - Jan 23/12 Page: 1

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