A300-600 A300-600

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 MANDATORY

ATA SYSTEM : 57

TITLE : WINGS - COLD EXPANSION OF THE CENTER SPAR SEALING ANGLES OUTBOARD OF RIB 8

ADJACENT TO THE PYLON ATTACHMENT FITTING

MODIFICATION No. : 08609H5276

This page transmits Revision No. 02 of Service Bulletin No. A300-57-6033

ADDITIONAL WORK

No additional work is required by this revision for aircraft modified by any previous issue of this

Service Bulletin.

REASON

This revision has been issued to include the embodiment timescales that are reflected in the associated

Inspection Service Bulletin A300-57-6027 at Rev 07 in the frame of the Extended Service Goal 2

(ESG2) program.

CHANGES

SUMMARY :

- REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. AD reference revised. Modification classification table added.

- EFFECTIVITY

. Effectivity updated.

- REFERENCES/REPERCUSSIONS

. TFU’s added.

PLANNING INFORMATION :

- EFFECTIVITY

. 1.A. Effectivity updated.

- COMPLIANCE

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 1 of 2

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- Accomplishment Timescale

. 1.E.(2) Accomplishment timescales revised and Extended Service Goal (ESG) thresholds added.

- APPROVAL

. 1.F. AD reference revised.

- REFERENCES

. 1.J. AD reference removed.

MATERIAL INFORMATION :

- INDUSTRIAL SUPPORT

. 2.B. Standard sentence revised to latest standard.

ACCOMPLISHMENT INSTRUCTIONS :

- GENERAL

. 3.A. CAUTION added.

- MODIFICATION

. 3.B. Minor corrections.

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

Revision 01 was issued to make the accomplishment of this Service Bulletin mandatory in accordance

with Airworthiness Directive (AD) (Consigne de Navigabilite) No.2003-290(B).

The Change Notices OA and OB were also incorporated.

REVISION SEQUENCE

ORIGINAL : Mar 31/93

REVISION No. : 01 - Dec 18/03

REVISION No. : 02 - Sep 19/11

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

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 MANDATORY

ATA SYSTEM : 57

TITLE : WINGS - COLD EXPANSION OF THE CENTER SPAR SEALING ANGLES OUTBOARD OF RIB 8

ADJACENT TO THE PYLON ATTACHMENT FITTING

MODIFICATION No. : 08609H5276

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During full scale fatigue tests cracks have been found in the vertical web of a center spar sealing angle,

adjacent to Rib 8, at approximately 45,000 simulated flights. At 58,650 flights a crack was subsequently found

in the bottom skin, adjacent to the aft pylon attachment fitting. At 72,000 flights another crack was found

in a sealing angle of the opposite wing.

It was established that the cracking initiated in the vertical web of the sealing angles. There is a possibility of

a similar crack appearing on in-service aircraft which will lead to a rupture of the sealing angles, which may

be followed by cracking of the bottom skin. The incorporation of this modification reduces the probability of

cracks and subsequent difficult and extensive repairs.

This Service Bulletin has been issued for the removal of nine bolts from the sealing angle vertical flange,

the re-machining of the spot faces of the bolt holes, the cold expansion of the nine bolt holes in the vertical

flange, the installation of oversize bolts in the vertical flange and the installation of new oversize bolts at

the skin attachment positions if required.

Accomplishment of this Service Bulletin has been 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.

EVALUATION TABLE

COMPLIANCE Mandatory CANCELS INSPECTION SB No

AD Yes A/C OPERATION AFFECTED No

RELIABILITY AFFECTED No PAX COMFORT AFFECTED No

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 1 of 4

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A300-600 A300-600

SERVICE BULLETIN

SUMMARY

EVALUATION TABLE

COST SAVING Yes ETOPS AFFECTED No

STRUCTURAL LIFE EXTN Yes VENDOR SB INVOLVED No

KIT PRICE (USD) A01 1,249

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 08609H5276

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.

EFFECTIVITY

This Service Bulletin is applicable to these operators :

AAL AAW ABD CES DLH F2I FDX G8E IRA IRM JAL KAC KAL LAA MON MSR OHY QTR TAR THA

NOTE : The intent of this modification has been done in production on aircraft MSN 0645 and subsequent

by modification 08608H5275.

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : 57.60.08.001, 57.60.08.002

OEB : None

AOT : None

SIL : None

LIFE LIMIT : Extended

LINE MAINTENANCE AFFECTED : No

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 2

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A300-600 A300-600

SERVICE BULLETIN

SUMMARY

OTHERS : None

NATURE OF THE WORK

AIRCRAFT : Yes

EQUIPMENT : No

HARD : No

SOFT : No

OBRM : No

MANPOWER

TOTAL MANHOURS 42.0

ELAPSED TIME (HOURS) 29.0

MATERIAL INFORMATION

AIRCRAFT DATA

The modification of one aircraft requires one Kit 576033A01

The kit consists of nuts, bolts and washers.

APPENDICES

None

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 3

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

SUMMARY

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 4

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

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 MANDATORY

ATA SYSTEM : 57

TITLE : WINGS - COLD EXPANSION OF THE CENTER SPAR SEALING ANGLES OUTBOARD OF RIB 8

ADJACENT TO THE PYLON ATTACHMENT FITTING

MODIFICATION No. : 08609H5276

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

A. EFFECTIVITY

(1) Models

B4-601 B4-603 B4-605R B4-620 B4-622 B4-622R C4-620

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft MSN :

0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 0354 0358 0361 0365

0368 0380 0388 0398 0401 0405 0408 0411 0414 0417 0423 0459-0466 0469 0470

0474 0477 0479 0505-0518 0521 0525 0529 0530 0532 0536 0540 0543 0546

0553-0561 0563 0566 0569 0572 0575 0577 0579 0581 0582 0584 0601-0619 0621

0623 0625-0633 0635 0637 0639 0641 0643

(b) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the

time of issue in accordance with the information available to AIRBUS. Any future

changes resulting from transfer of an aircraft from one operator to another will not be

reflected in this list unless the Service Bulletin is revised for another reason.

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 1 of 18

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A300-600 A300-600

SERVICE BULLETIN

OPERATOR MSN

AAL 0423 0459 0460 0461 0463 0466 0469 0470 0474 0506 0507 0508

0509 0510 0511 0512 0513 0514 0515 0516 0517 0606 0610 0612

0615 0619 0626 0639 0643

AAW 0354

ABD 0529 0557

CES 0521 0525 0532

DLH 0380 0401 0405 0623

F2I 0284 0294 0301 0307 0312 0317 0321 0336 0348 0351 0408 0618

FDX 0358 0361 0365 0388 0417 0477 0479 0530 0536 0543 0555 0559

0572 0575 0579 0581 0611 0613 0625 0630 0633

G8E 0462 0465

IRA 0632

IRM 0411 0414 0546 0553 0608

JAL 0602 0617 0621 0637 0641

KAC 0344

KAL 0582 0609 0627 0631

LAA 0601 0616

MON 0540 0556 0604 0605

MSR 0561 0607

OHY 0584 0603

QTR 0554 0560 0614

TAR 0505 0558 0563

THA 0368 0398 0464 0518 0566 0569 0577 0628 0629 0635

(c) Effectivity by MSN and Kit/Configuration

The Kits and configurations applicable to these MSNs are given at the end of this list

0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 0354 0358 0361 0365

0368 0380 0388 0398 0401 0405 0408 0411 0414 0417 0423 0459-0466 0469-0470

0474 0477 0479 0505-0518 0521 0525 0529-0530 0532 0536 0540 0543 0546

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

0553-0561 0563 0566 0569 0572 0575 0577 0579 0581-0582 0584 0601-0619 0621

0623 0625-0633 0635 0637 0639 0641 0643

KIT No. QTY PER A/C CONFIGURATION

576033A01 01 None

01

NOTE : Config. 01 is valid for all the aircraft given in the effectivity of this

Service Bulletin.

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During full scale fatigue tests cracks have been found in the vertical web of a center spar

sealing angle, adjacent to Rib 8, at approximately 45,000 simulated flights. At 58,650 flights

a crack was subsequently found in the bottom skin, adjacent to the aft pylon attachment

fitting. At 72,000 flights another crack was found in a sealing angle of the opposite wing.

It was established that the cracking initiated in the vertical web of the sealing angles.

There is a possibility of a similar crack appearing on in-service aircraft which will lead to a

rupture of the sealing angles, which may be followed by cracking of the bottom skin.

The incorporation of this modification reduces the probability of cracks and subsequent

difficult and extensive repairs.

(2) Objective/Action

This Service Bulletin has been issued for the removal of nine bolts from the sealing angle

vertical flange, the re-machining of the spot faces, the cold expansion of the nine bolt

holes in the vertical flange, the installation of oversize bolts in the vertical flange and the

installation of new oversize bolts at the skin attachment positions if required.

(3) Advantages

The embodiment of this modification reduces the possibility of cracks and the subsequent

difficult and extensive repairs. This modification also allows the inspection threshold to

be extended (refer to ISB A300-57-6027).

(4) Operational/Maintenance Consequences

None

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 3

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to (LH and RH wing):

(1) Defuel and vent the fuel tanks.

(2) Make sure that the applicable manhole covers are removed for access.

(3) Remove any skin attachment bolts in the forward sealing angle, as necessary, to get access

to the bolts in the sealing angle vertical flange.

(4) Remove the nine bolts in the vertical flange of the sealing angle, outboard of Rib 8.

(5) Inspect all the bolt holes, including the skin bolt holes (refer to ISB A300-57-6027).

(6) Inspect the spot faces in the vertical flange for any fatigue damage and repair if necessary.

(7) Rework the spot faces of three bolt holes on each side of the sealing angle vertical flange.

(8) Cold expand the nine bolt holes in the vertical sealing angle.

(9) Install oversize bolts in all the cold expanded bolt holes.

(10) Install oversize bolts at the skin attachment positions where bolts have been removed.

(11) Repair any damage to the fuel tank sealing.

(12) Install the manhole covers.

(13) Refuel the fuel tanks.

(14) Do a fuel leak test.

(15) Close up.

E. COMPLIANCE

(1) Classification

Mandatory

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin has been 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.

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 4

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Embodiment time for SB A300-57-6033.

Normal operation Short Range operation

FC FH FC FH

9,000 18,600 10,600 15,900

NOTE : Short range operation is for aircraft with an average flight time of less than

1.5 hours.

F. APPROVAL

Approved under EASA 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 labour 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.

Kit 576033A01

Get access 8.0

Modification 25.0

Close up 8.0

Test 1.0

TOTAL MANHOURS 42.0

ELAPSED TIME (HOURS) 29.0

H. WEIGHT AND BALANCE

Not changed

I. ELECTRICAL LOAD DATA

Not applicable

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 5

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A300-600 A300-600

SERVICE BULLETIN

J. REFERENCES

Aircraft Maintenance Manual (AMM) : 12-11-28 28-00-00 28-11-22 28-12-00

28-25-00

Structural Repair Manual (SRM) : 51-40-21 51-40-40 51-40-41 51-75-10

51-76-20 51-43-00

Nondestructive Test Manual (NTM) : 51-10-01, Part 6, 51-10-08, Part 6

Inspection Service Bulletin (ISB) A300-57-6027

K. PUBLICATIONS AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

None

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 6

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A300-600 A300-600

SERVICE BULLETIN

2. MATERIAL INFORMATION

A. MATERIAL - PRICE AND AVAILABILITY

(1) Material

Operators 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 SUPPORT CENTER

P.O.Box 630262

22312 HAMBURG

GERMANY

(2) Price and Availability

Kit 576033A01

Cost : 1,249 US dollars

Availability : 120 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.

NOTE : 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 not provide industry support for accomplishment of this Service Bulletin.

C. LIST OF COMPONENTS

Kit 576033A01

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP

2 NSA5478BV6-20 6 Bolt

3 NSA5478BV6-21 6 Bolt

4 NSA5478BV6-22 2 Bolt

5 NSA5479BV4-18Y 2 Bolt

6 NSA5479BV6-10Y 2 Bolt

7 NSA5479BV6-14Y 12 Bolt

8 NSA5479BV6-20Y 2 Bolt

9 NSA5472-6K7 16 Nut

10 NSA5472-4K7 2 Nut

11 NSA5353-06B 32 Washer

12 NSA5353-04B 4 Washer

13 NSA5470-6K7 14 Nut

14 NSA5474-6K7 14 Nut

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 7

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A300-600 A300-600

SERVICE BULLETIN

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP

MAT No.

Cleaning agent Mat. No. 11-026 As required

Sealant Mat. No. 09-005 As required

Cetyl Alcohol Mat. No. 06-005 As required

SPS Lub-7 Mat. No. 06-004 As required *

Primer Mat. No. 16-006 As required

Alodine 1200 Mat. No. 13-002 As required

NOTE : * Alternative to Cetyl Alcohol Mat.No.06-005.

(2) Components

None

E. PARTS TO BE RE-IDENTIFIED BY THE OPERATOR

None

F. TOOLING - PRICE AND AVAILABILITY

No AIRBUS kit will be provided. Parts required are to be purchased from AIRBUS. The address is:

AIRBUS

MATERIAL SUPPORT CENTER

P.O.Box 630262

22312 HAMBURG

GERMANY

ITEM PART NUMBER QTY DESCRIPTION

STD237B/11 1 Radius Cutter

STD237B/13 1 Radius Cutter

STD58/62 1 Spot Face Cutter

STD58/141 1 Spot Face Cutter

CHS442/52 1 Arbor

CHS442/53 1 Arbor

NOTE : A 550 RPM pneumatic drill and chuck key will also be required (Operator supply).

Supply terms for the Cold Expansion Tools listed below are to be negotiated with:

FATIGUE TECHNOLOGY INC.

401 Andover Park East

Seattle

Washington

98188-7605

USA

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 8

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A300-600 A300-600

SERVICE BULLETIN

Cold Expansion Tools

ITEM PART NUMBER QTY DESCRIPTION

LB-20 1 Puller Unit

FT20/200 1 Power Pack

CBSD-8-1-N-1 2 Starting Drill

CBSD-12-1-N-1 2 Starting Drill

CBSR-12-1-N-1 2 Start Reamer

CBSR-8-1-N-1 2 Start Reamer

CBG-12-1-N-1 2 Combination Gage

CBG-8-1-N-1 2 Combination Gage

CBMG-12-1-N 2 Mandrel Gage

CBMG-8-1-N 2 Mandrel Gage

CBS-12-1-N-23F 16 Sleeve

CBS-8-1-N-20F 2 Sleeve

CBM-12-1-N-1-30-V1 2 Mandrel (Short)

CBM-8-1-N-1-30-V1 2 Mandrel (Short)

CBM-12-1-N-1-40-V1 2 Mandrel

CBM-8-1-N-1-30-V1 2 Mandrel

CBCE-42S-1201F 2 Extension Nose Cap

CBCE-42S-0801F 2 Extension Nose Cap

CBR-12-1-N-1-4062 2 Finsh Reamer

CBR-8-1-N-1-2812 2 Finish Reamer

LBOA-20 2 Offset Adapter

G. SPECIAL TOOLS

Refer to para.F.TOOLING

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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This Page Intentionally Left Blank

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL

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

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING : OBEY THE SAFETY REQUIREMENTS AND PROCEDURES FOR WORKING IN

THE FUEL TANKS (REFER TO AMM 28-00-00).

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.

IN CASE OF CONTAMINATION, REFER TO ESPM 20-55-00, CLEANING.

(1) Preparation

(a) Defuel the aircraft (Refer to AMM 28-25-00, Page block 301).

(b) Vent the fuel tanks (Refer to AMM 28-12-00, Page block 301).

(c) Make sure that the manhole covers in the area of Rib 8 are removed (refer to AMM

28-11-22, Page block 401).

NOTE : Contact AIRBUS for applicable jacking instructions if

Modifications/Repairs are to be accomplished at the same time as this

Service Bulletin. The address is:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

NOTE : Contact AIRBUS at the above address for applicable jacking instructions

if any REPAIR is to be accomplished as a result of this Service Bulletin.

(2) Standard Practices

(a) For the removal/installation of fasteners, refer to SRM 51-40-21.

(b) For cold expansion, refer to SRM 51-40-41.

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 11

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SERVICE BULLETIN

(c) For fastener hole and drill data, refer to SRM 51-40-40.

(d) For the repair of paint coatings, refer to SRM 51-75-10.

(e) For the repair of integral tank sealing, refer to SRM 51-76-20.

(f) For torque values, refer to SRM 51-43-00.

B. MODIFICATION

NOTE : The worksteps that follow are applicable to the LH and RH wing unless otherwise

stated.

Refer to Figure 1 thru to Figure 3

CAUTION : MAKE SURE THAT ONLY ALTERNATE BOLTS ARE REMOVED SO THAT THE

ASSEMBLED PARTS CANNOT BE REMOVED.

(1) Find the nine bolts, Item (1), in the vertical flange of the sealing angle, outboard of Rib 8.

Remove the sealant from the bolt heads.

(2) Remove the bolts, Item (1), from the bolt holes one, two, three, five, seven and nine.

Discard the bolts from the bolt holes one, two and three. Retain the bolts from bolt holes

five, seven and nine.

NOTE : Remove any skin attachment bolts which prevent the removal of the bolts from

the vertical flange. Removal of the skin attachment bolts must be kept to a

minimum. Any fasteners removed from the skin will need to be increased to

2nd oversize see paragraph (22).

(3) Do an inspection of the bolt holes that the bolts have been removed from and the spot face

corner radii in the vertical flange for cracks. Use the eddy current technique NTM 51-10-01,

Part 6, Procedure B for bolt holes and eddy current technique NTM 51-10-08, Part 6 for the

spot faces. If any cracks are found report all findings to AIRBUS and repair as detailed in

the Inspection Service Bulletin A300-57-6027.

(4) Temporarily re-install the bolts, Item (1), in bolt holes five, seven and nine in their initial

positions.

(5) Remove and discard the bolts, Item (1) from the bolt holes four, six and eight.

NOTE : Remove any skin attachment bolts which prevent the removal of the bolts from

the vertical flange. Removal of the skin attachment bolts must be kept to a

minimum. Any fasteners removed from the skin will need to be increased to

2nd oversize see paragraph (22).

(6) Do the eddy current inspection as given in para 3.B.(3) at bolt holes four, six and eight.

(7) Machine the spot face of bolt hole two until (refer to Figure 2):

- the diameter is 0.813in. (20.65mm).

- the corner radius is 0.125in. (3.18mm).

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

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A300-600 A300-600

SERVICE BULLETIN

- the maximum increase in depth 0.010in. (0.25mm).

- the surface finish is 63 microns.

(8) Machine the spot faces of holes one and three (Refer to 2) until:

- the diameter is 1.000in.(25.40mm).

- the corner radius is 0.125in. (3.18mm).

- the maximum increase in depth 0.010in. (0.25mm).

- the surface finish is 63 microns.

(9) Apply protection treatment to the machined surfaces. Use Epoxide primer (Mat. No.

16-006) and Alodine 1200 (Mat. No. 13-002).

(10) Drill and ream the bolt holes in the vertical flange to the cold expansion start hole

dimensions shown in Table 1:

Table 1

Hole Number

(Refer to Figure

1)

Max

in.

Max

mm

Min.

in.

Min.

mm

One 0.3770 9.576 0.3750 9.525

Two 0.2520 6.400 0.2500 6.350

Three thru Nine 0.3770 9.576 0.3750 9.525

(11) Do an inspection of the bolt holes for diameter and ovality. Use a combination gage of a

type specified in para.F.TOOLING - PRICE AND AVAILABILITY.

(12) Cold expand the bolt holes one thru nine in the vertical flange of the sealing angle. Use the

tools listed in Figure 3.

(13) Ream the cold expanded bolt holes to the final hole diameters shown in Table 2:

Table 2

Hole Number

(Refer to Figure

1)

Max

in.

Max

mm

Min.

in.

Min.

mm

One 0.4082 10.369 0.4062 10.317

Two 0.2832 7.193 0.2812 7.142

Three thru Nine 0.4082 10.368 0.4062 10.317

(14) Deburr all the bolt holes and clean with Cleaning agent (Mat. No. 11-026).

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 13

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CAUTION : MAKE SURE THAT ALL THE NUTS USED IN THE WORKSTEPS THAT FOLLOW

ARE LUBRICATED. IF THE LUBRICANT IS NOT SUFFICIENT, LUBRICATE THE

NUTS WITH CETYL ALCOHOL (Mat. No. 06-005) OR, AS AN ALTERNATIVE,

USE SPS LUBE-7 (Mat. No. 06-004).

(15) Install the bolts, Item 8, at bolt hole one with the nut, Item 9, and the washer(s), Item 11.

(16) Apply Sealant (Mat. No. 09-005) to the bolt, Item 5, and install the bolt at bolt hole two with

the nut, Item 10, and the washer(s), Item 12.

(17) At bolt holes three, four, six and eight, install the bolt, Item 7, with the nuts, Item 9, and the

washers, Item 11.

(18) Torque the nuts at bolt hole one and bolt holes three thru eight to 195/230 lb.in.(2.20/2.60

mdaN). Torque the bolt at hole two to 60/70 lb.in.(0.68/0.79 mdaN).

(19) Remove and discard the bolts that you temporarily installed at bolt holes five, seven and

nine and do the worksteps 3.B.(12) thru (16) at the holes.

(20) At the bolt holes five and seven, install the bolts, Item 7, with the nuts, Item 9, and the

washer(s), Item 11. At bolt hole nine install the bolt, Item 6, with the nut, Item 9, and

the washer(s), Item 11.

(21) Torque the nuts at bolt holes five, seven and nine to 195/230 lb.in.(2.20/2.60 mdaN).

(22) Oversize the skin attachment holes where bolts have been removed to a maximum diameter

of 0.4027in.(10.228mm) and a minimum diameter of 0.4007in.(10.179mm).

(23) Clean the skin attachment bolt holes with cleaning agent (Mat. No. 11-026).

(24) Install oversize bolts at the skin attachment positions where bolts have been removed.

Refer to Figure 2 for Item numbers.

(25) Torque the nut, Item 13 to 210/230 lbf (2.36/2.60 mdaN). If Item 14 was used torque

the nut to 195/230 lbf (2.20/2.60 mdaN).

(26) Repair any damage to the fuel tank sealant.

C. TEST

(1) Preparation

(a) Make sure that all swarf, tools and equipment have been removed from inside the

fuel tanks.

(b) Install the manhole covers (refer to AMM 28-11-22, Page block 401).

(2) Test

(a) Refuel the wing tanks (refer to AMM 12-11-28, Page block 1)

(b) Do an inspection of the modification area for fuel leaks.

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 14

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SERVICE BULLETIN

D. CLOSE UP

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

E. DOCUMENTATION

Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 15

Printed in France © AIRBUS 2008 All rights reserved
A300-600 A300-600

SERVICE BULLETIN

Figure 1, Sheet 1

Holes to be Cold Expanded

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 16

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SERVICE BULLETIN

Figure 2, Sheet 1

Position of New Items

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 17

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A300-600 A300-600

SERVICE BULLETIN

Figure 3, Sheet 1

Tooling Table

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 18

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SERVICE BULLETIN

REPORTING SHEET

TITLE : WINGS - COLD EXPANSION OF THE CENTER SPAR SEALING ANGLES OUTBOARD OF RIB 8

ADJACENT TO THE PYLON ATTACHMENT FITTING

MODIFICATION No. : 08609H5276

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 embodiement:

.............................................................................................................................................................................

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B - SB HAS BEEN embodied on aircraft: ............................................................................................................

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Operator comments:............................................................................................................................................

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.............................................................................................................................................................................

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 : Advance data................................................................................... YES/NO

Or : Intermediate/Temporary 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: SEDCC1 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 : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 1 of 1

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SERVICE BULLETIN

REPORTING QUALITY

TITLE : WINGS - COLD EXPANSION OF THE CENTER SPAR SEALING ANGLES OUTBOARD OF RIB 8

ADJACENT TO THE PYLON ATTACHMENT FITTING

MODIFICATION No. : 08609H5276

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 futher 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 4 3 2 1

-Quality rating of the Accomplishment Instructions 4 3 2 1

-Quality rating of the Illustrations 4 3 2 1

-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 X Mod/Inspection

X Manpower Operator Supplied 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: SEMB Service Bulletins Management

FAX: (+33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033

REVISION No. : 02 - Sep 19/11 Page : 1 of 1

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