7 DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

This summary is for information only

and is not approved for modification of the aircraf

ATA SYSTEM : 57

TITLE : WINGS - MAIN LANDING GEAR ATTACHMENT - INTRODUCTION OF BU

INCREASED INTERFERENCE FIT INTO AFT BEARING FORWARD LUG O

MODIFICATION No. : 13329H5686

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During routine maintenance, a crack has been found visually in mai

(MLG) rib 5 on two A310 in-service aircraft. The crack was found 

lug of the MLG rib 5 aft bearing attachment. The concerned aircra

accumulated 24,000 flight cycles (FC) and 27,000 FC at the time o

refer to Operator Information Telex (OIT) 999.0115/06.

In both cases the cracks extended through the entire thickness of 

lug. Inspection of the MLG rib 5 forward lug on the opposite wings 

after removal of the bushes on the concerned aircraft. The inspec

medium to heavy corrosion in the forward lug holes. A laboratory 

the two cracked ribs confirmed that the origin of the cracks was 

corrosion.

This Service Bulletin introduces new bushes with an increased int

in the aft bearing forward lugs. The aft lug of the aft bearing a

not affected as the bush is already installed during production w

increased interference fit. After removal of the old bushes, a dy

flaw detection inspection is carried out on the lug bores and fac

installation of the new bushes to make sure that the lugs are dam

If oversized interference fit bushes have already been installed 

of the forward lug positions of the MLG rib 5 aft bearing as per 

R57249121, the intent of this modification can be considered as e

these positions.

Accomplishment of this Service Bulletin will significantly reduce 

of corrosion and any subsequent cracks in the forward lug of the 

bearing attachment.

Accomplishment of this Service Bulletin will cancel the inspectio

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

The intent of this Service Bulletin has been validated on A310 air

by the application of repair R57249121.
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

As per EASA IR 21, a minor change is one that has no appreciable 

mass, balance, structural strength, reliability, operational char

affecting the airworthiness of the product. All other changes are 

EFFECTIVITY

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

34W 58X 82Z 85Z 99Y A1L ABD AIC ARG BAF BBC BLM CFC CSA DAH DGA D

IRA IRM IYE JAB JAV KAC KYV MGL MPD MPJ MWA PIA QAF QSC R1T RJA RO

SGX SUD TAP THY TSC UAE UZB WHT

This modification is applicable by Service Bulletin only.

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : 57.51.11.004

OEB : None

AOT : None

SIL : None

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

OTHERS : OIT SE 999.0115/06

COST SAVING No ETOPS AFFECTED 

STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED 

KIT PRICE (USD)B01R02 3960 NORMAL JACKING 

MODIFICATION CLASSIFICATION

MAJOR None

MINOR

13329H5686

2
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

MANPOWER

Config. 01

NOTE : If the Repair Instruction R57249121, "Removal of corrosion 

rib lugs and the installation of oversized bushes" is nece

approximately 52.0 manhours for each wing will be necessary 

MATERIAL INFORMATION

AIRCRAFT DATA

2 x Kit 572090B01R02 will be necessary for accomplishment of 

Bulletin on each aircraft. Kit 572090B01R02 comprises 1 bush A

and 1 bush A5724244220200. 1 kit will be necessary for the LH 

1 kit will be necessary for the RH Gear Rib 5.

A Tool Kit 044A411058D is necessary to accomplish this Service 

Tool Kit includes tools for the removal/installation of the b

line honing tool to finish the internal diameter of the bushe

installation.

NOTE : Tool Kit 044A411058D also includes the re-boring tool w

required to repair aft bearing attachment lugs in case 

to be damaged.

APPENDICES

None

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

3
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

4
7 DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

ATA SYSTEM : 57

TITLE : WINGS - MAIN LANDING GEAR ATTACHMENT - INTRODUCTION OF BU

INCREASED INTERFERENCE FIT INTO AFT BEARING FORWARD LUG O

MODIFICATION No. : 13329H5686

This document contains AIRBUS PROPRIETARY INFORMATION and shall a

remain the property of AIRBUS; no intellectual property right or 

granted by AIRBUS in connection with any information contained in 

delivered on the express condition that said document and the inf

contained in it shall be treated as confidential, shall not be us

purpose other than that for which it is hereby delivered. It shal

disclosed in whole or in part to third parties and shall not be d

any manner (except for the purposes of performing the tasks descr

and provided that any recipient of such document shall comply wit

conditions herein), without AIRBUS' prior written consent.

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Models

310-203 310-203C 310-204 310-222 310-304 310-308 310

310-325

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft 

0162 0172 0191 0201 0217 0224 0230 0233 0237 024

0251 0254 0257 0260 0264 0267 0273 0278 0281 02

0293 0297 0300 0303 0309 0313 0316 0318 0320 03

0335 0338 0339 0342 0343 0345 0346 0349 0353 03

0360 0362 0364 0367 0369 0370 0372 0375 0378 03

0390 0392 0394 0397 0399 0400 0406 0407 0410 04

0419 0421 0422 0425 0427-0431 0434 0436 0437 04

0444-0449 0451-0458 0467 0468 0472 0473 0475 04

0480-0492 0494-0503 0519 0520 0522-0524 0526 05

0535 0537-0539 0541 0542 0544 0545 0547-0552 05

0567 0568 0571 0573 0574 0576 0585-0595 0597-060

0624 0634 0636 0638 0640 0642 0644 0646-0654 06

0661 0663 0665 0667 0669 0671 0672 0674 0676 06
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

from transfer of an aircraft from one operator t

not be reflected in this list unless the Service 

revised for another reason.

OPERATOR MSN

34W 0399

58X 0431

82Z 0550 0551

85Z 0524

99Y 0489

A1L 0648

ABD 0624

AIC 0392 0406 0407 0413 0428 0429 0501 0

0598 0654 0665 0669 0680 0684 0693 0

ARG 0640 0686

BAF 0367 0372

BBC 0594 0650 0698 0700

BLM 0488

CFC 0425 0441 0444 0446 0482

CSA 0564 0567 0672 0674

DAH 0291 0293

DGA 0418 0421 0422

DRD 0527

F2I 0309 0320

FDX 0162 0191 0201 0217 0224 0230 0233 0

0248 0251 0254 0257 0260 0264 0267 0

0283 0288 0297 0303 0313 0316 0318 0

0335 0339 0342 0343 0345 0346 0349 0

0359 0360 0362 0364 0369 0378 0394 0

0449 0452 0454 0456 0457 0458 0467 0

0539 0542 0549 0552 0589 0593 0634 0

GAF 0434 0484 0498 0499 0503 0522 0523

IRA 0338 0370 0375 0379 0389 0390 0436 0

IRM 0537 0586

IYE 0535 0568 0702 0704

JAB 0419

2
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

This modification is applicable by Service Bulle

(c) Effectivity by MSN and Kit/Configuration

The kits and configurations applicable to these 

at the end of this list:

0162 0172 0191 0201 0217 0224 0230 0233 0237 024

0251 0254 0257 0260 0264 0267 0273 0278 0281 02

0293 0297 0300 0303 0309 0313 0316 0318 0320 03

0335 0338-0339 0342-0343 0345-0346 0349 0353 03

0359-0360 0362 0364 0367 0369-0370 0372 0375 03

0389-0390 0392 0394 0397 0399-0400 0406-0407 04

0418-0419 0421-0422 0425 0427-0431 0434 0436-04

0444-0449 0451-0458 0467-0468 0472-0473 0475-04

0480-0492 0494-0503 0519-0520 0522-0524 0526-05

0534-0535 0537-0539 0541-0542 0544-0545 0547-05

MPD 0451 0455 0642

MPJ 0410

MWA 0652

PIA 0585 0587 0590 0653 0656 0660 0676 0

0689 0691

QAF 0473

QSC 0620

R1T 0591

RJA 0416 0445 0490 0491 0531

ROT 0636 0644

RZO 0571 0651 0661

S8G 0300

SBI 0427 0430 0453 0468 0475 0486 0487 0

SGX 0519 0562

SUD 0437

TAP 0483 0494 0495 0541 0565 0573

THY 0386 0476 0478 0480 0496 0497 0502

TSC 0447 0472 0485 0545 0547 0588 0595 0

0658

UAE 0592 0622 0646 0667

UZB 0574 0576 0706

WHT 0448

3
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Config. 01 is valid for all aircraft that 

oversized interference fit bushes install

bearing forward lug position by Repair In

R57249121. If oversized interference fit 

been installed at aft bearing forward lug 

Repair Instruction R57249121 on one wing 

only 1 Kit 572090B01R02 will be necessary

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During routine maintenance, a crack has been found v

rib 5 on two A310 in-service aircraft. The crack was 

forward lug of the MLG rib 5 aft bearing attachment 

concerned aircraft had accumulated 24,000 FC and 27,0

time of finding, refer to OIT 999.0115/06.

In both cases the cracks extended through the entire 

the forward lug. Inspection of the MLG rib 5 forward 

opposite wings was performed after removal of the bu

concerned aircraft. The inspection revealed medium to 

corrosion in the forward lug holes. A laboratory exam

two cracked ribs confirmed that the origin of the cra

pitting corrosion.

The intent of this Service Bulletin has been validat

aircraft MSN 0539 by the application of repair R5724

(2) Objective/Action

This Service Bulletin introduces new bushes with an 

interference fit in the aft bearing forward lugs. Th

the aft bearing attachment is not affected as the bu

installed during production with an increased interf

572090B01R02 2 01

4
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

can be considered as embodied in these positions.

(3) Advantages

Accomplishment of this Service Bulletin will signifi

the likelihood of corrosion and any subsequent crack

forward lug of the MLG rib 5 aft bearing attachment.

Accomplishment of this Service Bulletin will cancel t

requirements of Service Bulletins A310-57A2088 and A

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

(1) Config. 01

(a) Lift the aircraft on jacks.

(b) Remove the LH and RH MLG legs.

(c) Remove the LH and RH MLG secondary doors.

(d) Remove the bushes from the forward lugs of the g

rib 5 aft bearing attachment.

(e) Inspect the lug faces and bores for damage/corro

NOTE : If damage/corrosion is found on a lug it 

necessary to report to AIRBUS for advice 

to repair drawing R57249121.

(f) Install the new bushes in the forward lugs of th

rib 5 aft bearing attachment.

NOTE : It is necessary to freeze fit the new bus

(g) Line-hone the new bushes to the finished interna

(h) Install the LH and RH MLG secondary doors.

(i) Install the LH and RH MLG legs.

5
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(1) Classification

Recommended

(2) Accomplishment Timescale

Accomplishment is recommended at the next MLG overha

earliest opportunity where manpower and facilities a

F. APPROVAL

Approved under the EASA Design Organisation Approval No. 

If an aircraft listed in the effectivity has a modificatio

embodied that is not of AIRBUS origin, and which affects 

this Service Bulletin, the operator is responsible for ob

approval by its airworthiness authority for any adaptatio

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are 

direct labor cost to do the work. These estimates assume 

will be done by experienced personnel, and may need to be 

upwards to suit operator's circumstances. The estimates do 

the time to prepare, plan or inspect the work. Manufactur

procurement of parts and tools, drying times for paints, 

and general administration work are also not included.

Config. 01

Remove LH MLG 

Remove RH MLG 

Remove the LH MLG

secondary door

Remove the RH MLG

secondary door

Remove LH Gear Rib 5

bushes

Remove RH Gear Rib 5

bushes

Inspect bores/faces of the

LH lugs

6
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : If the Repair Instruction R57249121, "Removal of 

the gear rib lugs and the installation of oversized 

necessary, then approximately 52.0 manhours for eac

necessary for repair.

H. WEIGHT AND BALANCE

Not changed

I. ELECTRICAL LOAD DATA

Not changed

J. REFERENCES

K. PUBLICATIONS AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

Not applicable

Install the LH MLG

secondary door

Install the RH MLG

secondary door

Install LH MLG 

Install RH MLG 

Test 

Close up 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Aircraft Maintenance Manual (AMM) : 07-11-00 32-11-11 

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

Non destructive Testing Manual (NTM) : 51-90-00

Process and Mat. Spec. Manual (PMSM) : 01-06-12

Structural Repair Manual (SRM) : 51-21-10 51-76-10

7
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

This Page Intentionally Left Blank

8
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

of this Service Bulletin. The address is :

Airbus Spares Support and Services

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet: http://spa

For ordering by fax: +49 40 50 76 25 

(2) Price and Availability

Kit 572090B01R02

Cost : 3960 US Dollars

Availability : 90 calendar days from receipt of orde

The Kit availability given above is the standard lead 

date of your purchase order. If you require the Kit(

time, please include a retrofit planning schedule wit

so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimat

to economic conditions at the issue date of the Serv

B. INDUSTRY SUPPORT INFORMATION

Airbus will provide a 20 percent reduction to the applica

prices given in paragraph 2A(2) for orders placed before 

2012.

C. LIST OF COMPONENTS

Kit 572090B01R02

NOTE (*) Discard

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

1 A5724244220200 1 Bush (1) A5724244220000 

2 A5724244120200 1 Bush (2) A5724244120000 

9
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE (01) Mat. No. 07-018 is an alternative lacquer t

16-021B when used to protect written part 

NOTE (02) The Marker Pen 8404 can be procured from :

Edding (UK) Ltd.

Merlin Centre

Acrewood Way

St. Albans

Herts

England

(2) Components

None

E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR

NOTE : * Re-identify by marking the SB number "SB A310-57-

to the old part number.

g q

Varnish 07-018 As required 

Sealant, Anaerobic 08-003 As required

Fuel Tank Sealant

Polysulfide

09-002 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

Polyurethane Gloss Finish

(Clear Basecoat)

16-021B As required 

Marker Pen 8404 None 1 

ITEM NEW PART No. KEYWORD ITEM OLD PART No. INT

* Gear Rib A57242444000 02

* Gear Rib A57242444001 02

* Gear Rib A57242444004 02

* Gear Rib A57242444005 02

* Gear Rib A57242444008 02

* Gear Rib A57242444009 02

10
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

the bushes, Items (1) and (2) (Refer to Figure 

— Qty 1 044A411058D-34 Split Location Ring

— Qty 1 044A411058D-35 Bolt

— Qty 1 044A411058D-43 Enerpac Cylinder

— Qty 1 044A411058D-44 Enerpac Hand Pump

— Qty 1 044A411058D-45 Enerpac Connector Hose

— Qty 1 044A411058D-46 Spherical Washer

— Qty 1 044A411058D-47 Location Block

— Qty 4 044A411058D-48 Bolt (for Item 47)

— Qty 1 044A411058D-49 Thrust Washer

— Qty 2 044A411058D-50 Nut

— Qty 1 044A411058D-51 Reaction Block (Aft Bush 

— Qty 1 044A411058D-86 Captive Washer

— Qty 1 044A411058D-87 Shoulder Screw (for item 

— Qty 1 044A411058D-89 Reaction Block (Fwd Bush 

NOTE (02) The tool kit contains the following items for th

of the bushes, Items 1 and 2 (Refer to Figure 1 

— Qty 1 044A411058D-35 Bolt

— Qty 1 044A411058D-39 Installation Block

— Qty 1 044A411058D-43 Enerpac Cylinder

— Qty 1 044A411058D-44 Enerpac Hand Pump

— Qty 1 044A411058D-45 Enerpac Connector Hose

— Qty 1 044A411058D-46 Spherical Washer

— Qty 2 044A411058D-50 Nut

— Qty 1 044A411058D-51 Reaction Block (Fwd Bush 

11
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

diameter after installation (Refer to Figure 2 )

contain an Alignment Tool (truing sleeve) PN MT1

the In-Line Honing Tool.

G. SPECIAL TOOLS

None

12
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY 

MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENAN

REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICA

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBL

PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTH

NECESSARY ON WIRING AND COMPONENTS.

REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIA

CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONT

DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00

(1) Preparation

(a) Config. 01

1 Lift the aircraft on jacks (Refer to AMM 07-

block 1).

2 Remove the LH and RH MLG legs (Refer to AMM 

block 401).

3 Remove the LH and RH MLG secondary doors (Ref

32-12-13 Page block 401).

4 Put access platforms in position in Zones 730

(2) Standard Practices

(a) Part marking with indelible ink (Refer to PMS 0

Para. 2.D.).

(b) Application of protective treatments (Refer to 

Page block 1).

(c) Application of a bead sealant as a fillet (Refe

51-76-10 Page block 201).

B. MODIFICATION

NOTE : The worksteps that follow are applicable to the LH 

(1) Config. 01

13
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(b) Inspection of Lug Faces and Bores

Refer to Figure 1 , Sheet 1

1 Clean the bores of the lugs with a plastic s

Solvent General Purpose (Mat No. 11-026) .

2 Visually inspect the bore and the spotfaces o

make sure there is no corrosion and/or damage

NOTE : If corrosion and/or damage is found vi

not necessary to do the next workstep 

3 Do a dye penetrant flaw detection test of the 

spotfaces of the lug to make sure there is no 

and/or damage (Refer to NTM 51-90-00 Page blo

4 Do a check to make sure that the diameter of 

the lug (dimension F) is within the tolerance 

4.7805 ins. (121.389 to 121.425 mm).

5 If no damage and/or corrosion is found and d

within the tolerance do workstep 3.B.(1)(c).

6 If there is damage and/or corrosion found, o

F is more than the given tolerance, report t

AIRBUS and wait for advice for repair R57249

re-boring tool 044A411058D.

(c) Installation of Bushes

Refer to Figure 1 , Sheet 1 and 3 and Figure 

and 2

1 Apply Chemical Conversion Coating Yellow Alum

13-002) to the bore and the spotfaces of the 

2 Apply Sealant, Anaerobic (Mat No. 08-003) to 

the lug and the mating surface for the seat o

flange.

1 Bush A5724244120000 Item (2

14
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

3 Install these items from Kit 572090B01R02 a

— freeze each bush in sequence in liquid nit

less than three minutes,

— install each bush in sequence in the applic

the bore of forward lug of the aft gear rib 

— allow the bushes to return to ambient tempe

— before the sealant cures, use the installat

(refer to Figure 1 Sheet 3) to make sure th

fully installed.

4 Make sure that the dimension G is within the 

2.785 to 2.797 ins. (70.74 to 71.04 mm).

5 Make sure that the clearance dimension betwee

Item 1 and Item 2 is free of sealant.

6 Assemble the in-line honing tool as shown, re

2 , Sheet 1 .

7 Use the alignment tool (truing sleeve) to set 

in-line honing tool as shown, refer to Figure 

CAUTION : USE ONLY "DELAPENA" HONING FLUID (MAT 

8 Use the in-line honing tool to finish the int

(dimension E) of the bushes, Item 1 and Item 

tolerance of 4.5275 to 4.5289 ins. (114.999 t

and to a surface finish of 32 microns.

9 Use Solvent General Purpose (Mat No. 11-026) 

to clean the area.

10 Apply Adhesion Promoter For Polysulfide Seala

09-028) around the flanges of the bushes, It

11 Apply a continous bead of sealant around the 

bushes, Item 1 and Item 2 to form a fillet se

Tank Sealant Polysulfide (Mat No. 09-002) .

1 Bush A5724244220200 Item 1

1 Bush A5724244120200 Item 2

15
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

the part number, refer to Para. 2.E. and Para. 

Apply Polyurethane Gloss Finish (Clear Basecoat

16-021B) to protect the written SB No. from hyd

C. TEST

(1) Config. 01

(a) The test procedures necessary for the LH and RH 

MLG secondary door are included in the reference 

installation (Refer to Para. D.(1)(a) and (b)).

D. CLOSE UP

(1) Config. 01

(a) Install the LH and RH MLG secondary doors (Refe

32-12-13 Page block 401).

(b) Install the LH and RH MLG legs (Refer to AMM 32

block 401).

(c) Make sure that the work areas are clean and clea

other items of equipment.

(d) Remove the access platforms from Zones 730/740.

(e) Lower the aircraft off jacks (Refer to AMM 07-11

1).

E. DOCUMENTATION

Write in the applicable aircraft records that you have don

given in the Service Bulletin.

16
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 1 Sheet 1

Config. 01: Replacement of Gear Support Rib Bushes

17
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 1 Sheet 2

Config. 01: Replacement of Gear Support Rib Bushes

18
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 1 Sheet 3

Config. 01: Replacement of Gear Support Rib Bushes

19
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 2 Sheet 1

Config. 01: Line Honing of Bushes

20
DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 2 Sheet 2

Config. 01: Line Honing of Bushes

21
7 DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

A - SB WILL BE embodied............. YES/NO (if NO p

If YES, aircraft concerned (as per SB effectivity by default) and 

(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 th

information is needed prior to next normal revision or prior to S

please indicate required service:

Either: Modification Operational Impact (MOI), if available. . YE

Or : Intermediate revision. ................ YE

Important Information: This SB will only be incorporated in your m

operational documentation if this sheet is returned to Airbus and 

duly authorised representative. With the next feasible revision, 

result in

- updating of maintenance documentation to show pre and post S

- updating of maintenance and operational documentation to show 

after embodiment.

If this SB requires previous or simultaneous accomplishment of ot

Airbus shall automatically include them in the manual revisions. 

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.
7 DATE : May 22/07 SERVICE BULLETIN No. : A310

REVISION No. : 00 — Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(Please rate on a scale of 1 to 4, with 4 being the 

- Quality rating of this SB 

- Quality rating of the Accomplishment Instructions 

- Quality rating of the Illustrations 

- Is this SB easy to understand ? 

If you have had difficulties in the accomplishment of this SB plea

the area(s) and give a short description of the issue.

Planning Material Instruct

X Effectivity X Kit content X Preparat

X Reason X List of Materials X Mod/Insp

X Manpower Operator Supplied X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustra

Comments :

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Please return this form to :

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.