# Airbus Service Bulletin A300-57-6033

Copy: Revision 02 ("U.S. DOT/FAA - SB A300-57-6033 Rev. 02"), 26 pages: PDF https://openairdocs.org/files/sha256/5d/d3/5dd3f05761409ae3932f5c8f2542e745e3bb27b75a1a4949fa9628170b5b8700; text https://openairdocs.org/service-documents/airbus/a300-57-6033/file/5dd3f0576140.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2014-0282; AD 2015-17-09 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A300-57-6033
- Latest revision known: A300-57-6033, Revision 02, dated September 19, 2011 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a300-57-6033

## ADs that cite it (3) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2015-17-09](https://openairdocs.org/ad/2015-17-09.md), effective Sep 24, 2015: Revisions 01 and 02
- [AD 2006-07-07](https://openairdocs.org/ad/2006-07-07.md), effective Apr 17, 2006: Revision 01
- [AD 98-18-02](https://openairdocs.org/ad/98-18-02.md), effective Oct 1, 1998: No revision named

Also cited in [2 proposed ADs](https://openairdocs.org/service-documents/airbus/a300-57-6033/proposed.md), [3 difficulty reports](https://openairdocs.org/service-documents/airbus/a300-57-6033/reports.md).

## Text (26 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2014-0282; AD 2015-17-09 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

A300-600A300-600
SERVICE BULLETIN
REVISION TRANSMITT AL 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 EXP ANSION 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/OPERA TIONAL CONSEQUENCES
. AD reference revised. Modification classification table added.
- EFFECTIVITY
. Effectivity updated.
- REFERENCES/REPERCUSSIONS
. TFU’s added.
PLANNING INFORMA TION :
- EFFECTIVITY
. 1.A. Effectivity updated.
- COMPLIANCE
DA TE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033
REVISION No. : 02 - Sep 19/11 Page : 1 of 2
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### Page 2

A300-600A300-600
SERVICE BULLETIN
REVISION TRANSMITT AL 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.
MA TERIAL INFORMA TION :
- INDUSTRIAL SUPPORT
. 2.B. Standard sentence revised to latest standard.
ACCOMPLISHMENT INSTRUCTIONS :
- GENERAL
. 3.A. CAUTION added.
- MODIFICA TION
. 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 T ransmittal 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
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REVISION No. : 02 - Sep 19/11 Page : 2
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### Page 3

A300-600A300-600
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 EXP ANSION 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.
EVALUA TION T ABLE
COMPLIANCE Mandatory CANCELS INSPECTION SB No
AD Ye s A/C OPERA TION AFFECTED No
RELIABILITY AFFECTED No P AX COMFORT AFFECTED No
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### Page 4

A300-600A300-600
SERVICE BULLETIN
SUMMARY
EVALUA TION T ABLE
COST SAVING Ye s ETOPS AFFECTED No
STRUCTURAL LIFE EXTN Ye s VENDOR SB INVOL VED No
KIT PRICE (USD) A01 1,249
MODIFICA TION CLASSIFICA TION
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 T AR 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
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### Page 5

A300-600A300-600
SERVICE BULLETIN
SUMMARY
OTHERS : None
NATURE OF THE WORK
AIRCRAFT : Y es
EQUIPMENT : No
HARD : No
SOFT : No
OBRM : No
MANPOWER
TOTAL MANHOURS 42.0
ELAPSED TIME (HOURS) 29.0
MATERIAL INFORMATION
AIRCRAFT DA T A
The modification of one aircraft requires one Kit 576033A01
The kit consists of nuts, bolts and washers.
APPENDICES
None
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### Page 6 (OCR)

© A300-600
SERVICE BULLETIN
SUMMARY
CENTER SPAR  RIB 8 FWD
RIB 8 AFT
A
OUTS
SEALING ANGLE
STGR 13
DB7 57 6033 AA SA A  STGR 11
COLD EXPAND NINE HOLES
IN VERTICAL FLANGE
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

### Page 7

A300-600A300-600
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 EXP ANSION OF THE CENTER SPAR SEALING ANGLES OUTBOARD OF RIB 8
ADJACENT TO THE PYLON ATTACHMENT FITTING
MODIFICATION No. : 08609H5276
This document contains AIRBUS PROPRIET ARY INFORMA TION 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. P LANNING INFORMATION
A. E FFECTIVITY
(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.
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### Page 8

A300-600A300-600
SERVICE BULLETIN
OPERA TOR 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
T AR 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
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### Page 9

A300-600A300-600
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 CONFIGURA TION
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. C ONCURRENT REQUIREMENTS
None
C. R EASON
(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
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### Page 10

A300-600A300-600
SERVICE BULLETIN
D. D ESCRIPTION
T o 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. C OMPLIANCE
(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.
DA TE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033
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### Page 11

A300-600A300-600
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. A PPROVAL
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. M ANPOWER
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
T est 1.0
TOTAL MANHOURS 42.0
ELAPSED TIME (HOURS) 29.0
H. W EIGHT AND BALANCE
Not changed
I. E LECTRICAL LOAD DATA
Not applicable
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### Page 12

A300-600A300-600
SERVICE BULLETIN
J. R EFERENCES
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 T est Manual (NTM) : 51-10-01, Part 6, 51-10-08, Part 6
Inspection Service Bulletin (ISB) A300-57-6027
K. P UBLICATIONS AFFECTED
None
L. I NTERCHANGEABILITY/MIXABILITY
None
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### Page 13

A300-600A300-600
SERVICE BULLETIN
2. M ATERIAL INFORMATION
A. M ATERIAL - 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
MA TERIAL 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. I NDUSTRY SUPPORT INFORMATION
AIRBUS will not provide industry support for accomplishment of this Service Bulletin.
C. L IST OF COMPONENTS
Kit 576033A01
ITEM NEW P ART No. QTY UM KEYWORD ITEM OLD P ART 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
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### Page 14

A300-600A300-600
SERVICE BULLETIN
D. L IST OF MATERIALS - OPERATOR SUPPLIED
(1) Consumable Materials
DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP
MA T 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. P ARTS TO BE RE-IDENTIFIED BY THE OPERATOR
None
F. T OOLING - PRICE AND AVAILABILITY
No AIRBUS kit will be provided. Parts required are to be purchased from AIRBUS. The address is:
AIRBUS
MA TERIAL SUPPORT CENTER
P .O.Box 630262
22312 HAMBURG
GERMANY
ITEM P ART 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 T ools listed below are to be negotiated with:
FA TIGUE TECHNOLOGY INC.
401 Andover Park East
Seattle
Washington
98188-7605
USA
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### Page 15

A300-600A300-600
SERVICE BULLETIN
Cold Expansion T ools
ITEM P ART 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. S PECIAL TOOLS
Refer to para.F .TOOLING
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A300-600A300-600
SERVICE BULLETIN
This Page Intentionally Left Blank
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A300-600A300-600
SERVICE BULLETIN
3. A CCOMPLISHMENT INSTRUCTIONS
A. G ENERAL
WARNING : MAKE SURE THA T 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 T ANKS (REFER TO AMM 28-00-00).
CAUTION : ALWAYS OBEY THE PRECAUTIONS THA T FOLLOW TO KEEP ELECTRICAL
WIRING IN A SA TISFACTORY CONDITION (ELECTRICALL Y AND MECHANICALL Y
SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REP AIRS OR
MODIFICA TIONS, ALWA YS 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
- REGULARL Y REMOVE ALL SHAVINGS, UNWANTED MA TERIAL AND OTHER
CONT AMINA TION.
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONT AMINA TION AND
DAMAGE TO THE ELECTRICAL WIRING INST ALLA TION.
IN CASE OF CONT AMINA TION, 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 DIRECTORA TE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
NOTE : Contact AIRBUS at the above address for applicable jacking instructions
if any REP AIR 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.
DA TE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033
REVISION No. : 02 - Sep 19/11 Page : 11
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A300-600A300-600
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. M ODIFICATION
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 THA T ONL Y AL TERNA TE BOL TS ARE REMOVED SO THA T THE
ASSEMBLED P ARTS 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) T emporarily 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).
DA TE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033
REVISION No. : 02 - Sep 19/11 Page : 12
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A300-600A300-600
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 T able 1:
Ta b l e 1
Hole Number
(Refer to Figure
1)
Max
in.
Max
mm
Min.
in.
Min.
mm
One 0.3770 9.576 0.3750 9.525
Tw o 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 T able 2:
Ta b l e 2
Hole Number
(Refer to Figure
1)
Max
in.
Max
mm
Min.
in.
Min.
mm
One 0.4082 10.369 0.4062 10.317
Tw o 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).
DA TE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033
REVISION No. : 02 - Sep 19/11 Page : 13
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A300-600A300-600
SERVICE BULLETIN
CAUTION : MAKE SURE THA T ALL THE NUTS USED IN THE WORKSTEPS THA T FOLLOW
ARE LUBRICA TED. IF THE LUBRICANT IS NOT SUFFICIENT , LUBRICA TE THE
NUTS WITH CETYL ALCOHOL (Mat. No. 06-005) OR, AS AN AL TERNA TIVE,
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) T orque the nuts at bolt hole one and bolt holes three thru eight to 195/230 lb.in.(2.20/2.60
mdaN). T orque 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) T orque 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) T orque 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. T EST
(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) T est
(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.
DA TE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033
REVISION No. : 02 - Sep 19/11 Page : 14
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A300-600A300-600
SERVICE BULLETIN
D. C LOSE UP
(1) Make sure that the work areas are clean and clear of tools and other items of equipment.
E. D OCUMENTATION
Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.
DA TE : 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

### Page 22 (OCR)

© A300-600
SERVICE BULLETIN
CENTER SPAR  RIB 8 FWD
RIB 8 AFT
OUTB
SEALING ANGLE
HOLE  HOLE
THREE  FIVE
HOLE  HOLE
TWO  HOLE  EIGHT
FOUR  IC HOLE  HOLE  HOLE
SIX  SEVEN  NINE
STGR 13
HOLE
ONE
DB7 57 6033 AA AA A  STGR 11
NOTE: THE VIEW SHOWN ON ARROW A IS
NOT AS SEEN FROM THE MANHOLE
SKIN ATTACHMENT BOLTS TO BE
REMOVED ONLY IF CAUSING AN
OBSTRUCTION
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
Printed in France © AIRBUS 2008 All rights reserved

### Page 23 (OCR)

© A300-600
SERVICE BULLETIN
SECTION
B- B  1.00 in
(25.40 mm)
0.813 in
RIB 8 DATUM  (20.65 mm)
1.00 in
(25.40 mm)
VIEW ON LH WING TOP SKIN REMOVED
RH WING SIMILAR BUT OPPOSITE  7  5  THREE  HOLE  HOLE  TWO  HOLE
9  ONE
11  CORNER RADIUS
0.125 in (3.18mm)
TYPICAL
VIEW ON CENTER
SPAR LOOKING
FORWARD
OUTSIDE SKIN
LINE
4
13
CENTER
SPAR
DATUM
+ +
DB7 57 6033 AC AA A  NOTE: ITEM 14 CAN BE
USED WHEN IT IS
NOT POSSIBLE TO  PLAN VIEW ON BOTTOM SKIN
USE ITEM 13.
RIB 8 DATUM
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
Printed in France © AIRBUS 2008 All rights reserved

### Page 24 (OCR)

© A300-600
SERVICE BULLETIN
COLD EXPANSION
OF HOLES
STARTING DRILL  CBSD-8-1-N-1  CBSD-12-1-N-1
STARTING REAMER  CBSR-8-1-N-1  CBSR-12-1-N-1
COMBINATION GAGE  CBG-8-1-N-1  CBG-12-1-N-1
MANDREL  CBM-8-1-N-1-30-V1  CBM-12-1-N-1-30-V1
MANDREL  CBM-8-1-N-1-40-V1  CBM-12-1-N-1-40-V1
MANDREL GAGE  CBMG-8-1-N  CBMG-12-1-N
EXTENSION NOSE CAP  CBCE-42S-0801F  CBCE-42S-1201F
SLEEVE  CBS-8-12-N-20F  CBS-12-1-N-23F
FINAL REAMER  CBR-8-1-N-1-2812  CBR-12-1-N-1-4062
RADIUS CUTTER  STD237B/11  STD237B/13
DEBURR CUTTER  STD261/89  STD261/91
CSK CAGE  RB306  RB306
SPOTFACE CUTTER  STD58/62  STD58/141
ARBOR  CHS442/52  CHS442/53
D_SB_576033_7_AAXX_01_00
Figure 3, Sheet 1
Tooling Table
DATE: Mar 31/93  SERVICE BULLETIN No. : A300-57-6033
REVISION No. : 02 - Sep 19/11  Page : 18
Printed in France © AIRBUS 2008 All rights reserved

### Page 25

A300-600A300-600
SERVICE BULLETIN
REPORTING SHEET
TITLE : WINGS - COLD EXP ANSION 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 W ILL 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:
.............................................................................................................................................................................
.............................................................................................................................................................................
B - SB H AS 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 : Advance data................................................................................... YES/NO
Or : Intermediate/T emporary 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 DIRECTORA TE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX FRANCE
Attn: SEDCC1 T echnical 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.
DA TE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033
REVISION No. : 02 - Sep 19/11 Page : 1 of 1
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### Page 26

A300-600A300-600
SERVICE BULLETIN
REPORTING QUALITY
TITLE : WINGS - COLD EXP ANSION 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 T est
X References X Re-identification X Close-up
X Publication X T ooling X Illustrations
Comments :
Operator : Date:
Name/Title :
Please return this form to:
AIRBUS
CUSTOMER SERVICES DIRECTORA TE
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.
DA TE : Mar 31/93 SERVICE BULLETIN No. : A300-57-6033
REVISION No. : 02 - Sep 19/11 Page : 1 of 1
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