# Airbus Service Bulletin A300-57-6046

Copy: Revision 03 ("SB A300-57-6046 R3"), 54 pages: PDF https://openairdocs.org/files/sha256/26/98/2698750bed0035c3de6b998065bf79f37f666427b21d2bb52b3ee70bd2220993; text https://openairdocs.org/service-documents/airbus/a300-57-6046/file/2698750bed00.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-9572; AD 2017-15-03 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: A300-57-6046
- Latest revision known: A300-57-6046, Revision 03, dated February 4, 2015 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a300-57-6046

## ADs that cite it (2) (OpenAirDocs)

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

- [AD 2017-15-03](https://openairdocs.org/ad/2017-15-03.md), effective Aug 25, 2017: Revisions 01, 02 and 03
- [AD 2014-08-02](https://openairdocs.org/ad/2014-08-02.md), effective May 21, 2014: Revisions 01 and 02

Also cited in [2 proposed ADs](https://openairdocs.org/service-documents/airbus/a300-57-6046/proposed.md).

## Text (54 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-9572; AD 2017-15-03 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

@A300-600
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 57
TITLE: WINGS - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB14
MODIFICATION No.: 10326H5339
This page transmits Revision No.03 of Service Bulletin No.A300-57-6046
ADDITIONAL WORK
**CONF ALL
No additional work is required by this revision for aircraft modified by any previous issue.
REASON
Revision No. 03 issued to change the Mandatory threshold to 30000 FC from first flight.
CHANGES
SUMMARY
MATERIAL PRICE INFORMATION
 MATERIAL PRICE INFORMATION TABLE
UPDATED
R
MATERIAL PRICE INFORMATION TABLE
UPDATED
R
EFFECTIVITY
 OPERATOR LIST UPDATED
 R
PLANNING INFORMATION
EFFECTIVITY
 EFFECTIVITY RELATED INFORMATION
UPDATED
R
Configuration definition
CONF 001
 CONFIGURATION DEFINITION UPDATED
 R
CONF 002
 CONFIGURATION DEFINITION UPDATED
 R
COMPLIANCE
Accomplishment Timescale
 ACCOMPLISHMENT TIMESCALE UPDATED
 R
APPROVAL
 APPROVAL UPDATED
 R
REFERENCES
 REFERENCED DOCUMENTATION UPDATED
 R
REFERENCED DOCUMENTATION UPDATED
 R
MATERIAL INFORMATION
MATERIAL - PRICE AND AVAILABILITY
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 1
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 2

@A300-600
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Price and Availability
 PRICE AND AVAILABILITY UPDATED
MATERIAL PRICE UPDATED
R
ACCOMPLISHMENT INSTRUCTIONS
TASK 576046- 831-895-001-
MODIFICATION
TASK SOLUTION UPDATED
NOTE UPDATED
CAUTION UPDATED
R
Subtask 576046-910-401-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
REFERENCES UPDATED
R
Subtask 576046-910-401-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
REFERENCES UPDATED
R
Subtask 576046-941-401-001
 SUBTASK SOLUTION UPDATED
NOTE UPDATED
WARNING UPDATED
R
Subtask 576046-941-401-001
 SUBTASK SOLUTION UPDATED
NOTE UPDATED
WARNING UPDATED
R
Subtask 576046-831-401-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
REFERENCES UPDATED
R
Subtask 576046-831-402-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
REFERENCES UPDATED
R
Subtask 576046-831-403-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
REFERENCES UPDATED
R
Subtask 576046-750-401-001
 New detailed visual and HFEC inspection added
 R
Subtask 576046-831-401-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
REFERENCES UPDATED
R
Subtask 576046-831-402-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
REFERENCES UPDATED
R
Subtask 576046-831-403-002
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
REFERENCES UPDATED
R
Subtask 576046-750-401-001
 New detailed visual and HFEC inspection added
 R
Subtask 576046-914-401-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
R
Subtask 576046-942-401-001
 SUBTASK SOLUTION UPDATED
 R
Subtask 576046-914-401-001
 SUBTASK SOLUTION UPDATED
REFERENCED DOCUMENTATION UPDATED
R
Subtask 576046-942-401-001
 SUBTASK SOLUTION UPDATED
 R
APPENDIX 01: INSPECTION REPORT FORM
APPENDIX CONTENT
 APPENDIX CONTENT ADDED
 N
Fig. A-URAAA
 FIGURE SOLUTION ADDED
 N
Fig. A-URAAA Sheet 01
 SHEET ADDED
 N
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 2
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 3

@A300-600
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
APPENDIX
 APPENDIX DELETED
 D
FILING INSTRUCTIONS
This Service Bulletin has been generated electronically and is reissued as a complete document.
Replace the complete document.
Put this Revision Transmittal Sheet in front of the Service Bulletin.
HISTORY OF PREVIOUS REVISIONS
Revision No. 02 issued:
to include a High Frequency Eddy Current (HFEC) inspection after accomplishment of this modification
Service Bulletin.
The opportunity is taken to produce this Service Bulletin in the latest format.
NOTE
: This is only applicable for Revision No. 03 and subsequent. If information is required for
Revisions issued previous to this, please check your copies of Revision Transmittal
Sheets or contact AIRBUS.
REVISION SEQUENCE
ORIGINAL: Jan 18/94
REVISION No. : 02 - Jun 21/13
REVISION No. : 03 - Feb 04/15
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 3
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 4

@A300-600
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
This Page Intentionally Left Blank
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 4
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 5

@A300-600
SERVICE BULLETIN
SUMMARY
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
This summary is for information only and is not approved for modification of the aircraft.
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 57
TITLE: WINGS - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB14
**CONF ALL
MODIFICATIONS
MODIFICATION CLASSIFICATION
MAJOR
 None
MINOR
 10326H5339
NOTE
: As per EASA IR 21, a minor change is one that has no appreciable effect on the
mass, balance, structural strength, reliability, operational characteristics affecting the
airworthiness of the product. All other changes are major changes.
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
Cracks were found during full-scale fatigue testing in the bottom skin stringers at Rib 14. Following the
introduction of Maintenance Review Board (MRB) document inspection SSI 57-21-64 and SSI 57-21-78,
cracks were found on in-service aircraft in the same area.
The accomplishment of this Service-Bulletin improves the design of the stringer run-outs by re-profiling.
This will reduce the risk of cracks initiating at the stringer run-outs.
This Service-Bulletin also details the removal of the stringer end run-out plate at Stringer 19 on the
bottom skin. This will relieve stresses from the rear spar at Rib 14.
This Service-Bulletin also details the re-profiling of the Stringer 19 end run-out.
This modification limits the occurrence of cracks by reducing the stress concentrations in the affected
areas.
The embodiment of this Service Bulletin cancels the MRB document inspection SSI 57-21-64 and SSI
57-21-78 and changes the inspection requirements of SSI 57-21-66.
GENERAL EVALUATION
EVALUATION TABLE
COMPLIANCE
 MANDATORY (1)
 CANCELS INSPECTION SB
 NO
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 1
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 6

@A300-600
SERVICE BULLETIN
SUMMARY
EVALUATION TABLE
POTENTIAL AD
 YES
 A/C OPERATION AFFECTED
 NO
RELIABILITY AFFECTED
 NO
 PAX COMFORT AFFECTED
 NO
COST SAVING
 NO
 ETOPS AFFECTED
 NO
STRUCTURAL LIFE EXTN
 YES
 VENDOR SB INVOLVED
 NO
DEFUEL/VENTING
 YES
NOTE
 (1)
: Service Bulletin must be accomplished.
MATERIAL PRICE INFORMATION
**CONF 001
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 576046B01R00
 1
 2,360.00
 BOLTS, NUTS, WASHERS
Standard tool TOOLB01
 1
 See SB
 FTI KIT
**CONF 002
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 576046B02R00
 1
 2,360.00
 BOLTS, NUTS, WASHERS
EFFECTIVITY
**CONF ALL
This Service Bulletin is applicable to this (these) operator(s) :
36V
 67Q
 ABR AHK
 BCS CES F2I FDX IRA IRM KAC MNB
 MON
MSR SUD TAR THA UQA
 UZB
CONCURRENT REQUIREMENTS
None
REFERENCES / REPERCUSSIONS
TFU
 None
OEB
 None
AOT
 None
SIL
 None
LINE MAINTENANCE AFFECTED
 No
LIFE LIMIT
 None
OTHER
 None
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 2
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 7

@A300-600
SERVICE BULLETIN
SUMMARY
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
HARD
 NO
SOFT
 NO
OBRM
 NO
MANPOWER
**CONF 001
Task 576046-831-895-001: MODIFICATION
TOTAL MANHOURS
 63.00
ELAPSED TIME (HOURS)
 28.50
**CONF 002
Task 576046-831-895-001: MODIFICATION
TOTAL MANHOURS
 53.00
ELAPSED TIME (HOURS)
 25.50
APPENDICES
**CONF ALL
APPENDIX 01: INSPECTION REPORT FORM
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 3
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 8

@A300-600
SERVICE BULLETIN
SUMMARY
**CONF ALL
A
VIEW ON PANEL No. 3 BOTTOM SKIN:
STRINGERS 10, 11, 12 AND 17 EITHER SIDE OF RIB 14
(STRINGER 19 SIMILAR)
PROFILE BEFORE PROFILE AFTER
STRINGER
DATUM
RIB14
REAR
FRONT
MODIFICATION AREA
NOTE:
STRINGERS
SPAR
SPAR
RIB14
A
LH WING SHOWN
RH WING SIMILAR
D_SB_576046_7_SAAA_01_00
Figure A-USAAA - Sheet 01
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 4
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 9

@A300-600
SERVICE BULLETIN
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 57
TITLE: WINGS - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB14
MODIFICATION No.: 10326H5339
This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the
property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with
any information contained in it. It is delivered on the express condition that said document and the
information contained in it shall be treated as confidential, shall not be used for any purpose other than
that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall
not be duplicated in any manner (except for the purposes of performing the tasks described hereunder
and provided that any recipient of such document shall comply with the conditions herein), without
AIRBUS prior written consent.
1. PLANNING INFORMATION
**CONF ALL
A. EFFECTIVITY
This modification is embodied prior to delivery on A/C MSN 0723 and subsequent.
(1) Models
B4-603 B4-605R B4-620 B4-622 B4-622R C4-620
(2) Effectivity by MSN
0294 0344 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0477 0479
0505 0521 0525 0529-0530 0532 0536 0543 0546 0553
 0555
 0557-0559
 0561
 0563
0572 0575 0577 0579 0581
 0584 0602-0605 0607-0608
 0611 0613
 0617-0618 0621
0623 0625-0626
 0629-0630
 0632-0633
 0637 0641 0643 0657 0659 0664 0666 0668
0670 0673 0677 0679 0681 0683 0688 0694 0696 0699 0701 0703 0705 0707 0709
0711 0713 0715 0717 0719 0721-0722
(3) Effectivity by Operator
The Operator/MSN relationship is provided for information only and is correct at the time
of issue in accordance with the information available to AIRBUS. Any future changes
resulting from transfer of an aircraft from one operator to another will not be reflected in
this list unless the Service Bulletin is revised for another reason.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 1
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 10

@A300-600
SERVICE BULLETIN
OPERATOR
 MSN
36V
 0605
67Q
 0584
 0603
ABR
 0677
AHK
 0683
BCS
 0602 0617 0621 0637 0641 0670 0679 0703 0711
CES
 0707
F2I
 0294 0529
 0557
FDX
 0358 0361 0365 0388 0417 0477 0479 0530 0536 0543 0555 0559
0572 0575 0579 0581 0611 0613 0625 0630 0633 0657 0659 0664
0668 0688 0709 0713 0715
IRA
 0632 0696
IRM
 0380 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701
KAC
 0344 0673 0694 0699 0719 0721
MNB
 0521
 0525
 0532
MON
 0604
MSR
 0561 0607
SUD
 0666
TAR
 0505 0558 0563
THA
 0577 0629 0681 0705
UQA
 0626
 0643
UZB
 0717 0722
(4) Configuration by MSN
MSN
 CONFIGURATION
0294 0344 0358 0361 0365 0380 0388 0401 0405 0408 0411
0414 0417 0477 0479 0505
001
0521 0525 0529 0530 0532 0536 0543 0546 0553 0555 0557
0558 0559 0561 0563 0572 0575 0577 0579 0581 0584 0602
0603 0604 0605 0607 0608 0611 0613 0617 0618 0621 0623
0625 0626 0629 0630 0632 0633 0637 0641 0643 0657 0659
0664 0666 0668 0670 0673 0677 0679 0681 0683 0688 0694
0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717
0719 0721 0722
002
(5) Configuration definition
**CONF 001
Config. 001 is applicable to aircraft Pre Mod. No. 07207H1066.
**CONF 002
Config. 002 is applicable to aircraft Post Mod. No. 07207H1066.
(6) Material Effectivity
**CONF 001
MATERIAL
 QTY PER A/C
 SEE NOTES
Kit 576046B01R00
 1
 (1)
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 2
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 11

@A300-600
SERVICE BULLETIN
MATERIAL
 QTY PER A/C
 SEE NOTES
Standard tool TOOLB01
 1
Consumable CMLB01
 As required
NOTE
 (1)
: KITB01 contains the component parts to modify the LH and RH wings.
**CONF 002
MATERIAL
 QTY PER A/C
 SEE NOTES
Kit 576046B02R00
 1
 (1)
Consumable CMLB01
 As required
NOTE
 (1)
: KITB02 contains the component parts to modify the LH and RH wings.
**CONF ALL
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
Cracks were found during full-scale fatigue testing in the bottom skin stringers at Rib 14.
Following the introduction of Maintenance Review Board (MRB) document inspection
SSI 57-21-64 and SSI 57-21-78, cracks were found on in-service aircraft in the same
area.
(2) Objective/Action
The accomplishment of this Service-Bulletin improves the design of the stringer run-outs
by re-profiling. This will reduce the risk of cracks initiating at the stringer run-outs.
This Service-Bulletin also details the removal of the stringer end run-out plate at Stringer
19 on the bottom skin. This will relieve stresses from the rear spar at Rib 14.
This Service-Bulletin also details the re-profiling of the Stringer 19 end run-out.
(3) Advantages
This modification limits the occurrence of cracks by reducing the stress concentrations in
the affected areas.
The embodiment of this Service Bulletin cancels the MRB document inspection SSI
57-21-64 and SSI 57-21-78 and changes the inspection requirements of SSI 57-21-66.
(4) Operational/Maintenance Consequences
None
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 3
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 12

@A300-600
SERVICE BULLETIN
D. DESCRIPTION
To accomplish this Service Bulletin it is necessary to :
**CONF 001
Task 576046-831-895-001: MODIFICATION
(1) RE-PROFILE THE STRINGER RUN-OUTS
(2) RE-PROFILE THE STRINGER 19 RUN-OUT
(3) REMOVE THE STRINGER END RUN-OUT PLATE ON STRINGER 19
(4) DETAILED VISUAL AND HFEC INSPECTION
**CONF 002
Task 576046-831-895-001: MODIFICATION
(1) RE-PROFILE THE STRINGER RUN-OUTS
(2) RE-PROFILE THE STRINGER 19 RUN-OUT
(3) REMOVE THE STRINGER END RUN-OUT PLATE ON STRINGER 19
(4) DETAILED VISUAL AND HFEC INSPECTION
**CONF ALL
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
The accomplishment of this Service Bulletin is mandatory at or before 30000 Flight
Cycles (FC) from first flight or within 2000 FC from the issue date of this Service Bulletin
at Revision No. 03.
This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness
Directive (AD) published by the European Av iation Safety Agenc y (EASA) will be issued
to confirm this classification. It is anticipated that the AD will confirm the thresholds
and/or intervals and/or date given but reference should be made to the AD for
confirmation of the mandated accomplishment timescale.
F. APPROVAL
The technical content of this document is approved under the authority of Design
Organisation Approval No.
 EASA.21J.031.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 4
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 13

@A300-600
SERVICE BULLETIN
If an aircraft listed in the effectivity has a modification or repair embodied that is not of
AIRBUS origin, and which affects the content of this Service Bulletin, the operator is
responsible for obtaining approval by its airworthiness authority for any adaptation necessary
before incorporation of the Service Bulletin.
G. MANPOWER
The manpower estimates given in this Service Bulletin are based on the direct labor cost to
do the work. These estimates assume that the work will be done by experienced personnel,
and may need to be revised upwards to suit operator’s circumstances. The estimates do not
include the time to prepare, plan or inspect the work. Manufacture and procurement of parts
and tools, drying times for paints, sealants, etc., and general administration work are also not
included.
**CONF 001
Task 576046-831-895-001: MODIFICATION
Get Access
 13.00
On Aircraft
RE-PROFILE THE STRINGER RUN-OUTS
 15.00
RE-PROFILE THE STRINGER 19 RUN-OUT
 2.00
REMOVE THE STRINGER END RUN-OUT PLATE ON
STRINGER 19
15.00
DETAILED VISUAL AND HFEC INSPECTION
 3.00
Close-Up
 15.00
TOTAL MANHOURS
 63.00
ELAPSED TIME (HOURS)
 28.50
**CONF 002
Task 576046-831-895-001: MODIFICATION
Get Access
 13.00
On Aircraft
RE-PROFILE THE STRINGER RUN-OUTS
 15.00
RE-PROFILE THE STRINGER 19 RUN-OUT
 2.00
REMOVE THE STRINGER END RUN-OUT PLATE ON
STRINGER 19
5.00
DETAILED VISUAL AND HFEC INSPECTION
 3.00
Close-Up
 15.00
TOTAL MANHOURS
 53.00
ELAPSED TIME (HOURS)
 25.50
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 5
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 14

@A300-600
SERVICE BULLETIN
**CONF ALL
H. WEIGHT AND BALANCE
The weight and balance estimates given in this Service Bulletin are based on the
Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition
of (MEW) and operator’s items refer to the Weight and Balance Manual (WBM) Chapter
1-00-07.
Manufacturers Empty Weight -3.210 KG (-7.077 LB)
Effect on Balance -101.115 KGM (-731.364 LB.FT )
I. ELECTRICAL LOAD DATA
Not Changed
J. REFERENCES
**CONF 001
Aircraft Maintenance Manual (AMM)
 20-21-12 20-31-00 28-00-00
28-10-00 28-11-00 28-11-22
28-25-00
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
Non Destructive Test Manual (NTM)
 51-10-01 57-21-64
Process and Material Specification (PMS)
Service Information Letter (SIL)
 51-012
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-23-20 51-24-00 51-27-11
51-35-00 51-40-00
 51-40-20
51-40-21 51-40-40 51-40-41
51-40-46 51-49-00
 51-75-10
51-76-10 51-76-20
Weight and Balance Manual (WBM)
 Chapter 1-00-07
**CONF 002
Aircraft Maintenance Manual (AMM)
 20-21-12 20-31-00 28-00-00
28-10-00 28-11-00 28-11-22
28-25-00
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
Non Destructive Test Manual (NTM)
 51-10-01 57-21-64
Process and Material Specification (PMS)
Service Information Letter (SIL)
 51-012
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-23-20 51-24-00 51-27-11
51-35-00 51-40-00
 51-40-20
51-40-21 51-40-40 51-40-41
51-40-44 51-40-46 51-49-00
51-75-10 51-76-10 51-76-20
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 6
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 15

@A300-600
SERVICE BULLETIN
Weight and Balance Manual (WBM)
 Chapter 1-00-07
**CONF ALL
K. PUBLICATION AFFECTED
Maintenance Planning Document (MPD)
 SSI 57-21-64
SSI 57-21-66
SSI 57-21-78
Structural Repair Manual (SRM)
 57-20-14
L. INTERCHANGEABILITY/MIXABILITY
Not Applicable
M. SPARES
None
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 7
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 16

@A300-600
SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 8
7
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### Page 17

@A300-600
SERVICE BULLETIN
2. MATERIAL INFORMATION
**CONF ALL
A. MATERIAL - PRICE AND AVAILABILITY
(1) Procurement Addresses
Customers with aircraft shown in the effectivity of this Service Bulletin should send a
purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:
Kit 576046B01R00
Kit 576046B02R00
AIRBUS Material, Logistics and Suppliers
Weg beim Jaeger 150
D-22335 HAMBURG
GERMANY
For ordering by internet:
http://spares.airbus.com
For ordering by fax: +49 40 50 76 2590
For ordering by E-mail: airbus.kit@airbus.com
(2) Price and Availability
Kit 576046B01R00
Cost
 2,360.00
 USD
Availability
 180 calendar days from receipt of order
The availability given above is the standard lead time from the date of your purchase
order. If items are required before this time, please include a retrofit planning schedule
with your order so that we can try to comply with your requirements.
The sales terms (costs and availability) are estimated in relation to economic conditions.
The latest valid price and lead time for ordering purposes shall be obtained through the
AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.
Kit 576046B02R00
Cost
 2,360.00
 USD
Availability
 180 calendar days from receipt of order
The availability given above is the standard lead time from the date of your purchase
order. If items are required before this time, please include a retrofit planning schedule
with your order so that we can try to comply with your requirements.
The sales terms (costs and availability) are estimated in relation to economic conditions.
The latest valid price and lead time for ordering purposes shall be obtained through the
AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 9
7
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### Page 18

@A300-600
SERVICE BULLETIN
B. INDUSTRY SUPPORT INFORMATION
AIRBUS will not provide industry support for accomplishment of this Service Bulletin.
C. LIST OF COMPONENTS
Kit 576046B01R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
1
 NSA5475-6K7
 20
 NUT
2
 NSA5476VHK6-11
 10
 BOLT
3
 NSA5476VHK6-14
 10
 BOLT
4
 NSA5353-06A
 40
 WASHER
NOTE
: If you find part numbers of hardware components in the related kit(s) which
you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,
refer to Standards Manual (SM). The SM will give you the correct part number
to part number relationship.
Kit 576046B02R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
1
 NSA5475-5K7
 20
 NUT
2
 NSA5478VHK5-11
 10
 BOLT
3
 NSA5478VHK5-14
 10
 BOLT
4
 SL4087-05A
 40
 WASHER
NOTE
: If you find part numbers of hardware components in the related kit(s) which
you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,
refer to Standards Manual (SM). The SM will give you the correct part number
to part number relationship.
D. LIST OF MATERIALS - OPERATOR SUPPLIED
(1) Consumable Materials
Consumable CMLB01
ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
Anti Corrosion Primer Epoxy
 04DAB2
 As required
Brushable Fuel Resistant Coating
 06HAA1
 As required
Non Aqueous Cleaner
 08BAA9
 As required
Chemical Conversion Coating
Yellow Aluminum
10ABC1
 As required
(2) Components
None
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 10
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@A300-600
SERVICE BULLETIN
(3) Equipment
None
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
F. TOOLING
(1) Tooling - Price and Availability
(a) Procurement Addresses
Operators in Config. 001 interested in obtaining the FTI tool kits should contact:
Standard tool TOOLB01
 Fatigue Technology Inc
401 Andover Park
East SEATTLE
WA 98188-7605
USA
Internet: www.fatiguetech.com
Phone: (206) 2462010 Fax: (206) 2449886
(b) Price and Availability
Operators in Config. 001 who require kit number FTI-A300-57-6046-1, refer to
Fatigue Technology Inc.
For operators in Config. 001, supply terms for the Start Drill Block part number
CHS371J-10-3-N are to be negotiated with:
AIRBUS
Material, Logistics and Suppliers
Weg beim Jaeger 150
D-22335 HAMBURG
GERMANY
internet: http://spares.airbus.com
fax: +49 40 50 76 2590
E-mail: airbus.kit@airbus.com
(2) Tools
For operators in Config. 001, AIRBUS Spares Support and Services with FTI have
allocated the following tool kit numbers for cold expansion: For the definition of capital,
durable and expendable tools refer to SIL 51-012.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 11
7
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@A300-600
SERVICE BULLETIN
Standard tool TOOLB01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA300576046-1
 Durable Tooling
 1
 (1)
EKA300576046-1
 Expendable Tooling
 1
 (2)
FTIA300576046-1
 Capital Tooling
 1
 (3)
NOTE
 (1)
: Durable tooling: Ref. DK-A300-57-6046-1
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to SIL
51-012.
NOTE
 (2)
: Expendable tooling: Ref. EK-A300-57-6046-1
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
NOTE
 (3)
: Capital tooling: Ref. FTI-A300-57-6046-1
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operator’s stock as a long
term investment or can be loaned from FTI.
(3) Special Tools
None
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 12
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@A300-600
SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS
Task 576046-831-895-001 - MODIFICATION
WARNING
: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
WARNING
: THIS PROCEDURE USES A FUEL SYSTEM ITEM THAT IS IN A CATEGORY
KNOWN AS A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION
(CDCCL) CDCCL IDENTIFIES AN ITEM THAT CAN BE THE SOURCE OF A
POSSIBLE FUEL TANK IGNITION. YOU MUST KEEP ALL CDCCL ITEMS IN
THE APPROVED CONFIGURATION. DAMAGE, WEAR OR CHANGES TO A
CDCCL ITEM CAN CAUSE A POSSIBLE FUEL TANK EXPLOSION.
CAUTION
: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP
ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY
AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE
WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,
COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO
THIS:
- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC. AS
NECESSARY ON WIRING AND COMPONENTS.
- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND
OTHER CONTAMINATION.
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION
AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.
IF THERE IS CONTAMINATION, REFER TO
 ESPM 20-55-00.
NOTE
: The accomplishment instructions of this Service Bulletin include procedures given
in other documents or in other sections of the Service Bulletin. When the words
"refer to" are used and the operator has a procedure accepted by the local
authority he belongs to, the accepted alternative procedure can be used. When the
words "in accordance with" are used then the given procedure must be followed.
NOTE
: The access and close-up instructions, not comprising return to service tests, in this
Service Bulletin do not constitute or affect the technical intent of the Service
Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or
close-up steps to add flexibility to their maintenance operations as long as the
technical intent of the Service Bulletin is met within the set parameters.
NOTE
: Manual titles given in the accomplishment instructions are referred to by acronyms.
Refer to paragraph 1.J., References, for the definition of acronyms.
NOTE
: This Service Bulletin is classified mandatory or expected to be classified mandatory
by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these
accomplishment instructions are Required for Compliance (RC) and must be done
to comply with the AD. Other paragraphs are recommended and may be deviated
from, done as part of other actions or done with accepted methods different from
those given in the Service Bulletin, as long as the RC paragraphs can be done and
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 13
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@A300-600
SERVICE BULLETIN
the aircraft can be put back into a serviceable condition.
Task Associated Data
**CONF 001
Zone
543 550 643 650
Access
Panel
 543DB 550BB 643DB 650BB
Manpower
TOTAL MANHOURS
 63.00
ELAPSED TIME (HOURS)
 28.50
**CONF 002
Zone
543 550 643 650
Access
Panel
 543DB 550BB 643DB 650BB
Manpower
TOTAL MANHOURS
 53.00
ELAPSED TIME (HOURS)
 25.50
**CONF ALL
A. GENERAL
**CONF 001
(1) Subtask 576046-910-401-001 - STANDARD PRACTICES
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 20-21-12, Page Block 001
Consumable Material List (CML)
Process and Material Specification
(PMS)
Structural Repair Manual (SRM)
 51-24-00
51-27-11
51-40-00
51-40-20
51-40-40
51-49-00
51-75-10
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 14
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@A300-600
SERVICE BULLETIN
(a) If you find process and material specifications that you do not know in the design
drawings, refer to the cross-reference list in the Process and Material Specification
(PMS).
(b) For the specification of materials (Mat. No.) given in this Service Bulletin refer to
Consumable Materials List (CML).
(c) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page
Block 001.
(d) Torque tighten fasteners in repair areas in accordance with SRM 51-49-00.
(e) Remove and install fasteners in accordance with SRM 51-40-20.
(f) If the length of any fastener specified in this Service Bulletin does not meet
installation standards given in SRM Chapter 51, then a fastener of the same
specification, or an approved substitute, with a length which meets the installation
standards given in SRM Chapter 51 may be used. In addition, washers may be
installed for fastener grip length in accordance with SRM Chapter 51.
(g) If alternative and substitute fasteners have to be used, you must make sure that the
associated nut/collar are compatible in accordance with SRM 51-40-00 ’Mating Part’
column.
(h) Apply sealant in accordance with SRM 51-24-00.
(i) Cut metallic structures in accordance with SRM 51-27-11.
(j) Renew the protective finish in accordance with SRM 51-75-10.
(k) Obtain fastener hole diameters and drill and ’deburr’ data in accordance with SRM
51-40-40.
(2) Subtask 576046-839-401-001 - ADMINISTRATIVE
Manpower Resources
Skills
 UTILITY
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
**CONF 002
(1) Subtask 576046-910-401-001 - STANDARD PRACTICES
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 20-21-12, Page Block 001
Consumable Material List (CML)
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 15
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@A300-600
SERVICE BULLETIN
References
Process and Material Specification
(PMS)
Structural Repair Manual (SRM)
 51-24-00
51-27-11
51-40-00
51-40-20
51-40-40
51-49-00
51-75-10
(a) If you find process and material specifications that you do not know in the design
drawings, refer to the cross-reference list in the Process and Material Specification
(PMS).
(b) For the specification of materials (Mat. No.) given in this Service Bulletin refer to
Consumable Materials List (CML).
(c) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page
Block 001.
(d) Torque tighten fasteners in repair areas in accordance with SRM 51-49-00.
(e) Remove and install fasteners in accordance with SRM 51-40-20.
(f) If the length of any fastener specified in this Service Bulletin does not meet
installation standards given in SRM Chapter 51, then a fastener of the same
specification, or an approved substitute, with a length which meets the installation
standards given in SRM Chapter 51 may be used. In addition, washers may be
installed for fastener grip length in accordance with SRM Chapter 51.
(g) If alternative and substitute fasteners have to be used, you must make sure that the
associated nut/collar are compatible in accordance with SRM 51-40-00 ’Mating Part’
column.
(h) Apply sealant in accordance with SRM 51-24-00.
(i) Cut metallic structures in accordance with SRM 51-27-11.
(j) Renew the protective finish in accordance with SRM 51-75-10.
(k) Obtain fastener hole diameters and drill and ’deburr’ data in accordance with SRM
51-40-40.
(2) Subtask 576046-839-401-001 - ADMINISTRATIVE
Manpower Resources
Skills
 UTILITY
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 16
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@A300-600
SERVICE BULLETIN
**CONF ALL
B. PREPARATION
**CONF 001
(1) Subtask 576046-941-401-001 - JOB SET-UP
Manpower Resources
Skills
 AIRFRAME
References
Aircraft Maintenance Manual (AMM)
 28-00-00, Page Block 301
28-10-00, Page Block 301
28-11-00, Page Block 101
28-11-22, Page Block 401
28-25-00, Page Block 301
WARNING
: OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A
FUEL TANK. THIS WILL PREVENT INJURY OR DAMAGE, REFER TO
AMM 28-00-00, PAGE BLOCK 301.
NOTE
: The items given in this note shall be considered as the basic Aircraft
configuration before you start a maintenance task:
- Aircraft on the ground resting on landing gear (the ground safety
locks and the wheel chocks are in position on the landing gear)
- Engine shut down, thrust reversers closed and locked
- Aircraft in clean configuration
- Parking brake applied
- Aircraft electrical network de-energized
- Hydraulic system s depressurized
- Access to the cockpit and cabin is available
- All circuit breakers are in closed position
- All controls in NORM, AUTO or OFF position.
(a) Defuel the aircraft, refer to AMM 28-25-00, Page Block 301.
(b) Put the access platform(s) in position.
(c) Remove the manhole covers 543DB (643DB) and 550BB (650BB) from between
Rib 13 and Rib 15, refer to
 AMM 28-11-22, Page Block 401 and AMM 28-11-00,
Page Block 101.
(d) Vent the fuel tanks, refer to
 AMM 28-10-00, Page Block 301.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 17
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@A300-600
SERVICE BULLETIN
**CONF 002
(1) Subtask 576046-941-401-001 - JOB SET-UP
Manpower Resources
Skills
 AIRFRAME
References
Aircraft Maintenance Manual (AMM)
 28-00-00, Page Block 301
28-10-00, Page Block 301
28-11-00, Page Block 101
28-11-22, Page Block 401
28-25-00, Page Block 301
WARNING
: OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A
FUEL TANK. THIS WILL PREVENT INJURY OR DAMAGE, REFER TO
AMM 28-00-00, PAGE BLOCK 301.
NOTE
: The items given in this note shall be considered as the basic Aircraft
configuration before you start a maintenance task:
- Aircraft on the ground resting on landing gear (the ground safety
locks and the wheel chocks are in position on the landing gear)
- Engine shut down, thrust reversers closed and locked
- Aircraft in clean configuration
- Parking brake applied
- Aircraft electrical network de-energized
- Hydraulic system s depressurized
- Access to the cockpit and cabin is available
- All circuit breakers are in closed position
- All controls in NORM, AUTO or OFF position.
(a) Defuel the aircraft, refer to AMM 28-25-00, Page Block 301.
(b) Put the access platform(s) in position.
(c) Remove the manhole covers 543DB (643DB) and 550BB (650BB) from between
Rib 13 and Rib 15, refer to
 AMM 28-11-22, Page Block 401 and AMM 28-11-00,
Page Block 101.
(d) Vent the fuel tanks, refer to
 AMM 28-10-00, Page Block 301.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 18
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@A300-600
SERVICE BULLETIN
**CONF ALL
C. PROCEDURE
NOTE
: The procedures that follow must be accomplished on the LH and RH wings.
**CONF 001
(1) Subtask 576046-831-401-001 - RE-PROFILE THE STRINGER RUN-OUTS
Work Zones and Access Panels
Zone
 Access/Work location
543
 Work location
 from Rib 13 to Rib 14
643
 Work location
 from Rib 13 to Rib 14
550
 Work location
 from Rib 14 to Rib 15
from Stringer 10 to Stringer 12
Stringer 17
650
 Work location
 from Rib 14 to Rib 15
from Stringer 10 to Stringer 12
Stringer 17
Manpower Resources
Manhours
 15.00
Minimum number of person
 2
Subtask elapsed time
 7.50
Skills
 AIRFRAME
Material necessary to do the job
Consumable CMLB01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Anti Corrosion Primer
Epoxy
04DAB2
 As required
Non Aqueous Cleaner
 08BAA9
 As required
Chemical Conversion
Coating Yellow Aluminum
10ABC1
 As required
References
Aircraft Maintenance Manual (AMM)
 20-31-00
Consumable Material List (CML)
Structural Repair Manual (SRM)
 51-23-20
51-27-11
51-35-00
Fig. A-UBAAA
LOCATION AND AREA OF
MODIFICATION
Sheet 01
NOTE
: The procedures that follow must be accomplished on the LH and RH
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 19
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### Page 28

@A300-600
SERVICE BULLETIN
wings.
Refer to Fig. A-UBAAA Sheet 01
(a) Cut the stringers 10, 11, 12 and 17 on bottom skin panel No. 3, adjacent to Rib 14
to the new contour as follows:
1
 Go into the fuel tank. Use a non-metallic or graphite marker and mark out the
new profile to the contour shown on Fig. A-UBAAA Sheet 01
 .
2
 Cut the stringers to the new contour in accordance with SRM 51-27-11, take
care to remove only unwanted material.
3
 Deburr, blend and polish all cut edges.
WARNING
: USE SOLVENTS/CLEANING AG ENTS, SEALANTS AND OTHER
SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR.
4
 Clean the cut surfaces in accordance with SRM 51-35-00 and refer to AMM
20-31-00 with:
Non Aqueous
Cleaner
08BAA9 As required
5
 Apply
Chemical
Conversion Coating
Yellow Aluminum
10ABC1 As required
and
Anti Corrosion
Primer Epoxy
04DAB2 As required
to the cut surfaces in accordance with
 SRM 51-23-20 and Consumable
Material List (CML).
(2) Subtask 576046-831-402-001 - RE-PROFILE THE STRINGER 19 RUN-OUT
Work Zones and Access Panels
Zone
 Access/Work location
543
 Work location
 from Rib 13 to Rib 14
Stringer 19
643
 Work location
 from Rib 13 to Rib 14
Stringer 19
Manpower Resources
Manhours
 2.00
Minimum number of person
 2
Subtask elapsed time
 1.00
Skills
 AIRFRAME
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 20
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@A300-600
SERVICE BULLETIN
Material necessary to do the job
Consumable CMLB01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Anti Corrosion Primer
Epoxy
04DAB2
 As required
Non Aqueous Cleaner
 08BAA9
 As required
Chemical Conversion
Coating Yellow Aluminum
10ABC1
 As required
References
Aircraft Maintenance Manual (AMM)
 20-31-00
Structural Repair Manual (SRM)
 51-23-20
51-27-11
51-35-00
Fig. A-UBCAA
MODIFICATION TO END OF
STRINGER 19
Sheet 01
NOTE
: The worksteps that follow are to be accomplished on both the LH and
RH wings.
(a) Cut the end of stringer 19 on bottom skin panel No. 3, adjacent to Rib 14, to the
new contour as follows:
1
 Go into the fuel tank. Use a non-metallic or graphite marker and mark out the
new profile to the contour shown on Fig. A-UBCAA Sheet 01
 .
2
 Cut the end of stringer 19 to the new contour in accordance with SRM
51-27-11, take care to remove only unwanted material.
3
 Deburr, blend and polish all cut edges.
WARNING
: USE SOLVENTS/CLEANING AG ENTS, SEALANTS AND OTHER
SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR.
4
 Clean the cut surfaces in accordance with SRM 51-35-00 and refer to AMM
20-31-00, with:
Non Aqueous
Cleaner
08BAA9 As required
5
 Apply
Chemical
Conversion Coating
Yellow Aluminum
10ABC1 As required
and
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 21
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@A300-600
SERVICE BULLETIN
Anti Corrosion
Primer Epoxy
04DAB2 As required
to the cut surfaces in accordance with
 SRM 51-23-20 and refer to
 AMM
20-31-00.
(3) Subtask 576046-831-403-001 - REMOVE THE STRINGER END RUN-OUT PLATE ON
STRINGER 19
Work Zones and Access Panels
Zone
 Access/Work location
543
 Work location
 from Rib 13 to Rib 14
Stringer 19
643
 Work location
 from Rib 13 to Rib 14
Stringer 19
Manpower Resources
Manhours
 15.00
Minimum number of person
 2
Subtask elapsed time
 7.50
Skills
 AIRFRAME
Material necessary to do the job
Kit 576046B01R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 NSA5475-6K7
 20
 NUT
2
 NSA5476VHK6-11
 10
 BOLT
3
 NSA5476VHK6-14
 10
 BOLT
4
 NSA5353-06A
 40
 WASHER
Consumable CMLB01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Brushable Fuel Resistant
Coating
06HAA1
 As required
Non Aqueous Cleaner
 08BAA9
 As required
Standard tool TOOLB01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA300576046-1
 Durable Tooling
 1
 (1)
EKA300576046-1
 Expendable Tooling
 1
 (2)
FTIA300576046-1
 Capital Tooling
 1
 (3)
NOTE
 (1)
: Durable tooling: Ref. DK-A300-57-6046-1
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 22
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### Page 31

@A300-600
SERVICE BULLETIN
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to SIL
51-012.
NOTE
 (2)
: Expendable tooling: Ref. EK-A300-57-6046-1
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
NOTE
 (3)
: Capital tooling: Ref. FTI-A300-57-6046-1
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operator’s stock as a long
term investment or can be loaned from FTI.
References
Aircraft Maintenance Manual (AMM)
 20-31-00
Non Destructive Test Manual (NTM)
 51-10-01 Part 6
Structural Repair Manual (SRM)
 51-35-00
51-40-20
51-40-21
51-40-41
51-40-46
51-49-00
51-76-10
51-76-20
Fig. A-UBBAA
STRINGER END RUN-OUT PLATE
REMOVAL
Sheet 01
Fig. A-UBDAA
SPLIT SLEEVE POSITION ON REAR
SPAR
Sheet 01
NOTE
: The worksteps that follow are to be accomplished on both the LH and
RH wings.
Refer to Fig. A-UBBAA Sheet 01
(a) Get these items from KITB01 to modify the LH and RH wings:
20 Nut NSA5475-6K7 Item 1
10 Bolt-Hi Lok NSA5476VHK6-11 Item 2
10 Bolt-Hi Lok NSA5476VHK6-14 Item 3
40 Washer-Special NSA5353-06A Item 4
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 23
7
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@A300-600
SERVICE BULLETIN
(b) Remove the stringer end run-out plate on stringer 19 on bottom skin panel No. 3,
adjacent to Rib 14 as follows:
1
 Go into the fuel tank. Remove the sealant from the ten Nuts, Item (1) in
accordance with
 SRM 51-76-20.
2
 Remove and discard these items in accordance with
 SRM 51-40-20:
10 Nut Item (1)
5 Taperlock Bolt Item (2)
5 Taperlock Bolt Item (3)
1 Stringer End Run-Out
Plate
Item (5)
WARNING
: USE SOLVENTS/CLEANING AG ENTS, SEALANTS AND OTHER
SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR.
3
 Remove all traces of sealant. Use
Non Aqueous
Cleaner
08BAA9 As required
to clean the surfaces of the rear spar and the stringer flange which were
connected to the Stringer End Run-Out Plate, Item (5) in accordance with
SRM 51-76-20, SRM 51-35-00 and refer to
 AMM 20-31-00.
4
 Use procedure C of the Eddy Current Technique, refer to
 NTM 51-10-01 Part
6 to do an inspection of the ten fastener holes. Report any defects to AIRBUS
for repair instructions. Do not continue until repair instructions have been
received.
5
 Install slave bolts in each second hole of the ten fastener holes to hold the
bottom skin to the stringer and the rear spar.
6
 Use the FTI Tools:
FTIA300576046-1 Capital Tooling 1
DKA300576046-1 Durable Tooling 1
EKA300576046-1 Expendable Tooling 1
Drill and ream the holes through the spar to the cold expansion start drill
diameter of 8.789 to 8.864 mm (0.346 to 0.349 in.). Use the tools given as
follows:
Tool Name
 Tool Part No.
Start Drill Block
 CHS371J-10-3-N
Start Reamer
 CXSR-.3460/.3260-1
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 24
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@A300-600
SERVICE BULLETIN
Tool Name
 Tool Part No.
Start Drill
 CBSD-10-3-N-1
7
 Examine the reamed start holes through the rear spar. Use the combination
plug gage, Part No. CXG-.3460/.3490/.3500.
NOTE
: If a hole is found oversize or oval, report the defect to
AIRBUS.
8
 Drill and ream the holes through the stringer 19 to the cold expansion start
size diameter of 8.738 to 8.813 mm (0.344 to 0.347 in.).
Use the tools given as follows:
Tool Name
 Tool Part No.
Start Drill Block
 CHS371J-10-3-N
Start Reamer
 CBSR-10-3-N-1
Start Drill
 CBSD-10-3-N-1
9
 Examine the reamed start holes through stringer 19. Use the combination plug
gage, Part No. CBG-10-3-N-1.
NOTE
: If a hole is found oversize or oval, report the defect to
AIRBUS.
10
 Cold expand and final ream the holes, refer to
 Fig. A-UBDAA Sheet 01
 and in
accordance with
 SRM 51-40-41 use the tools given as follows:
Tool Name
 Tool Part No.
Split Sleeve
 CBS-10-3-N-23F
Mandrel
 CBM-10-3-N-1-40-V1
Nose Cap
 CBCE-14B-1023F
Mandrel Checking Fixture
 CBMG-10-3-N
Finish Reamer
 CBR-10-3-N-1-.3695
11
 Countersink the holes to 100 degrees for the new Bolts, Items 2 and 3 in
accordance with
 SRM 51-40-46.
12
 Deburr the edges of the holes.
13
 Apply
Brushable Fuel
Resistant Coating
06HAA1 As required
under the head of the new Bolts, Items 2 and 3, refer to
 AMM 20-31-00.
14
 On each wing, assemble in each of the non-slave bolted holes the interference
fit
2 Bolt-Hi Lok NSA5476VHK6-11 Item 2
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 25
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@A300-600
SERVICE BULLETIN
and
3 Bolt-Hi Lok NSA5476VHK6-14 Item 3
and the
5 Nut NSA5475-6K7 Item 1
with a maximum quantity of
2 Washer-Special NSA5353-06A Item 4
for each of the Bolts, Items 2 and 3.
a
 Torque tighten the Nuts, Item 1 to between 2.373 and 2.599 m.daN (210
and 230 lbf.in.) in accordance with
 SRM 51-40-21 and SRM 51-49-00.
15
 Remove the five slave bolts.
16
 Do worksteps 6_ thru 13_ for the holes that remain.
17
 On each wing, for the five holes that remain, assemble the interference fit
3 Bolt-Hi Lok NSA5476VHK6-11 Item 2
and
2 Bolt-Hi Lok NSA5476VHK6-14 Item 3
and the
5 Nut NSA5475-6K7 Item 1
with a maximum quantity of
2 Washer-Special NSA5353-06A Item 4
for each of the Bolts, Items 2 and 3.
a
 Torque tighten the Nuts, Item 1 to between 2.373 and 2.599 m.daN (210
and 230 lbf.in.) in accordance with
 SRM 51-40-21 and SRM 51-49-00.
(4) Subtask 576046-750- 401-001 - DETAILED VISUAL AND HFEC INSPECTION
Work Zones and Access Panels
Zone
 Access/Work location
550
 Work location
 from Rib 14 to Rib 15
from Stringer 10 to Stringer 12
Stringer 17
650
 Work location
 from Rib 14 to Rib 15
from Stringer 10 to Stringer 12
Stringer 17
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 26
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@A300-600
SERVICE BULLETIN
Manpower Resources
Manhours
 3.00
Minimum number of person
 2
Subtask elapsed time
 1.50
Skills
 NON DESTRUCTIVE
TESTING
References
Non Destructive Test Manual (NTM)
 57-21-64
NOTE
: The worksteps that follow are to be accomplished on both the LH and
RH wings.
(a) Make sure that the inspection area is sufficiently clean to do an eddy current
inspection.
(b) Do a detailed visual and a HFEC inspection of the stringer run-outs at stringers 10,
11, 12 and 17 in accordance with
 NTM 57-21-64.
(c) If there are signs of cracks or damage at stringers 10, 11, 12 or 17, contact
AIRBUS.
(d) Use the results from the eddy current inspection to complete the Inspection Report
Form to identify areas of st ringer damage (cra cks), refer to
 APPENDIX 01:
INSPECTION REPORT FORM .
**CONF 002
(1) Subtask 576046-831-401-001 - RE-PROFILE THE STRINGER RUN-OUTS
Work Zones and Access Panels
Zone
 Access/Work location
543
 Work location
 from Rib 13 to Rib 14
643
 Work location
 from Rib 13 to Rib 14
550
 Work location
 from Rib 14 to Rib 15
from Stringer 10 to Stringer 12
Stringer 17
650
 Work location
 from Rib 14 to Rib 15
from Stringer 10 to Stringer 12
Stringer 17
Manpower Resources
Manhours
 15.00
Minimum number of person
 2
Subtask elapsed time
 7.50
Skills
 AIRFRAME
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 27
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@A300-600
SERVICE BULLETIN
Material necessary to do the job
Consumable CMLB01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Anti Corrosion Primer
Epoxy
04DAB2
 As required
Non Aqueous Cleaner
 08BAA9
 As required
Chemical Conversion
Coating Yellow Aluminum
10ABC1
 As required
References
Aircraft Maintenance Manual (AMM)
 20-31-00
Consumable Material List (CML)
Structural Repair Manual (SRM)
 51-23-20
51-27-11
51-35-00
Fig. A-UBAAA
LOCATION AND AREA OF
MODIFICATION
Sheet 01
NOTE
: The procedures that follow must be accomplished on the LH and RH
wings.
Refer to Fig. A-UBAAA Sheet 01
(a) Cut the stringers 10, 11, 12 and 17 on bottom skin panel No. 3, adjacent to Rib 14
to the new contour as follows:
1
 Go into the fuel tank. Use a non-metallic or graphite marker and mark out the
new profile to the contour shown on Fig. A-UBAAA Sheet 01
 .
2
 Cut the stringers to the new contour in accordance with SRM 51-27-11, take
care to remove only unwanted material.
3
 Deburr, blend and polish all cut edges.
WARNING
: USE SOLVENTS/CLEANING AG ENTS, SEALANTS AND OTHER
SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR.
4
 Clean the cut surfaces in accordance with SRM 51-35-00 and refer to AMM
20-31-00 with:
Non Aqueous
Cleaner
08BAA9 As required
5
 Apply
Chemical
Conversion Coating
Yellow Aluminum
10ABC1 As required
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 28
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### Page 37

@A300-600
SERVICE BULLETIN
and
Anti Corrosion
Primer Epoxy
04DAB2 As required
to the cut surfaces in accordance with
 SRM 51-23-20 and Consumable
Material List (CML).
(2) Subtask 576046-831-402-001 - RE-PROFILE THE STRINGER 19 RUN-OUT
Work Zones and Access Panels
Zone
 Access/Work location
543
 Work location
 from Rib 13 to Rib 14
Stringer 19
643
 Work location
 from Rib 13 to Rib 14
Stringer 19
Manpower Resources
Manhours
 2.00
Minimum number of person
 2
Subtask elapsed time
 1.00
Skills
 AIRFRAME
Material necessary to do the job
Consumable CMLB01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Anti Corrosion Primer
Epoxy
04DAB2
 As required
Non Aqueous Cleaner
 08BAA9
 As required
Chemical Conversion
Coating Yellow Aluminum
10ABC1
 As required
References
Aircraft Maintenance Manual (AMM)
 20-31-00
Structural Repair Manual (SRM)
 51-23-20
51-27-11
51-35-00
Fig. A-UBCAA
MODIFICATION TO END OF
STRINGER 19
Sheet 01
NOTE
: The worksteps that follow are to be accomplished on both the LH and
RH wings.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 29
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@A300-600
SERVICE BULLETIN
(a) Cut the end of stringer 19 on bottom skin panel No. 3, adjacent to Rib 14, to the
new contour as follows:
1
 Go into the fuel tank. Use a non-metallic or graphite marker and mark out the
new profile to the contour shown on Fig. A-UBCAA Sheet 01
 .
2
 Cut the end of stringer 19 to the new contour in accordance with SRM
51-27-11, take care to remove only unwanted material.
3
 Deburr, blend and polish all cut edges.
WARNING
: USE SOLVENTS/CLEANING AG ENTS, SEALANTS AND OTHER
SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR.
4
 Clean the cut surfaces in accordance with SRM 51-35-00 and refer to AMM
20-31-00, with:
Non Aqueous
Cleaner
08BAA9 As required
5
 Apply
Chemical
Conversion Coating
Yellow Aluminum
10ABC1 As required
and
Anti Corrosion
Primer Epoxy
04DAB2 As required
to the cut surfaces in accordance with
 SRM 51-23-20 and refer to
 AMM
20-31-00.
(3) Subtask 576046-831-403-002 - REMOVE THE STRINGER END RUN-OUT PLATE ON
STRINGER 19
Work Zones and Access Panels
Zone
 Access/Work location
543
 Work location
 from Rib 13 to Rib 14
Stringer 19
643
 Work location
 from Rib 13 to Rib 14
Stringer 19
Manpower Resources
Manhours
 5.00
Minimum number of person
 2
Subtask elapsed time
 2.50
Skills
 AIRFRAME
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 30
7
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@A300-600
SERVICE BULLETIN
Material necessary to do the job
Kit 576046B02R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 NSA5475-5K7
 20
 NUT
2
 NSA5478VHK5-11
 10
 BOLT
3
 NSA5478VHK5-14
 10
 BOLT
4
 SL4087-05A
 40
 WASHER
Consumable CMLB01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Brushable Fuel Resistant
Coating
06HAA1
 As required
Non Aqueous Cleaner
 08BAA9
 As required
References
Aircraft Maintenance Manual (AMM)
 20-31-00
Non Destructive Test Manual (NTM)
 51-10-01 Part 6
Structural Repair Manual (SRM)
 51-35-00
51-40-20
51-40-21
51-40-41
51-40-44
51-40-46
51-49-00
51-76-10
51-76-20
Fig. A-UBBAA
STRINGER END RUN-OUT PLATE
REMOVAL
Sheet 01
NOTE
: The worksteps that follow are to be accomplished on both the LH and
RH wings.
Refer to Fig. A-UBBAA Sheet 01
(a) Get these items from KITB02 to modify the LH and RH wings:
20 Nut NSA5475-5K7 Item 1
10 Bolt-Hi Lok NSA5478VHK5-11 Item 2
10 Bolt-Hi Lok NSA5478VHK5-14 Item 3
40 Washer SL4087-05A Item 4
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 31
7
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### Page 40

@A300-600
SERVICE BULLETIN
(b) Remove the stringer end run-out plate on stringer 19 on bottom skin panel No. 3,
adjacent to Rib 14 as follows:
1
 Go into the fuel tank. Remove the sealant from the ten Nuts, Item (1) in
accordance with
 SRM 51-76-20.
2
 Remove and discard these items in accordance with
 SRM 51-40-20:
10 Nut Item (1)
5 Interference Fit Bolt Item (2)
5 Interference Fit Bolt Item (3)
1 Stringer End Run-Out
Plate
Item (5)
WARNING
: USE SOLVENTS/CLEANING AG ENTS, SEALANTS AND OTHER
SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR.
3
 Remove all traces of sealant. Use
Non Aqueous
Cleaner
08BAA9 As required
to clean the surfaces of the rear spar and the stringer flange which were
connected to the Stringer End Run-Out Plate, Item (5) in accordance with
SRM 51-76-20, SRM 51-35-00 and refer to
 AMM 20-31-00.
4
 Use procedure B of the Eddy Current Technique, refer to
 NTM 51-10-01 Part
6 to do an inspection of the ten fastener holes. Report any defects to AIRBUS
for repair instructions. Do not continue until repair instructions have been
received.
5
 Drill and ream the holes through the stringer 19 to between 8.738 to
8.813 mm (0.344 to 0.347 in.) for second oversize interference fit bolts in
accordance with
 SRM 51-40-44.
6
 Deburr the edges of the holes.
7
 Apply
Brushable Fuel
Resistant Coating
06HAA1 As required
under the head of the new Bolts, Items 2 and 3, refer to
 AMM 20-31-00.
8
 On each wing, install second oversize interference fit
5 Bolt-Hi Lok NSA5478VHK5-11 Item 2
and
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 32
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### Page 41

@A300-600
SERVICE BULLETIN
5 Bolt-Hi Lok NSA5478VHK5-14 Item 3
and the
10 Nut NSA5475-5K7 Item 1
with a maximum quantity of
2 Washer SL4087-05A Item 4
for each of the Bolts, Items 2 and 3.
a
 Torque tighten the Nuts, Item 1 to between 1.413 and 1.525 m.daN (125
and 135 lbf.in.) in accordance with
 SRM 51-40-20 and SRM 51-49-00.
(4) Subtask 576046-750- 401-001 - DETAILED VISUAL AND HFEC INSPECTION
Work Zones and Access Panels
Zone
 Access/Work location
550
 Work location
 from Rib 14 to Rib 15
from Stringer 10 to Stringer 12
Stringer 17
650
 Work location
 from Rib 14 to Rib 15
from Stringer 10 to Stringer 12
Stringer 17
Manpower Resources
Manhours
 3.00
Minimum number of person
 2
Subtask elapsed time
 1.50
Skills
 NON DESTRUCTIVE
TESTING
References
Non Destructive Test Manual (NTM)
 57-21-64
NOTE
: The worksteps that follow are to be accomplished on both the LH and
RH wings.
(a) Make sure that the inspection area is sufficiently clean to do an eddy current
inspection.
(b) Do a detailed visual and a HFEC inspection of the stringer run-outs at stringers 10,
11, 12 and 17 in accordance with
 NTM 57-21-64.
(c) If there are signs of cracks or damage at stringers 10, 11, 12 or 17, contact
AIRBUS.
(d) Use the results from the eddy current inspection to complete the Inspection Report
Form to identify areas of st ringer damage (cra cks), refer to
 APPENDIX 01:
INSPECTION REPORT FORM .
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 33
7
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### Page 42

@A300-600
SERVICE BULLETIN
**CONF ALL
D. TEST
**CONF 001
None
**CONF 002
None
**CONF ALL
E. CLOSE-UP
**CONF 001
(1) Subtask 576046-914-401-001 - APPLY SEALANTS
Work Zones and Access Panels
Zone
 Access/Work location
550
 Work location
 from Rib 14 to Rib 15
from Stringer 10 to Stringer 12
Stringer 17
Stringer 19
650
 Work location
 from Rib 14 to Rib 15
from Stringer 10 to Stringer 12
Stringer 17
Stringer 19
Manpower Resources
Skills
 AIRFRAME
Material necessary to do the job
Consumable CMLB01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Brushable Fuel Resistant
Coating
06HAA1
 As required
References
Aircraft Maintenance Manual (AMM)
 20-31-00
Structural Repair Manual (SRM)
 51-76-10
51-76-20
NOTE
: The worksteps that follow are to be accomplished on both the LH and
RH wings.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 34
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### Page 43

@A300-600
SERVICE BULLETIN
(a) Apply, refer to AMM 20-31-00:
Brushable Fuel
Resistant Coating
06HAA1 As required
as a bead along the stringer flange edges and also to fully cover all the Nuts, Item
1 and the Special Washers, Item 4 in accordance with
 SRM 51-76-20.
(b) Allow the sealant to cure in accordance with
 SRM 51-76-10.
(2) Subtask 576046-942-401-001 - CLOSE-UP
Work Zones and Access Panels
Zone
 Access/Work location
543
 Access
 Panel 543DB
643
 Access
 Panel 643DB
550
 Access
 Panel 550BB
650
 Access
 Panel 650BB
Manpower Resources
Skills
 AIRFRAME
References
Aircraft Maintenance Manual (AMM)
 28-11-00, Page Block 101
28-11-00, Page Block 501
28-11-22, Page Block 401
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(b) Install the access panels 543DB (643DB) and 550BB (650BB) between
 Rib 13 and
Rib 15, refer to
 AMM 28-11-22, Page Block 401 and AMM 28-11-00, Page Block
101.
(c) Remove the access platform(s).
(d) Refuel the aircraft and inspect for leaks, refer to
 AMM 28-11-00, Page Block 501.
(e) Put the aircraft back to its initial configuration.
**CONF 002
(1) Subtask 576046-914-401-001 - APPLY SEALANTS
Work Zones and Access Panels
Zone
 Access/Work location
550
 Work location
 from Rib 14 to Rib 15
from Stringer 10 to Stringer 12
Stringer 17
Stringer 19
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 35
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### Page 44

@A300-600
SERVICE BULLETIN
650
 Work location
 from Rib 14 to Rib 15
from Stringer 10 to Stringer 12
Stringer 17
Stringer 19
Manpower Resources
Skills
 AIRFRAME
Material necessary to do the job
Consumable CMLB01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Brushable Fuel Resistant
Coating
06HAA1
 As required
References
Aircraft Maintenance Manual (AMM)
 20-31-00
Structural Repair Manual (SRM)
 51-76-10
51-76-20
NOTE
: The worksteps that follow are to be accomplished on both the LH and
RH wings.
(a) Apply, refer to AMM 20-31-00:
Brushable Fuel
Resistant Coating
06HAA1 As required
as a bead along the stringer flange edges and also to fully cover all the Nuts, Item
1 and the Special Washers, Item 4 in accordance with
 SRM 51-76-20.
(b) Allow the sealant to cure in accordance with
 SRM 51-76-10.
(2) Subtask 576046-942-401-001 - CLOSE-UP
Work Zones and Access Panels
Zone
 Access/Work location
543
 Access
 Panel 543DB
643
 Access
 Panel 643DB
550
 Access
 Panel 550BB
650
 Access
 Panel 650BB
Manpower Resources
Skills
 AIRFRAME
References
Aircraft Maintenance Manual (AMM)
 28-11-00, Page Block 101
28-11-00, Page Block 501
28-11-22, Page Block 401
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 36
7
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### Page 45

@A300-600
SERVICE BULLETIN
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(b) Install the access panels 543DB (643DB) and 550BB (650BB) between
 Rib 13 and
Rib 15, refer to
 AMM 28-11-22, Page Block 401 and AMM 28-11-00, Page Block
101.
(c) Remove the access platform(s).
(d) Refuel the aircraft and inspect for leaks, refer to
 AMM 28-11-00, Page Block 501.
(e) Put the aircraft back to its initial configuration.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 37
7
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### Page 46

@A300-600
SERVICE BULLETIN
**CONF ALL
F
W
D
INBD
REAR SPAR
DATUM
FRONT SPAR
DATUM
LH WING SHOWN
RH WING SIMILAR
PLAN VIEW LH WING
BOTTOM SKIN PANEL No. 3
STGR8
STGR10
STGR11
STGR12
STGR13
STGR16
STGR17
STGR19
RIB12
RIB9
RIB10
RIB11
RIB13
RIB14
RIB15
CONTOUR BEFORE
MODIFICATION
31.50 mm
(1.24 in)
CONTOUR BEFORE
MODIFICATION
RIB14 DATUM
A
EXAMPLE FOR ALL
AFFECTED STRINGERS
31.50 mm
(1.24 in)
CONTOUR AFTER
MODIFICATION
CONTOUR AFTER
MODIFICATION
25°25°
R 50.80 mm
(2.00 in)
R 50.80 mm
(2.00 in)
STRINGER 13 AND 16
NOT AFFECTED STRINGER
RUN−OUTS
A
D_SB_576046_7_BAAA_01_00
Figure A-UBAAA - Sheet 01
LOCATION AND AREA OF MODIFICATION
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 38
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 47

@A300-600
SERVICE BULLETIN
**CONF ALL
INBD
A
STRINGER END
RUN−OUT PLATE
A
PLAN VIEW LH WING
BOTTOM SKIN PANEL No. 3
F
W
D
INBD
REAR SPAR
DATUM
FRONT SPAR
DATUM
LH WING SHOWN
RH WING SIMILAR
STGR8
STGR10
STGR11
STGR12
STGR13
STGR16
STGR17
STGR19
RIB12
RIB9
RIB10
RIB11
RIB13
RIB14
RIB15
REAR SPAR
DATUM
RIB14
STGR19 DATUM
DATUM
(1) 1
(2) 2
4
(1) 1
(3) 3
4
(5)
D_SB_576046_7_BBAA_01_00
Figure A-UBBAA - Sheet 01
STRINGER END RUN-OUT PLATE REMOVAL
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 39
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 48

@A300-600
SERVICE BULLETIN
**CONF ALL
PLAN VIEW LH WING
BOTTOM SKIN PANEL No. 3
RIB13
RIB14
RIB15
A
CONTOUR BEFORE
MODIFICATION
CONTOUR AFTER
MODIFICATION
30°
R 76.20 mm
(3.00 in)
R 15.20 mm
(0.60 in)
30.50 mm
(1.20 in)
STGR19
FRONT SPAR
DATUM
REAR SPAR
DATUM A
STGR10
STGR11
STGR12
STGR13
STGR16
STGR17
STGR19
F
W
D
INBD
LH WING SHOWN
RH WING SIMILAR
D_SB_576046_7_BCAA_01_00
Figure A-UBCAA - Sheet 01
MODIFICATION TO END OF STRINGER 19
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 40
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 49

@A300-600
SERVICE BULLETIN
**CONF 001
OR OUTBOARD PERMITTED.
SPAR DATUM
PLAN VIEW
SPLIT SLEEVE POSITION ± 10°
SPLIT SLEEVE ON INBOARD
IN RELATION TO SPAR DATUM.
D_SB_576046_7_BDAA_01_00
Figure A-UBDAA - Sheet 01
SPLIT SLEEVE POSITION ON REAR SPAR
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 41
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 50

@A300-600
SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 42
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 51

@A300-600
SERVICE BULLETIN
APPENDIX 01: INSPECTION REPORT FORM
**CONF ALL
Record the location of cracks on the Inspection Report Form shown below:
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 1
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 52

@A300-600
SERVICE BULLETIN
APPENDIX 01: INSPECTION REPORT FORM
**CONF ALL
INSPECTION REPORT
SERVICE BULLETIN NO:
FINDINGS:
RETURN TO:
AIRBUS
FAX +33 (0)5 61 93 36 14
A300−57−6046
LOCATION OF FINDINGS
STRINGER 10
MSN:AIRCRAFT
FLIGHT CYCLES:
FLIGHT HOURS:
CUSTOMER SERVICE ENGINEERING − SEES2
1 ROND POINT MAURICE BELLONTE
31707 BLAGNAC CEDEX
FRANCE
YES NO
Structure.sbinspectionresult@airbus.com
DATE OF INSPECTION:
INSPECTION METHOD:
HIGH FREQUENCY
EDDY CURRENT
STRINGER 11
STRINGER 12
STRINGER 17
CRACKS FOUND
YES: PROVIDE DETAILS BELOW NO
D_SB_576046_7_RAAA_01_00
Figure A-URAAA - Sheet 01
APPENDIX 01: INSPECTION REPORT FORM
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 2
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 53

@A300-600
SERVICE BULLETIN
REPORTING SHEET
TITLE: WINGS - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB14
MODIFICATION No.: 10326H5339
Please complete the appropriate item (A or B):
A - SB WILL BE
 embodied YES/NO (if NO please comment)
If YES, aircraft concer ned (as per SB effectivity by default) and planned dates (month/year) of
embodiment:
B - SB HAS BEEN
 embodied on aircraft:
Operator comments:
From Airline:
Name/Title:
Signature: Date:
If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to
next normal revision or prior to SB embodiment, please indicate required service(s):
Either: Modification Operational Impact (MOI), if available YES/NO
Or : Intermediate revision YES/NO
Important Information:
 This SB will only be incorporated in your maintenance and operational
documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With
the next feasible revision, this will result in
- Updating of maintenance documentation to show pre and post SB data.
- Updating of maintenance and operational documentation to show post SB data after embodiment.
If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically
include them in the manual revisions. Refer to SIL 00-037 for detailed information.
Please return this completed sheet to:
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX FRANCE
Attn: SDC32 Technical Data and Documentation Services
F A X :( + 3 3 )56 19 32 80 6
e-mail: sb.reporting@airbus.com
or via your Resident Customer Support Office.
Alternatively, SB lists via letters or fax are also accepted.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 1
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 54

@A300-600
SERVICE BULLETIN
QUALITY PERCEPTION FORM
Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data
that you provide us will be used to analyse areas of difficulties and to take corrective action to further
improve the quality of our Service Bulletins.
We thank you for the time you have taken in completing this form.
(Please rate on a scale of 1 to 4, with 4 being the highest score)
- Quality rating of this SB 4321
- Quality rating of the Accomplishment Instructions 4321
- Quality rating of the Illustrations 4321
- Is this SB easy to understand ? Y/N
If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a
short description of the issue.
Planning Material Instructions
X Effectivity X Kit content X Preparation
X Reason X List of Materials Operator Supplied X Mod/Inspection
X Manpower X Industry support X Test
X References X Re-identification X Close-Up
X Publication X Tooling X Illustrations
Comments:
Operator: Date:
Name/Title:
Please return this form to:
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX FRANCE
Attn : SEM4 Service Bulletins Management
F A X:( 3 3 )56 19 34 25 1
Or via your Resident Customer Support Office.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046
REVISION No.: 03 - Feb 04/15 Page: 1
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

---
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