# Airbus Service Bulletin A300-57-6086

## Copies (2)

Copies the FAA filed in AD dockets on regulations.gov, newest revision first. A newer revision may exist.

- Revision 7 ("A300-57-6086 R7"), 92 pages: PDF https://openairdocs.org/files/sha256/dd/9c/dd9c62f66bca0b40eb764d88fad0e2a958b014c1ad41c0ed159bbaac2026d2a7; text https://openairdocs.org/service-documents/airbus/a300-57-6086/file/dd9c62f66bca.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2018-0497; AD 2018-19-18 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Revision 05 ("U.S. DOT/FAA - Service Bulletin A300-57-6086 Revision 05"), 100 pages: PDF https://openairdocs.org/files/sha256/30/c4/30c4ab6e4276b451f60fb5769e5b5fe67542bd87acdbc34cf3954446b60d51fd; text https://openairdocs.org/service-documents/airbus/a300-57-6086/file/30c4ab6e4276.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2013-1064; AD 2014-20-18 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: A300-57-6086
- Latest revision known: A300-57-6086, Revision 7, dated March 26, 2018 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a300-57-6086

## ADs that cite it (4) (OpenAirDocs)

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

- [AD 2019-12-04](https://openairdocs.org/ad/2019-12-04.md), effective Aug 7, 2019: Revisions 6 and 7
- [AD 2018-19-18](https://openairdocs.org/ad/2018-19-18.md), effective Nov 7, 2018: Revisions 6 and 7
- [AD 2014-20-18](https://openairdocs.org/ad/2014-20-18.md), effective Dec 11, 2014: Revisions 01 and 05
- [AD 2005-23-08](https://openairdocs.org/ad/2005-23-08.md), effective Dec 19, 2005: Revision 01

Also cited in [4 proposed ADs](https://openairdocs.org/service-documents/airbus/a300-57-6086/proposed.md), [7 difficulty reports](https://openairdocs.org/service-documents/airbus/a300-57-6086/reports.md).

## Text (92 pages)

Revision 7, the newest copy. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2018-0497; AD 2018-19-18 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 - CENTER WING BOX - INSPECTION OF HORIZONTAL
SPLICING BETWEEN REAR SPAR AND BOTTOM PANEL AT
JUNCTION WITH FUSELAGE AT FR47
MODIFICATION No.: None
This page transmits Revision No.07 of Service Bulletin No.A300-57-6086
ADDITIONAL WORK
**CONF ALL
No additional work is required by this revision for aircraft inspected by any previous issue.
REASON
Revision No. 07 issued to add an inspection report dedicated to ultrasonic inspections.
CHANGES
The main changes of this revision are:
- Effectivity updated
- Inspection report dedicated to ultrasonic inspections added
- Compliance table modified
- Flowchart modified
- Fig. A-FCAAA modified to add one hole to be inspected (hole type 1)
- Minor changes applied.
PLANNING INFORMATION
EFFECTIVITY
 EFFECTIVITY RELATED INFORMATION
UPDATED
R
Configuration definition
CONF 002
 CONFIGURATION DEFINITION UPDATED
 R
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 2

@A300-600
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
COMPLIANCE
Accomplishment Timescale
 ACCOMPLISHMENT TIMESCALE UPDATED
 R
MATERIAL INFORMATION
MATERIAL - PRICE AND AVAILABILITY
Price and Availability
 PRICE AND AVAILABILITY UPDATED
 R
INDUSTRY SUPPORT INFORMATION
 INDUSTRY SUPPORT INFORMATION UPDATED
 R
ACCOMPLISHMENT INSTRUCTIONS
TASK 576086- 832-801-001-Inspection
 TASK SOLUTION UPDATED
NOTE UPDATED
R
Subtask 576086-910-001-002
 SUBTASK SOLUTION UPDATED
 R
Subtask 576086-910-001-002
 SUBTASK SOLUTION UPDATED
 R
Subtask 576086-941-001-002
 SUBTASK SOLUTION UPDATED
NOTE UPDATED
R
Subtask 576086-941-001-002
 SUBTASK SOLUTION UPDATED
NOTE UPDATED
R
Subtask 576086-832-004-001
 SUBTASK SOLUTION UPDATED
 R
Subtask 576086-832-005-001
 SUBTASK SOLUTION UPDATED
 R
Subtask 576086-832-006-001
 SUBTASK SOLUTION UPDATED
 R
Subtask 576086-832-007-001
 SUBTASK SOLUTION UPDATED
 R
Subtask 576086-832-008-001
 SUBTASK SOLUTION UPDATED
 R
Subtask 576086-832-009-001
 SUBTASK SOLUTION UPDATED
 R
Subtask 576086-832-004-002
 SUBTASK SOLUTION UPDATED
 R
Subtask 576086-832-005-002
 SUBTASK SOLUTION UPDATED
 R
Subtask 576086-832-006-002
 SUBTASK SOLUTION UPDATED
 R
Subtask 576086-832-007-002
 SUBTASK SOLUTION UPDATED
 R
Subtask 576086-832-008-002
 SUBTASK SOLUTION UPDATED
 R
Subtask 576086-832-009-002
 SUBTASK SOLUTION UPDATED
 R
Fig. A-FFBAB
Fig. A-FFBAB Sheet 01
 SHEET UPDATED
 R
Fig. A-FBAAA
Fig. A-FBAAA Sheet 02
 SHEET UPDATED
 R
Fig. A-FCAAA
Fig. A-FCAAA Sheet 01
 SHEET UPDATED
 R
Appendix 01 - Inspection Report
Fig. A-FAHAA
 FIGURE SOLUTION ADDED
 N
Fig. A-FAHAA Sheet 01
 SHEET ADDED
 N
Fig. A-FAHAA Sheet 02
 SHEET ADDED
 N
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.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 3

@A300-600
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
HISTORY OF PREVIOUS REVISIONS
Revision No. 01 issued to update the PNs of the fasteners and add Kit A02. Also, this revision is issued
to inform the operators that this Service Bulletin is rendered mandatory by Airworthiness Directive No.
2000-533-328(B).
Revision No. 02 issued to delete the Airworthiness Directive (AD) No. the synoptic chart and the
effectivity and add a NOTE which specifies that this inspection is no longer necessary if Service Bulletin
No. A300-57-6069 is accomplished.
Revision No. 03 issued to modify figure 2 sheet 3 : the values in the table must be in accordance with
SRM 51-40-00.
Revision No. 04 issued to .
modify the threshold and interval of the inspection
add an Ultra Sonic inspection of the CWB lower panel
add an instruction for the installation of removed fasteners in transition fit instead of interference.
Revision No. 05 issued to:
add a note concerning the threshold of the inspection
modify the Figure A-FFBAA sheet 01
Revision No. 06 issued to update accomplishment timescale and to add Service Bulletin No.
A300-57-6113 as terminating action of inspection Service Bulletin No. A300-57-6086.
REVISION SEQUENCE
ORIGINAL: Jun 06/00
REVISION No.: 01 - Apr 02/02
REVISION No.: 02 - Dec 22/06
REVISION No.: 03 - Sep 24/07
REVISION No. : 04 - Oct 17/11
REVISION No. : 05 - Jan 30/12
REVISION No. : 06 - Jul 04/17
REVISION No. : 07 - Mar 26/18
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 3
5
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: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 4
5
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 - CENTER WING BOX - INSPECTION OF HORIZONTAL
SPLICING BETWEEN REAR SPAR AND BOTTOM PANEL AT
JUNCTION WITH FUSELAGE AT FR47
**CONF ALL
MODIFICATIONS
None
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
During accomplishment of Structure Significant Item (SSI) Inspection 571011 and Modification as per
the Service Bulletin No. A300-57-6050, cracks have been found on the horizontal flange of the Frame
47 internal corner angle fitting, on three aircraft. At the time of the findings, the aircraft were below the
SSI inspection threshold of 18,000 FC.
This Service Bulletin calls for a rotating probe inspection of twenty holes in the horizontal flange of the
Frame 47 internal corner angle fitting and for an Ultra Sonic inspection of seventy holes of the CWB
lower panel.
The procedure as described in this Service Bulletin is to be performed if no Airbus repair and/or repair
improvement has been previously performed in the same area. In case of repairs performed previously,
please contact AIRBUS Repair Support department for further instructions.
If undetected, cracks can increase in magnitude, leading to a reduction of the residual strength of the
structure. Thus, accomplishment of this Service Bulletin will avoid extensive structural repairs.
Accomplishment of Service Bulletfin No. A300-57-6113 cancels the requirement of inspection defined in
this Service Bulletin.
The Operational/Maintenance Consequences of this Service Bulletin are covered by the update of the
affected publications detailed in ’PLANNING INFORMATION’.
This Service Bulletin supersedes Maintenance Planning Document (MPD) task 571011-01-1, SSI task
571011.
NOTE
: Service Bulletin No. A300-57-6050 has been embodied in all in-service aircraft included
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 6

@A300-600
SERVICE BULLETIN
SUMMARY
in its effectivity, mandated at 15100 Flight C ycles (FC) or 38900 Flight Hours (FH) since
first flight, whichever occurs first.
GENERAL EVALUATION
EVALUATION TABLE
COMPLIANCE
 MANDATORY (1)
 CANCELS INSPECTION SB
 NO
POTENTIAL AD
 YES
 A/C OPERATION AFFECTED
 NO
RELIABILITY AFFECTED
 NO
 PAX COMFORT AFFECTED
 NO
COST SAVING
 NO
 ETOPS AFFECTED
 NO
STRUCTURAL LIFE EXTN
 NO
 VENDOR SB INVOLVED
 NO
DE-FUELLING
 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 576086A01R05
 1
 41,310.00
 Bolt, Nut, Washer
**CONF 002
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 576086A02R02
 1
 14,130.00
 Bolt, Nut, Washer.
EFFECTIVITY
**CONF ALL
This Service Bulletin is applicable to this (these) operator(s) :
14S AAW ABR AHK BCS EFX FDX IRA IRM KAC MNB MRJ MSR
QSM SOP SUD TAR THA TNO URS UTP
CONCURRENT REQUIREMENTS
None
REFERENCES / REPERCUSSIONS
TFU
 57.10.00.007
OEB
 None
AOT
 None
SIL
 None
ISI
 00.00.00179
00.00.00198
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 7

@A300-600
SERVICE BULLETIN
SUMMARY
LINE MAINTENANCE AFFECTED
 No
LIFE LIMIT
 None
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
HARD
 NO
SOFT
 NO
OBRM
 NO
MANPOWER
**CONF 001
Task 576086-832-801-001: Inspection
TOTAL MANHOURS
 35.00
ELAPSED TIME (HOURS)
 28.50
**CONF 002
Task 576086-832-801-001: Inspection
TOTAL MANHOURS
 35.00
ELAPSED TIME (HOURS)
 28.50
APPENDICES
**CONF ALL
Appendix 01 - Inspection Report
Appendix 02 - Manpower Gantt Chart
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 3
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 8

@A300-600
SERVICE BULLETIN
SUMMARY
**CONF ALL
FUEL CENTER TANK
A
FR47
FR40
AREA TO BE INSPECTED.
NOTE:
A
Z140
D_SB_576086_5_SAAA_01_01
Figure A-FSAAA - Sheet 01
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 4
5
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 - CENTER WING BOX - INSPECTION OF HORIZONTAL
SPLICING BETWEEN REAR SPAR AND BOTTOM PANEL AT
JUNCTION WITH FUSELAGE AT FR47
MODIFICATION No.: None
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
NOTE
: This Service Bulletin is only applicable to aircraft on which MOD No.
12171S21827 (REINFORCE FR47) or MOD No. 12249S21912 (REINFORCE
FR47) are not embodied and on which Service Bulletin No. A300-57-6113
(MOD No. 13673S22887) is not accomplished.
(1) Models
B4-603 B4-605R B4-622 B4-622R C4-605R/FC4-620 F4-605R
(2) Effectivity by MSN
0344 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0477 0479 0505
0521 0525 0530 0532 0536 0543 0546 0553 0555 0557-0559 0561 0563 0572 0575
0579 0581 0584 0602-0603 0607-0608 0611 0613 0617-0618 0621 0623 0625-0626
0629-0630 0632-0633 0637 0641 0643 0657 0659 0664 0666 0668 0670 0677 0679
0683 0688 0694 0696 0699 0701 0703 0707 0709 0711 0713 0715 0717 0719
0721-0730 0732-0746 0748-0750 0752-0764 0766 0768-0775 0777-0794 0797
0799-0804
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 10

@A300-600
SERVICE BULLETIN
(3) Effectivity by Operator
The Operator/MSN relationship is provided for information only and is correct at the time
of issue in accordance with the information available to AIRBUS. Any future changes
resulting from transfer of an aircraft from one operator to another will not be reflected in
this list unless the Service Bulletin is revised for another reason.
OPERATOR
 MSN
14S
 0694 0699
 0719
 0721
 0782
 0786
 0787
AAW
 0788
ABR
 0557 0677 0717 0722
AHK
 0683 0770
BCS
 0602 0617 0621 0637 0641 0670 0679 0703 0711 0724 0729 0730
0737 0740 0743 0753 0783 0797
EFX
 0755
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 0726 0728 0735 0736 0738 0742 0745
0748 0752 0757 0759 0760 0761 0766 0768 0769 0771 0772 0774
0777 0778 0779 0780 0781 0789 0790 0791 0792 0793 0794 0799
0800 0801 0802 0803 0804
IRA
 0632 0696 0723 0727
IRM
 0380 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701
0773
KAC
 0344
MNB
 0521 0525 0734 0739 0756 0758
MRJ
 0750 0762
MSR
 0561 0607
QSM
 0584 0603 0744 0749 0764
SOP
 0532
SUD
 0666 0775
TAR
 0505 0558 0563
THA
 0629 0784 0785
TNO
 0626 0643
URS
 0733
UTP
 0707 0725 0732 0741 0746 0754 0763
(4) Configuration by MSN
MSN
 CONFIGURATION
0344 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414
0417 0477 0479 0505 0521 0525 0530 0532 0536 0543 0546
0553 0555 0557 0558 0559 0561 0563 0572 0575 0579 0581
0584 0602 0603 0607 0608 0611 0613 0617 0618 0621 0623
0625 0626 0629 0630 0632 0633 0637 0641 0643 0657 0659
0664 0666 0668 0670 0677 0679 0683 0688 0694 0696 0699
0701 0703 0707 0709 0711 0713 0715 0717 0719 0721 0722
0723 0724 0725
002
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 11

@A300-600
SERVICE BULLETIN
MSN
 CONFIGURATION
0726 0727 0728 0729 0730 0732 0733 0734 0735 0736 0737
0738 0739 0740 0741 0742 0743 0744 0745 0746 0748 0749
0750 0752 0753 0754 0755 0756 0757 0758 0759 0760 0761
0762 0763 0764 0766 0768 0769 0770 0771 0772 0773 0774
0775 0777 0778 0779 0780 0781 0782 0783 0784 0785 0786
0787 0788 0789 0790 0791 0792 0793 0794 0797 0799 0800
0801 0802 0803 0804
001
(5) Configuration definition
**CONF 001
Config. 001 is valid for aircraft on which MOD No. 10155S20321 is embodied.
**CONF 002
Config. 002 is valid for aircraft on which MOD No. 10155S20321 is not embodied and on
which Service Bulletin No. A300-57-6050 (MOD No. 10454S20572) is accomplished.
MSNs 0722 thru 0725 are in Config. 002 because MOD No. 10155S20321 is partially
embodied.
(6) Material Effectivity
**CONF 001
MATERIAL
 QTY PER A/C
 SEE NOTES
Kit 576086A01R05
 1
Consumable CMLA01
 1
**CONF 002
MATERIAL
 QTY PER A/C
 SEE NOTES
Kit 576086A02R02
 1
Consumable CMLA01
 1
**CONF ALL
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
During accomplishment of Structure Significant Item (SSI) Inspection 571011 and
Modification as per the Service Bulletin No. A300-57-6050, cracks have been found on
the horizontal flange of the Frame 47 internal corner angle fitting, on three aircraft. At the
time of the findings, the aircraft were below the SSI inspection threshold of 18,000 FC.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 3
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 12

@A300-600
SERVICE BULLETIN
(2) Objective/Action
This Service Bulletin calls for a rotating probe inspection of twenty holes in the horizontal
flange of the Frame 47 internal corner angle fitting and for an Ultra Sonic inspection of
seventy holes of the CWB lower panel.
The procedure as described in this Service Bulletin is to be performed if no Airbus repair
and/or repair improvement has been previously performed in the same area. In case of
repairs performed previously, please contact AIRBUS Repair Support department for
further instructions.
(3) Advantages
If undetected, cracks can increase in magnitude, leading to a reduction of the residual
strength of the structure. Thus, accomplishment of this Service Bulletin will avoid
extensive structural repairs.
Accomplishment of Service Bulletfin No. A300-57-6113 cancels the requirement of
inspection defined in this Service Bulletin.
(4) Operational/Maintenance Consequences
The Operational/Maintenance Consequences of this Service Bulletin are covered by the
update of the affected publications detailed in ’PLANNING INFORMATION’.
This Service Bulletin supersedes Maintenance Planning Document (MPD) task
571011-01-1, SSI task 571011.
NOTE
: Service Bulletin No. A300-57-6050 has been embodied in all in-service
aircraft included in its effectivity, mandated at 15100 Flight Cycles (FC)
or 38900 Flight Hours (FH) since first flight, whichever occurs first.
D. DESCRIPTION
NOTE
: In case of concurrent embodiment of both inspection Service Bulletin No.
A300-57-6049 and inspection Service Bulletin No. A300-57-6086, AIRBUS
recommends to ensure that a maximum of 50% of the fasteners concerned by
each inspection Service Bulletin (which means a maximum of 50% of the
fasteners of inspection Service Bulletin No. A300-57-6049 and a maximum of
50% of the fasteners of inspection Service Bulletin No. A300-57-6086) are
removed at any time.
To accomplish this Service Bulletin it is necessary to :
**CONF 001
Task 576086-832-801-001: Inspection
(1) Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal
angle of the center wing box
(2) Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal
angle of the center wing box
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 4
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 13

@A300-600
SERVICE BULLETIN
(3) Do an inspection of the hole T (adjacent to the hole G), at the LH internal angle of
the center wing box
(4) Do an inspection of the hole T (adjacent to the hole G), at the RH internal angle of
the center wing box
(5) Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the LH aft
bottom panel of the center wing box
(6) Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the RH aft
bottom panel of the center wing box
**CONF 002
Task 576086-832-801-001: Inspection
(1) Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal
angle of the center wing box
(2) Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal
angle of the center wing box
(3) Do an inspection of the hole T (adjacent to the hole G), at the LH internal angle of
the center wing box
(4) Do an inspection of the hole T (adjacent to the hole G), at the RH internal angle of
the center wing box
(5) Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the LH aft
bottom panel of the center wing box
(6) Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the RH aft
bottom panel of the center wing box
**CONF ALL
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
**CONF 001
This Service Bulletin has been classified Mandatory by the issue of an Airworthiness
Directive (AD) published by the European Av iation Safety Agenc y (EASA). The AD must
be used as the reference document for the mandated accomplishment timescale.
All inspection reports must be sent to AIRBUS within 30 days after the inspection date.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 5
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 14

@A300-600
SERVICE BULLETIN
Table 1, Config. 001 - Ultrasonic Inspection at the LH and RH AFT bottom panel of the center wing
box
Compliance time (whichever occurs
later)
Condition
 Action
Threshold
(whichever occurs
first)
Grace Period
Repetitive interval
(whichever occurs
first)
Average flight time
greater than 1.5
FH/FC
Do the ultrasonic
inspection in
accordance with
SUBTASK
576086-832-008
001 and SUBTASK
576086-832-009
001
6800 FC or 14750
FH since Entry Into
Service (EIS)
12 months
NOTE (*)
None
Crack found
 Contact AIRBUS
and follow their
instructions
NOTE (***)
Before next flight
 None
 None
Apply Service
Bulletin No.
A300-57-6113
and
Before next flight
 None
 None
No further action in
accordance with
this Service
Bulletin
NOTE (**)
None
 None
 None
OR
Crack not found
Repeat the
ultrasonic
inspection in
accordance with
SUBTASK
576086-832-008
001 and SUBTASK
576086-832-009
001
None
 None
 1400 FC or 3050
FH
Average flight time
lower than 1.5
FH/FC
Do the ultrasonic
inspection in
accordance with
SUBTASK
576086-832-008
001 and SUBTASK
576086-832-009
001
7350 FC or 11050
FH since EIS
12 months
NOTE (*)
None
Crack found
 Contact AIRBUS
and follow their
instructions
NOTE (***)
Before next flight
 None
 None
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 6
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 15

@A300-600
SERVICE BULLETIN
Table 1, Config. 001 - Ultrasonic Inspection at the LH and RH AFT bottom panel of the center wing
box
Compliance time (whichever occurs
later)
Condition
 Action
Threshold
(whichever occurs
first)
Grace Period
Repetitive interval
(whichever occurs
first)
Apply Service
Bulletin No.
A300-57-6113
and
Before next flight
 None
 None
No further action in
accordance with
this Service
Bulletin
NOTE (**)
None
 None
 None
OR
Crack not found
Repeat the
ultrasonic
inspection in
accordance with
SUBTASK
576086-832-008
001 and SUBTASK
576086-832-009
001
None
 None
 1500 FC or 2250
FH
NOTE (*): To be counted from revision No. 06 of this Service Bulletin, without exceeding previous
threshold and interval of Service Bulletin revision No. 05.
NOTE (**): Accomplishment of Service Bulletin No. A300-57-6113 cancels the requirement of
inspection defined in this Service Bulletin. The applicable inspection programme is provided in Service
Bulletin No. A300-57-6119.
NOTE (***): Depending on crack finding, please be informed that modification Service Bulletin No.
A300-57-6113 accomplishment could be required by AIRBUS before next flight.
Table 2, Config. 001 - Rototest High Frequency Eddy Current (HFEC) Inspection at the LH and RH
internal angle of the center wing box
Compliance time (whichever occurs
later)
Condition
 Action
Threshold
(whichever occurs
first)
Grace Period
Repetitive
interval
(whichever
occurs first)
Average
flight time
greater
than 1.5
FH/FC
Remove the fasteners A, B, C, D,
E, F, G, P, Q, S (and T if
affected) and do the rototest
HFEC inspection in accordance
with SUBTASK 576086-832-004
001, SUBTASK 576086-832-005
001, SUBTASK 576086-832-006
001 NOTE (***) and SUBTASK
576086-832-007 001 NOTE (***)
6800 FC or 14750
FH since Entry Into
Service (EIS)
12 months
NOTE (*)
None
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 7
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 16

@A300-600
SERVICE BULLETIN
Table 2, Config. 001 - Rototest High Frequency Eddy Current (HFEC) Inspection at the LH and RH
internal angle of the center wing box
Compliance time (whichever occurs
later)
Condition
 Action
Threshold
(whichever occurs
first)
Grace Period
Repetitive
interval
(whichever
occurs first)
Crack
found
Contact AIRBUS and follow their
instructions
NOTE (****)
Before next flight
 None
 None
Apply Service Bulletin No.
A300-57-6113
and
Before next flight
 None
 None
No further action in accordance
with this Service Bulletin
NOTE (**)
None
 None
 None
OR
Install new nominal, R1 oversize
or R2 oversize fasteners and do
the sealing of the fasteners A, B,
C, D, E, F, G, P, Q, S (and T if
affected) in accordance with
SUBTASK 576086-832-004 001,
SUBTASK 576086-832-005 001,
SUBTASK 576086-832-006 001
NOTE (***) and SUBTASK
576086-832-007 001 NOTE (***)
and
Before next flight
 None
 None
Crack not
found
Repeat the rototest HFEC
inspection in accordance with
SUBTASK 576086-832-004 001,
SUBTASK 576086-832-005 001,
SUBTASK 576086-832-006 001
NOTE (***) and SUBTASK
576086-832-007 001 NOTE (***)
None
 None
 6300 FC or
13650 FH
Average
flight time
lower
than 1.5
FH/FC
Remove the fasteners A, B, C, D,
E, F, G, P, Q, S (and T if
affected) and do the rototest
HFEC inspection in accordance
with SUBTASK 576086-832-004
001, SUBTASK 576086-832-005
001, SUBTASK 576086-832-006
001 NOTE (***) and SUBTASK
576086-832-007 001 NOTE (***)
7350 FC or 11050
FH since EIS
12 months
NOTE (*)
None
Crack
found
Contact AIRBUS and follow their
instructions
NOTE (****)
Before next flight
 None
 None
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 8
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 17

@A300-600
SERVICE BULLETIN
Table 2, Config. 001 - Rototest High Frequency Eddy Current (HFEC) Inspection at the LH and RH
internal angle of the center wing box
Compliance time (whichever occurs
later)
Condition
 Action
Threshold
(whichever occurs
first)
Grace Period
Repetitive
interval
(whichever
occurs first)
Apply Service Bulletin No.
A300-57-6113
and
Before next flight
 None
 None
No further action in accordance
with this Service Bulletin
NOTE(**)
None
 None
 None
OR
Install new nominal, R1 oversize
or R2 oversize fasteners and do
the sealing of the fasteners A, B,
C, D, E, F, G, P, Q, S (and T if
affected) in accordance with
SUBTASK 576086-832-004 001,
SUBTASK 576086-832-005 001,
SUBTASK 576086-832-006 001
NOTE (***) and SUBTASK
576086-832-007 001 NOTE (***)
and
Before next flight
 None
 None
Crack not
found
Repeat the rototest HFEC
inspection in accordance with
SUBTASK 576086-832-004 001,
SUBTASK 576086-832-005 001,
SUBTASK 576086-832-006 001
NOTE (***) and SUBTASK
576086-832-007 001 NOTE (***)
None
 None
 6800 FC or
10250 FH
NOTE (*): To be counted from revision No. 06 of this Service Bulletin, without exceeding previous
threshold and interval of Service Bulletin revision No. 05.
NOTE (**): Accomplishment of Service Bulletin No. A300-57-6113 cancels the requirement of
inspection defined in this Service Bulletin. The applicable inspection programme is provided in Service
Bulletin No. A300-57-6119.
NOTE (***): Only if crack found in hole G.
NOTE (****): Depending on crack finding, please be informed that modification Service Bulletin No.
A300-57-6113 accomplishment could be required by AIRBUS before next flight.
**CONF 002
This Service Bulletin has been classified Mandatory by the issue of an Airworthiness
Directive (AD) published by the European Av iation Safety Agenc y (EASA). The AD must
be used as the reference document for the mandated accomplishment timescale.
All inspection reports must be sent to AIRBUS within 30 days after the inspection date.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 9
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 18

@A300-600
SERVICE BULLETIN
Table 1, Config. 002 - Ultrasonic Inspection at the LH and RH AFT bottom panel of the center wing
box
Compliance time (whichever occurs
later)
Condition
 Action
Threshold
(whichever occurs
first)
Grace Period
Repetitive interval
(whichever occurs
first)
Average flight time
greater than 1.5
FH/FC
Do the ultrasonic
inspection in
accordance with
SUBTASK
576086-832-008
002 and SUBTASK
576086-832-009
002
6800 FC or 14750
FH since the
accomplishment of
Service Bulletin
No. A300-57-6050
12 months
NOTE (*)
None
Crack found
 Contact AIRBUS
and follow their
instructions
NOTE (***)
Before next flight
 None
 None
Apply Service
Bulletin No.
A300-57-6113
and
Before next flight
 None
 None
No further action in
accordance with
this Service
Bulletin
NOTE (**)
None
 None
 None
OR
Crack not found
Repeat the
ultrasonic
inspection in
accordance with
SUBTASK
576086-832-008
002 and SUBTASK
576086-832-009
002
None
 None
 1400 FC or 3050
FH
Average flight time
lower than 1.5
FH/FC
Do the ultrasonic
inspection in
accordance with
SUBTASK
576086-832-008
002 and SUBTASK
576086-832-009
002
7350 FC or 11050
FH since the
accomplishment of
Service Bulletin
No. A300-57-6050
12 months
NOTE (*)
None
Crack found
 Contact AIRBUS
and follow their
instructions
NOTE (***)
Before next flight
 None
 None
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 10
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 19

@A300-600
SERVICE BULLETIN
Table 1, Config. 002 - Ultrasonic Inspection at the LH and RH AFT bottom panel of the center wing
box
Compliance time (whichever occurs
later)
Condition
 Action
Threshold
(whichever occurs
first)
Grace Period
Repetitive interval
(whichever occurs
first)
Apply Service
Bulletin No.
A300-57-6113
and
Before next flight
 None
 None
No further action in
accordance with
this Service
Bulletin
NOTE(**)
None
 None
 None
OR
Crack not found
Repeat the
ultrasonic
inspection in
accordance with
SUBTASK
576086-832-008
002 and SUBTASK
576086-832-009
002
None
 None
 1500 FC or 2250
FH
NOTE (*): To be counted from revision No. 06 of this Service Bulletin, without exceeding previous
threshold and interval of Service Bulletin revision No. 05.
NOTE (**): Accomplishment of Service Bulletin No. A300-57-6113 cancels the requirement of
inspection defined in this Service Bulletin. The applicable inspection programme is provided in Service
Bulletin No. A300-57-6119.
NOTE (***): Depending on crack finding, please be informed that modification Service Bulletin No.
A300-57-6113 accomplishment could be required by AIRBUS before next flight.
Table 2, Config. 002 - Rototest High Frequency Eddy Current (HFEC) Inspection at the LH and RH
internal angle of the center wing box
Compliance time (whichever occurs
later)
Condition
 Action
Threshold
(whichever occurs
first)
Grace Period
Repetitive
interval
(whichever
occurs first)
Average
flight time
greater
than 1.5
FH/FC
Remove the fasteners A, B, C, D,
E, F, G, P, Q, S (and T if
affected) and do the rototest
HFEC inspection in accordance
with SUBTASK 576086-832-004
002, SUBTASK 576086-832-005
002, SUBTASK 576086-832-006
002 NOTE (***) and SUBTASK
576086-832-007 002 NOTE (***)
6800 FC or 14750
FH since the
accomplishment of
Service Bulletin No.
A300-57-6050
12 months
NOTE (*)
None
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 11
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 20

@A300-600
SERVICE BULLETIN
Table 2, Config. 002 - Rototest High Frequency Eddy Current (HFEC) Inspection at the LH and RH
internal angle of the center wing box
Compliance time (whichever occurs
later)
Condition
 Action
Threshold
(whichever occurs
first)
Grace Period
Repetitive
interval
(whichever
occurs first)
Crack
found
Contact AIRBUS and follow their
instructions
NOTE (****)
Before next flight
 None
 None
Apply Service Bulletin No.
A300-57-6113
and
Before next flight
 None
 None
No further action in accordance
with this Service Bulletin
NOTE(**)
None
 None
 None
OR
Install new R2 oversize fasteners
and do the sealing of the
fasteners A, B, C, D, E, F, G, P,
Q, S (and T if affected) in
accordance with SUBTASK
576086-832-004 002, SUBTASK
576086-832-005 002, SUBTASK
576086-832-006 002 NOTE (***)
and SUBTASK 576086-832-007
002 NOTE (***)
and
Before next flight
 None
 None
Crack not
found
Repeat the rototest HFEC
inspection in accordance with
SUBTASK 576086-832-004 002,
SUBTASK 576086-832-005 002,
SUBTASK 576086-832-006 002
NOTE (***) and SUBTASK
576086-832-007 002 NOTE (***)
None
 None
 6300 FC or
13650 FH
Average
flight time
lower
than 1.5
FH/FC
Remove the fasteners A, B, C, D,
E, F, G, P, Q, S (and T if
affected) and do the rototest
HFEC inspection in accordance
with SUBTASK 576086-832-004
002, SUBTASK 576086-832-005
002, SUBTASK 576086-832-006
002 NOTE (***) and SUBTASK
576086-832-007 002 NOTE (***)
7350 FC or 11050
FH since the
accomplishment of
Service Bulletin No.
A300-57-6050
12 months
NOTE (*)
None
Crack
found
Contact AIRBUS and follow their
instructions
NOTE (****)
Before next flight
 None
 None
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 12
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 21

@A300-600
SERVICE BULLETIN
Table 2, Config. 002 - Rototest High Frequency Eddy Current (HFEC) Inspection at the LH and RH
internal angle of the center wing box
Compliance time (whichever occurs
later)
Condition
 Action
Threshold
(whichever occurs
first)
Grace Period
Repetitive
interval
(whichever
occurs first)
Apply Service Bulletin No.
A300-57-6113
and
Before next flight
 None
 None
No further action in accordance
with this Service Bulletin
NOTE(**)
None
 None
 None
OR
Install new R2 oversize fasteners
and do the sealing of the
fasteners A, B, C, D, E, F, G, P,
Q, S (and T if affected) in
accordance with SUBTASK
576086-832-004 002, SUBTASK
576086-832-005 002, SUBTASK
576086-832-006 002 NOTE (***)
and SUBTASK 576086-832-007
002 NOTE (***)
and
Before next flight
 None
 None
Crack not
found
Repeat the rototest HFEC
inspection in accordance with
SUBTASK 576086-832-004 002,
SUBTASK 576086-832-005 002,
SUBTASK 576086-832-006 002
NOTE (***) and SUBTASK
576086-832-007 002 NOTE (***)
None
 None
 6800 FC or
10250 FH
NOTE (*): To be counted from revision No. 06 of this Service Bulletin, without exceeding previous
threshold and interval of Service Bulletin revision No 05.
NOTE (**): Accomplishment of Service Bulletin No. A300-57-6113 cancels the requirement of
inspection defined in this Service Bulletin. The applicable inspection programme is provided in Service
Bulletin No. A300-57-6119.
NOTE (***): Only if crack found in hole G.
NOTE (****): Depending on crack finding, please be informed that modification Service Bulletin No.
A300-57-6113 accomplishment could be required by AIRBUS before next flight.
**CONF ALL
F. APPROVAL
The technical content of this document is approved under the authority of Design
Organisation Approval No. EASA.21J.031
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 13
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 22

@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 576086-832-801-001: Inspection
Get Access
 12.00
On Aircraft
Do an inspection of the holes A, B, C, D, E, F, G, P, Q
and S, at the LH internal angle of the center wing box
4.00
Do an inspection of the holes A, B, C, D, E, F, G, P, Q
and S, at the RH internal angle of the center wing box
4.00
Do an inspection of the hole T (adjacent to the hole G),
at the LH internal angle of the center wing box
0.50
Do an inspection of the hole T (adjacent to the hole G),
at the RH internal angle of the center wing box
0.50
Do an ultrasonic inspection of the holes type 1, type 2
and type 3, at the LH aft bottom panel of the center
wing box
2.00
Do an ultrasonic inspection of the holes type 1, type 2
and type 3, at the RH aft bottom panel of the center
wing box
2.00
Tests
 0.50
Close-Up
 9.50
TOTAL MANHOURS
 35.00
ELAPSED TIME (HOURS)
 28.50
NOTE
: For an explanation of the manhours and elapsed time, refer to the Gantt
Chart, Fig. A-FARAA
 given in Appendix 02.
NOTE
: The minimum manhours necessary to accomplish this Service Bulletin are
those for the Inspection. Depending on the inspection result, additional
manhours can apply.
**CONF 002
Task 576086-832-801-001: Inspection
Get Access
 12.00
On Aircraft
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 14
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 23

@A300-600
SERVICE BULLETIN
Task 576086-832-801-001: Inspection
Do an inspection of the holes A, B, C, D, E, F, G, P, Q
and S, at the LH internal angle of the center wing box
4.00
Do an inspection of the holes A, B, C, D, E, F, G, P, Q
and S, at the RH internal angle of the center wing box
4.00
Do an inspection of the hole T (adjacent to the hole G),
at the LH internal angle of the center wing box
0.50
Do an inspection of the hole T (adjacent to the hole G),
at the RH internal angle of the center wing box
0.50
Do an ultrasonic inspection of the holes type 1, type 2
and type 3, at the LH aft bottom panel of the center
wing box
2.00
Do an ultrasonic inspection of the holes type 1, type 2
and type 3, at the RH aft bottom panel of the center
wing box
2.00
Tests
 0.50
Close-Up
 9.50
TOTAL MANHOURS
 35.00
ELAPSED TIME (HOURS)
 28.50
NOTE
: For an explanation of the manhours and elapsed time, refer to the Gantt
Chart, Fig. A-FARAA
 given in Appendix 02.
NOTE
: The minimum manhours necessary to accomplish this Service Bulletin are
those for the Inspection. Depending on the inspection result, additional
manhours can apply.
**CONF ALL
H. WEIGHT AND BALANCE
Not Changed
I. ELECTRICAL LOAD DATA
Not Changed
J. REFERENCES
**CONF 001
Aircraft Maintenance Manual (AMM)
 06-31-53 06-41-00 06-41-53
20-21-12 24-00-00 28-10-00
28-11-00 28-11-29 28-25-00
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
Non Destructive Test Manual (NTM)
 57-10-11 57-10-45
Service Bulletin (SB)
 A300-57-6050
A300-57-6113
Standards Manual (SM)
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 15
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 24

@A300-600
SERVICE BULLETIN
Structural Repair Manual (SRM)
 51-24-00 51-40-00 51-40-20
51-40-30 51-40-40 51-75-10
**CONF 002
Aircraft Maintenance Manual (AMM)
 06-31-53 06-41-00 06-41-53
20-21-12 24-00-00 28-10-00
28-11-00 28-11-29 28-25-00
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
Non Destructive Test Manual (NTM)
 57-10-11 57-10-45
Service Bulletin (SB)
 A300-57-6050
A300-57-6113
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-24-00 51-40-00 51-40-20
51-40-30 51-40-40 51-75-10
**CONF ALL
K. PUBLICATION AFFECTED
Maintenance Planning Document (MPD)
 571011-01-1
L. INTERCHANGEABILITY/MIXABILITY
Not Applicable
M. SPARES
None
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 16
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 25

@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 576086A01R05
Kit 576086A02R02
AIRBUS Material, Logistics and Suppliers
ATP II B,
Hein-Sass-Weg 24
21129 HAMBURG
GERMANY
For ordering by internet:
http://spares.airbus.com
For ordering by E-mail: airbus.kit@airbus.com
Telephone Hotline: +49 40 743 51616
(2) Price and Availability
Kit 576086A01R05
Cost
 41,310.00 USD
Availability
 200 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
AIRBUS Spares portal or through a request for quotation to airbus.kit@airbus.com.
Kit 576086A02R02
Cost
 14,130.00 USD
Availability
 200 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
AIRBUS Spares portal or through a request for quotation to airbus.kit@airbus.com.
B. INDUSTRY SUPPORT INFORMATION
AIRBUS will not provide industry support for accomplishment of this Service Bulletin.
This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 17
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 26

@A300-600
SERVICE BULLETIN
For the organization of this retrofit, you are kindly requested to contact AIRBUS retrofit
management department: monitored.retrofit@airbus.com.
C. LIST OF COMPONENTS
Kit 576086A01R05
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
1
 ASNA2532-9
 8
 Nut
1
 NAS1727-9E
 8
 Nut
2
 ASNA2026T9-40
 2
 Bolt
2
 NSA5356-9-40
 2
 Bolt
2
 NSA5358-9-40
 2
 Bolt
3
 NSA5368PD916B
 4
 Washer
3
 NSA5369PD916B
 4
 Washer
4
 ASNA2026T9-32
 2
 Bolt
4
 NSA5356-9-32
 2
 Bolt
4
 NSA5358-9-32
 2
 Bolt
5
 ASNA2532-8
 8
 Nut
5
 NAS1727-8E
 8
 Nut
6
 NSA5368PD816D
 8
 Washer
6
 NSA5369PD816D
 8
 Washer
7
 ASNA2026T8-32
 2
 Bolt
7
 NSA5356-8-32
 2
 Bolt
7
 NSA5358-8-32
 2
 Bolt
8
 ASNA2026T9-30
 2
 Bolt
8
 NSA5356-9-30
 2
 Bolt
8
 NSA5358-9-30
 2
 Bolt
9
 ASNA2026T8-27
 2
 Bolt
9
 NSA5356-8-27
 2
 Bolt
9
 NSA5358-8-27
 2
 Bolt
10
 NSA5368PD816B
 4
 Washer
10
 NSA5369PD816B
 4
 Washer
11
 ASNA2026T8-36
 2
 Bolt
11
 NSA5356-8-36
 2
 Bolt
11
 NSA5358-8-36
 2
 Bolt
12
 ASNA2026T8-38
 2
 Bolt
12
 NSA5356-8-38
 2
 Bolt
12
 NSA5358-8-38
 2
 Bolt
13
 ASNA2531-8
 2
 Nut
13
 NAS1726-8E
 2
 Nut
15
 ASNA2026T9-42
 2
 Bolt
15
 NSA5356-9-42
 2
 Bolt
15
 NSA5358-9-42
 2
 Bolt
16
 ASNA2532-10
 4
 Nut
16
 NAS1727-10E
 4
 Nut
17
 ASNA2026T10-44
 2
 Bolt
17
 NSA5356-10-44
 2
 Bolt
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 18
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SERVICE BULLETIN
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
17
 NSA5358-10-44
 2
 Bolt
18
 ASNA2026T10-47
 2
 Bolt
18
 NSA5356-10-47
 2
 Bolt
18
 NSA5358-10-47
 2
 Bolt
19
 ASNA2027T8-26
 2
 Bolt
19
 NSA5357-8-24
 2
 Bolt
19
 NSA5359-8-24
 2
 Bolt
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 576086A02R02
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
1
 ASNA2532-9
 8
 Nut
1
 NAS1727-9E
 8
 Nut
2
 NSA5358-9-40
 2
 Bolt
3
 NSA5368PD916B
 4
 Washer
4
 NSA5358-9-32
 2
 Bolt
5
 ASNA2532-8
 8
 Nut
5
 NAS1727-8E
 8
 Nut
6
 NSA5368PD816D
 8
 Washer
7
 NSA5358-8-32
 2
 Bolt
8
 NSA5358-9-30
 2
 Bolt
9
 NSA5358-8-27
 2
 Bolt
10
 NSA5368PD816B
 4
 Washer
11
 NSA5358-8-36
 2
 Bolt
12
 NSA5358-8-38
 2
 Bolt
13
 ASNA2531-8
 2
 Nut
13
 NAS1726-8E
 2
 Nut
15
 NSA5358-9-42
 2
 Bolt
16
 ASNA2532-10
 4
 Nut
16
 NAS1727-10E
 4
 Nut
17
 NSA5358-10-44
 2
 Bolt
18
 NSA5358-10-47
 2
 Bolt
19
 NSA5359-8-24
 2
 Bolt
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.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 19
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D. LIST OF MATERIALS - OPERATOR SUPPLIED
(1) Consumable Materials
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
Fuel Tank Sealant Polysulfide
 09-001
 As required
Solvent
 11-026
 As required
Chemical Conversion Coating
Yellow Aluminum
13-002
 As required
Primer Coating Epoxy Polyamide
Chemical
16-006
 As required
Polyurethane Finish Paint (For
External Applic.)
16-018
 As required
(2) Components
None
(3) Equipment
None
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
F. TOOLING
(1) Tooling - Price and Availability
Tools listed in NTM 57-10-11 Part 6 and NTM 57-10-45 Part 4.
(2) Tools
(1) To accomplish this Service Bulletin it is necessary to use the following tools and
equipment :
Equipment and materials for check of holes as per NTM 57-10-11 Part 6 and NTM
57-10-45 Part 4.
None
(3) Special Tools
None
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 20
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3. ACCOMPLISHMENT INSTRUCTIONS
Task 576086-832-801-001 - Inspection
WARNING
: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
WARNING
: MAKE SURE THAT YOU OBEY ALL THE SAFETY PRECAUTIONS APPLICABLE
TO THE ACCESS TO AND THE WORK IN THE FUEL CENTER TANK.
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. To allow more flexibility, the rule "refer to" and "in
accordance with" will apply to these paragraphs 3.C. and 3.D. 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 the aircraft can be put back into a
serviceable condition.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 21
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NOTE
: This Service Bulletin contains the instructions for the on-aircraft maintenance
necessary to ensure the continued airworthiness of the aircraft.
For any deviations to the instructions contained herein, contact Airbus for further
instructions and approval.
NOTE
: The purpose of flowcharts is to supplement the information given in the Procedure
and Compliance paragraphs and not to serve as the primary source for tasks or
compliance times given in this Service Bulletin.
Task Associated Data
**CONF 001
Zone
140
Manpower
TOTAL MANHOURS
 35.00
ELAPSED TIME (HOURS)
 28.50
**CONF 002
Zone
140
Manpower
TOTAL MANHOURS
 35.00
ELAPSED TIME (HOURS)
 28.50
**CONF ALL
A. GENERAL
**CONF 001
(1) Subtask 576086-910-001-002 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
Material necessary to do the job
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Fuel Tank Sealant
Polysulfide
09-001
 As required
Solvent
 11-026
 As required
Chemical Conversion
Coating Yellow Aluminum
13-002
 As required
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 22
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ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Primer Coating Epoxy
Polyamide Chemical
16-006
 As required
Polyurethane Finish Paint
(For External Applic.)
16-018
 As required
References
Aircraft Maintenance Manual (AMM)
 06-31-53, Page Block 001
06-41-00, Page Block 001
20-21-12, Page Block 001
Consumable Material List (CML)
Structural Repair Manual (SRM)
 51-24-00
51-40-00
51-40-20
51-40-30
51-40-40
51-75-10
(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to
the Consumable Materials List (CML).
(b) Clean the surfaces to do an inspection with:
Solvent 11-026 As required
(c) Renew the protective finish in accordance with SRM 51-75-10:
Chemical
Conversion Coating
Yellow Aluminum
13-002 As required
Primer Coating
Epoxy Polyamide
Chemical
16-006 As required
and
Polyurethane Finish
Paint (For External
Applic.)
16-018 As required
(d) Apply sealant in accordance with SRM 51-24-00:
Fuel Tank Sealant
Polysulfide
09-001 As required
(e) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30.
(f) 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.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 23
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(g) Remove and install fasteners in accordance with SRM 51-40-20.
(h) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page
Block 001.
(i) Use a non-metallic spatula to remove the sealant and clean the areas with
Solvent 11-026 As required
(j) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.
(k) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.
(l) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40.
(m) 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.
(2) Subtask 576086-839-001-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
**CONF 002
(1) Subtask 576086-910-001-002 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
Material necessary to do the job
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Fuel Tank Sealant
Polysulfide
09-001
 As required
Solvent
 11-026
 As required
Chemical Conversion
Coating Yellow Aluminum
13-002
 As required
Primer Coating Epoxy
Polyamide Chemical
16-006
 As required
Polyurethane Finish Paint
(For External Applic.)
16-018
 As required
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 24
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References
Aircraft Maintenance Manual (AMM)
 06-31-53, Page Block 001
06-41-00, Page Block 001
20-21-12, Page Block 001
Consumable Material List (CML)
Structural Repair Manual (SRM)
 51-24-00
51-40-00
51-40-20
51-40-30
51-40-40
51-75-10
(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to
the Consumable Materials List (CML).
(b) Clean the surfaces to do an inspection with:
Solvent 11-026 As required
(c) Renew the protective finish in accordance with SRM 51-75-10:
Chemical
Conversion Coating
Yellow Aluminum
13-002 As required
Primer Coating
Epoxy Polyamide
Chemical
16-006 As required
and
Polyurethane Finish
Paint (For External
Applic.)
16-018 As required
(d) Apply sealant in accordance with SRM 51-24-00:
Fuel Tank Sealant
Polysulfide
09-001 As required
(e) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30.
(f) 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.
(g) Remove and install fasteners in accordance with SRM 51-40-20.
(h) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page
Block 001.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 25
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(i) Use a non-metallic spatula to remove the sealant and clean the areas with
Solvent 11-026 As required
(j) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.
(k) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.
(l) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40.
(m) 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.
(2) Subtask 576086-839-001-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
**CONF ALL
B. PREPARATION
**CONF 001
(1) Subtask 576086-941-001-002 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-41-53
24-00-00, Page Block 301
28-10-00, Page Block 301
28-11-29, Page Block 401
28-25-00, Page Block 301
NOTE
: For the basic Aircraft configuration, refer to AMM Chapter "Introduction -
Aircraft status for maintenance" in Manual Front Matter section.
(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00 Page
Block 301).
(b) Put the access platform(s) in position.
(c) Defuel the fuel center tank (Refer to AMM 28-25-00 Page Block 301).
NOTE
: Defuel the fuel center tank only for the HFEC inspection.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 26
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(d) Open the access doors 147AZ and 148AZ (Refer to AMM 28-11-29 Page Block
401 and AMM 06-41-53).
(e) Respect the procedure required to work in the fuel center tank (Refer to AMM
28-10-00 Page Block 301).
**CONF 002
(1) Subtask 576086-941-001-002 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-41-53
24-00-00, Page Block 301
28-10-00, Page Block 301
28-11-29, Page Block 401
28-25-00, Page Block 301
NOTE
: For the basic Aircraft configuration, refer to AMM Chapter "Introduction -
Aircraft status for maintenance" in Manual Front Matter section.
(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00 Page
Block 301).
(b) Put the access platform(s) in position.
(c) Defuel the fuel center tank (Refer to AMM 28-25-00 Page Block 301).
NOTE
: Defuel the fuel center tank only for the HFEC inspection.
(d) Open the access doors 147AZ and 148AZ (Refer to AMM 28-11-29 Page Block
401 and AMM 06-41-53).
(e) Respect the procedure required to work in the fuel center tank (Refer to AMM
28-10-00 Page Block 301).
**CONF ALL
C. PROCEDURE
**CONF 001
(1) Subtask 576086-832-004-001 - Do an inspection of the holes A, B, C, D, E, F, G, P,
Q and S, at the LH internal angle of the center wing box
Work Zones and Access Panels
Zone
 Access/Work location
140
 Work location
 Frame 47
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 27
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Manpower Resources
Manhours
 4.00
Minimum number of person
 1
Subtask elapsed time
 4.00
Skills
 AIRFRAME
Material necessary to do the job
Kit 576086A01R05
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 ASNA2532-9
 4
 Nut
1
 NAS1727-9E
 4
 Nut
2
 ASNA2026T9-40
 1
 Bolt
2
 NSA5356-9-40
 1
 Bolt
2
 NSA5358-9-40
 1
 Bolt
3
 NSA5368PD916B
 2
 Washer
3
 NSA5369PD916B
 2
 Washer
4
 ASNA2026T9-32
 1
 Bolt
4
 NSA5356-9-32
 1
 Bolt
4
 NSA5358-9-32
 1
 Bolt
5
 ASNA2532-8
 3
 Nut
5
 NAS1727-8E
 3
 Nut
6
 NSA5368PD816D
 3
 Washer
6
 NSA5369PD816D
 3
 Washer
7
 ASNA2026T8-32
 1
 Bolt
7
 NSA5356-8-32
 1
 Bolt
7
 NSA5358-8-32
 1
 Bolt
8
 ASNA2026T9-30
 1
 Bolt
8
 NSA5356-9-30
 1
 Bolt
8
 NSA5358-9-30
 1
 Bolt
9
 ASNA2026T8-27
 1
 Bolt
9
 NSA5356-8-27
 1
 Bolt
9
 NSA5358-8-27
 1
 Bolt
10
 NSA5368PD816B
 2
 Washer
10
 NSA5369PD816B
 2
 Washer
11
 ASNA2026T8-36
 1
 Bolt
11
 NSA5356-8-36
 1
 Bolt
11
 NSA5358-8-36
 1
 Bolt
12
 ASNA2026T8-38
 1
 Bolt
12
 NSA5356-8-38
 1
 Bolt
12
 NSA5358-8-38
 1
 Bolt
13
 ASNA2531-8
 1
 Nut
13
 NAS1726-8E
 1
 Nut
15
 ASNA2026T9-42
 1
 Bolt
15
 NSA5356-9-42
 1
 Bolt
15
 NSA5358-9-42
 1
 Bolt
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 28
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@A300-600
SERVICE BULLETIN
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
16
 ASNA2532-10
 2
 Nut
16
 NAS1727-10E
 2
 Nut
17
 ASNA2026T10-44
 1
 Bolt
17
 NSA5356-10-44
 1
 Bolt
17
 NSA5358-10-44
 1
 Bolt
18
 ASNA2026T10-47
 1
 Bolt
18
 NSA5356-10-47
 1
 Bolt
18
 NSA5358-10-47
 1
 Bolt
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Fuel Tank Sealant
Polysulfide
09-001
 As required
Solvent
 11-026
 As required
References
Aircraft Maintenance Manual (AMM)
 20-21-12, Page Block 001
Non Destructive Test Manual (NTM)
 57-10-11
Service Bulletin (SB)
 A300-57-6113
Structural Repair Manual (SRM)
 51-40-20
51-40-30
Fig. A-FBAAA
Inspection of the Holes A, B, C, D, E, F,
G, P, Q, S and T (adjacent to the Hole
G), at LH and RH Internal Angle of the
Center Wing Box
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Fig. A-FFBAA
Flowchart
Sheet 01
NOTE
: Firstly, the stack up assembly must be checked to determine the actual
length of the bolt to be used.
NOTE
: The installed fasteners shall be checked in accordance with the
requirements of SRM Chapter 51 to ensure that adequate thread
protrusion is maintained after installation.
(a) Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal
angle of the center wing box
Refer to Fig. A-FBAAA
 and Fig. A-FFBAA
(b) Remove the sealant around the fasteners.
(c) Remove the fasteners from the holes A, B, C, D, E, F, G, P, Q and S (Items (1)
thru (18)).
In accordance with SRM 51-40-20
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 29
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(d) Clean the holes with
Solvent 11-026 As required
(e) Measure the diameter of the holes (nominal diameter, R1 oversize or R2 oversize).
(f) Do a rotating probe inspection
(Refer to NTM 57-10-11, Part 6)
1
 Crack found
a
 If crack found in hole G do SUBTASK 576086-832-006 001 Do an
inspection of the hole T (adjacent to the hole G), at the LH internal angle
of the center wing box .
b
 Contact AIRBUS and follow their instructions before next flight.
NOTE
: Depending on crack finding, please be informed
that modification Service Bulletin No. A300-57-6113
accomplishment could be required by AIRBUS before
next flight.
2
 No crack found
Accomplish Service Bulletin No. A300-57-6113 and no further action in
accordance with this Service Bulletin.
or
Install the new nominal, R1 oversize or R2 oversize fasteners in relation to the
removed fasteners and the initial hole diameter measured in step (e) of this
subtask.
In accordance with SRM 51-40-20 and SRM 51-40-30
Refer to AMM 20-21-12, Page Block 001
a
 Install :
Hole A :
1 Nut NAS1727-9E Item 1
or
1 Nut ASNA2532-9 Item 1
1 Bolt ASNA2026T9-40 Item 2
or
1 Bolt NSA5356-9-40 Item 2
or
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 30
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@A300-600
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1 Bolt NSA5358-9-40 Item 2
Hole B :
1 Nut NAS1727-9E Item 1
or
1 Nut ASNA2532-9 Item 1
1 Washer NSA5369PD916B Item 3
or
1 Washer NSA5368PD916B Item 3
1 Bolt ASNA2026T9-32 Item 4
or
1 Bolt NSA5356-9-32 Item 4
or
1 Bolt NSA5358-9-32 Item 4
NOTE
: Only install the washer Item 3 if you found a washer
during the removal procedure.
Hole C :
1 Nut NAS1727-8E Item 5
or
1 Nut ASNA2532-8 Item 5
1 Washer NSA5369PD816D Item 6
or
1 Washer NSA5368PD816D Item 6
1 Bolt ASNA2026T8-32 Item 7
or
1 Bolt NSA5356-8-32 Item 7
or
1 Bolt NSA5358-8-32 Item 7
NOTE
: Only install the washer Item 6 if you found a washer
during the removal procedure.
Hole D :
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
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1 Nut NAS1727-9E Item 1
or
1 Nut ASNA2532-9 Item 1
1 Washer NSA5369PD916B Item 3
or
1 Washer NSA5368PD916B Item 3
1 Bolt ASNA2026T9-30 Item 8
or
1 Bolt NSA5356-9-30 Item 8
or
1 Bolt NSA5358-9-30 Item 8
NOTE
: Only install the washer Item 3 if you found a washer
during the removal procedure.
Hole E :
1 Nut NAS1727-8E Item 5
or
1 Nut ASNA2532-8 Item 5
1 Washer NSA5369PD816D Item 6
or
1 Washer NSA5368PD816D Item 6
1 Bolt ASNA2026T8-27 Item 9
or
1 Bolt NSA5356-8-27 Item 9
or
1 Bolt NSA5358-8-27 Item 9
NOTE
: Only install the washer Item 6 if you found a washer
during the removal procedure.
Hole F :
1 Nut NAS1727-8E Item 5
or
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 32
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### Page 41

@A300-600
SERVICE BULLETIN
1 Nut ASNA2532-8 Item 5
1 Washer NSA5369PD816B Item 10
or
1 Washer NSA5368PD816B Item 10
or
1 Washer NSA5369PD816D Item 6
or
1 Washer NSA5368PD816D Item 6
1 Bolt ASNA2026T8-36 Item 11
or
1 Bolt NSA5356-8-36 Item 11
or
1 Bolt NSA5358-8-36 Item 11
NOTE
: Only install the washer Item 6 or Item 10 if you found a
washer during the removal procedure.
Hole G :
1 Nut NAS1726-8E Item 13
or
1 Nut ASNA2531-8 Item 13
1 Washer NSA5369PD816B Item 10
or
1 Washer NSA5368PD816B Item 10
1 Bolt ASNA2026T8-38 Item 12
or
1 Bolt NSA5356-8-38 Item 12
or
1 Bolt NSA5358-8-38 Item 12
NOTE
: Only install the washer Item 10 if you found a washer
during the removal procedure.
Hole P :
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 33
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### Page 42

@A300-600
SERVICE BULLETIN
1 Nut NAS1727-9E Item 1
or
1 Nut ASNA2532-9 Item 1
1 Bolt ASNA2026T9-42 Item 15
or
1 Bolt NSA5356-9-42 Item 15
or
1 Bolt NSA5358-9-42 Item 15
Hole Q :
1 Nut NAS1727-10E Item 16
or
1 Nut ASNA2532-10 Item 16
1 Bolt ASNA2026T10-44 Item 17
or
1 Bolt NSA5356-10-44 Item 17
or
1 Bolt NSA5358-10-44 Item 17
Hole S :
1 Nut NAS1727-10E Item 16
or
1 Nut ASNA2532-10 Item 16
1 Bolt ASNA2026T10-47 Item 18
or
1 Bolt NSA5356-10-47 Item 18
or
1 Bolt NSA5358-10-47 Item 18
b
 Apply
Fuel Tank Sealant
Polysulfide
09-001 As required
to the fasteners of the holes A, B, C, D, E, F, G, P, Q and S.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 34
5
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### Page 43

@A300-600
SERVICE BULLETIN
c
 Do the subsequent inspections at the intervals given in Accomplishment
Timescale Table 2.
(g) Upload the completed Inspection Report sheet given in Appendix 01 in accordance
with ISI 00.00.00179 through the SB Reporting application in AirbusWorld.
(2) Subtask 576086-832-005-001 - Do an inspection of the holes A, B, C, D, E, F, G, P,
Q and S, at the RH internal angle of the center wing box
Work Zones and Access Panels
Zone
 Access/Work location
140
 Work location
 Frame 47
Manpower Resources
Manhours
 4.00
Minimum number of person
 1
Subtask elapsed time
 4.00
Skills
 AIRFRAME
Material necessary to do the job
Kit 576086A01R05
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 ASNA2532-9
 4
 Nut
1
 NAS1727-9E
 4
 Nut
2
 ASNA2026T9-40
 1
 Bolt
2
 NSA5356-9-40
 1
 Bolt
2
 NSA5358-9-40
 1
 Bolt
3
 NSA5368PD916B
 2
 Washer
3
 NSA5369PD916B
 2
 Washer
4
 ASNA2026T9-32
 1
 Bolt
4
 NSA5356-9-32
 1
 Bolt
4
 NSA5358-9-32
 1
 Bolt
5
 ASNA2532-8
 3
 Nut
5
 NAS1727-8E
 3
 Nut
6
 NSA5368PD816D
 3
 Washer
6
 NSA5369PD816D
 3
 Washer
7
 ASNA2026T8-32
 1
 Bolt
7
 NSA5356-8-32
 1
 Bolt
7
 NSA5358-8-32
 1
 Bolt
8
 ASNA2026T9-30
 1
 Bolt
8
 NSA5356-9-30
 1
 Bolt
8
 NSA5358-9-30
 1
 Bolt
9
 ASNA2026T8-27
 1
 Bolt
9
 NSA5356-8-27
 1
 Bolt
9
 NSA5358-8-27
 1
 Bolt
10
 NSA5368PD816B
 2
 Washer
10
 NSA5369PD816B
 2
 Washer
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 35
5
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### Page 44

@A300-600
SERVICE BULLETIN
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
11
 ASNA2026T8-36
 1
 Bolt
11
 NSA5356-8-36
 1
 Bolt
11
 NSA5358-8-36
 1
 Bolt
12
 ASNA2026T8-38
 1
 Bolt
12
 NSA5356-8-38
 1
 Bolt
12
 NSA5358-8-38
 1
 Bolt
13
 ASNA2531-8
 1
 Nut
13
 NAS1726-8E
 1
 Nut
15
 ASNA2026T9-42
 1
 Bolt
15
 NSA5356-9-42
 1
 Bolt
15
 NSA5358-9-42
 1
 Bolt
16
 ASNA2532-10
 2
 Nut
16
 NAS1727-10E
 2
 Nut
17
 ASNA2026T10-44
 1
 Bolt
17
 NSA5356-10-44
 1
 Bolt
17
 NSA5358-10-44
 1
 Bolt
18
 ASNA2026T10-47
 1
 Bolt
18
 NSA5356-10-47
 1
 Bolt
18
 NSA5358-10-47
 1
 Bolt
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Fuel Tank Sealant
Polysulfide
09-001
 As required
Solvent
 11-026
 As required
References
Aircraft Maintenance Manual (AMM)
 20-21-12, Page Block 001
Non Destructive Test Manual (NTM)
 57-10-11
Service Bulletin (SB)
 A300-57-6113
Structural Repair Manual (SRM)
 51-40-20
51-40-30
Fig. A-FBAAA
Inspection of the Holes A, B, C, D, E, F,
G, P, Q, S and T (adjacent to the Hole
G), at LH and RH Internal Angle of the
Center Wing Box
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Fig. A-FFBAA
Flowchart
Sheet 01
(a) Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the RH internal
angle of the center wing box
refer to Fig. A-FBAAA
 and Fig. A-FFBAA
(b) Remove the sealant around the fasteners.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 36
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### Page 45

@A300-600
SERVICE BULLETIN
(c) Remove the fasteners from the holes A, B, C, D, E, F, G, P, Q and S (Items (1)
thru (18)).
In accordance with SRM 51-40-20
(d) Clean the holes with
Solvent 11-026 As required
(e) Measure the diameter of the holes (nominal diameter, R1 oversize or R2 oversize).
(f) Do a rotating probe inspection
(Refer to NTM 57-10-11, Part 6)
1
 Crack found
a
 If crack found in hole G do SUBTASK 576086-832-007 001 Do an
inspection of the hole T (adjacent to the hole G), at the RH internal angle
of the center wing box .
b
 Contact AIRBUS and follow their instructions before next flight.
NOTE
: Depending on crack finding, please be informed
that modification Service Bulletin No. A300-57-6113
accomplishment could be required by AIRBUS before
next flight.
2
 No crack found
Accomplish Service Bulletin No. A300-57-6113 and no further action in
accordance with this Service Bulletin.
or
Install the new nominal R1 oversize or R2 oversize fasteners in relation to the
removed fasteners and the initial hole diameter measured in step (e) of this
subtask.
In accordance with SRM 51-40-20 and SRM 51-40-30
Refer to AMM 20-21-12, Page Block 001
a
 Install :
Hole A :
1 Nut NAS1727-9E Item 1
or
1 Nut ASNA2532-9 Item 1
1 Bolt ASNA2026T9-40 Item 2
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 37
5
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### Page 46

@A300-600
SERVICE BULLETIN
or
1 Bolt NSA5356-9-40 Item 2
or
1 Bolt NSA5358-9-40 Item 2
Hole B :
1 Nut NAS1727-9E Item 1
or
1 Nut ASNA2532-9 Item 1
1 Washer NSA5369PD916B Item 3
or
1 Washer NSA5368PD916B Item 3
1 Bolt ASNA2026T9-32 Item 4
or
1 Bolt NSA5356-9-32 Item 4
or
1 Bolt NSA5358-9-32 Item 4
NOTE
: Only install the washer Item 3 if you found a washer
during the removal procedure.
Hole C :
1 Nut NAS1727-8E Item 5
or
1 Nut ASNA2532-8 Item 5
1 Washer NSA5369PD816D Item 6
or
1 Washer NSA5368PD816D Item 6
1 Bolt ASNA2026T8-32 Item 7
or
1 Bolt NSA5356-8-32 Item 7
or
1 Bolt NSA5358-8-32 Item 7
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 38
5
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### Page 47

@A300-600
SERVICE BULLETIN
NOTE
: Only install the washer Item 6 if you found a washer
during the removal procedure.
Hole D :
1 Nut NAS1727-9E Item 1
or
1 Nut ASNA2532-9 Item 1
1 Washer NSA5369PD916B Item 3
or
1 Washer NSA5368PD916B Item 3
1 Bolt ASNA2026T9-30 Item 8
or
1 Bolt NSA5356-9-30 Item 8
or
1 Bolt NSA5358-9-30 Item 8
NOTE
: Only install the washer Item 3 if you found a washer
during the removal procedure.
Hole E :
1 Nut NAS1727-8E Item 5
or
1 Nut ASNA2532-8 Item 5
1 Washer NSA5369PD816D Item 6
or
1 Washer NSA5368PD816D Item 6
1 Bolt ASNA2026T8-27 Item 9
or
1 Bolt NSA5356-8-27 Item 9
or
1 Bolt NSA5358-8-27 Item 9
NOTE
: Only install the washer Item 6 if you found a washer
during the removal procedure.
Hole F :
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 39
5
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### Page 48

@A300-600
SERVICE BULLETIN
1 Nut NAS1727-8E Item 5
or
1 Nut ASNA2532-8 Item 5
1 Washer NSA5369PD816B Item 10
or
1 Washer NSA5368PD816B Item 10
or
1 Washer NSA5369PD816D Item 6
or
1 Washer NSA5368PD816D Item 6
1 Bolt ASNA2026T8-36 Item 11
or
1 Bolt NSA5356-8-36 Item 11
or
1 Bolt NSA5358-8-36 Item 11
NOTE
: Only install the washer Item 6 or Item 10 if you found a
washer during the removal procedure.
Hole G :
1 Nut NAS1726-8E Item 13
or
1 Nut ASNA2531-8 Item 13
1 Washer NSA5369PD816B Item 10
or
1 Washer NSA5368PD816B Item 10
1 Bolt ASNA2026T8-38 Item 12
or
1 Bolt NSA5356-8-38 Item 12
or
1 Bolt NSA5358-8-38 Item 12
NOTE
: Only install the washer Item 10 if you found a washer
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 40
5
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### Page 49

@A300-600
SERVICE BULLETIN
during the removal procedure.
Hole P :
1 Nut NAS1727-9E Item 1
or
1 Nut ASNA2532-9 Item 1
1 Bolt ASNA2026T9-42 Item 15
or
1 Bolt NSA5356-9-42 Item 15
or
1 Bolt NSA5358-9-42 Item 15
Hole Q :
1 Nut NAS1727-10E Item 16
or
1 Nut ASNA2532-10 Item 16
1 Bolt ASNA2026T10-44 Item 17
or
1 Bolt NSA5356-10-44 Item 17
or
1 Bolt NSA5358-10-44 Item 17
Hole S :
1 Nut NAS1727-10E Item 16
or
1 Nut ASNA2532-10 Item 16
1 Bolt ASNA2026T10-47 Item 18
or
1 Bolt NSA5356-10-47 Item 18
or
1 Bolt NSA5358-10-47 Item 18
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 41
5
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### Page 50

@A300-600
SERVICE BULLETIN
b
 Apply
Fuel Tank Sealant
Polysulfide
09-001 As required
to the fasteners of the holes A, B, C, D, E, F, G, P, Q and S.
c
 Do the subsequent inspections at the intervals given in Accomplishment
Timescale Table 2.
(g) Upload the completed Inspection Report sheet given in Appendix 01 in accordance
with ISI 00.00.00179 through the SB Reporting application in AirbusWorld.
(3) Subtask 576086-832-006-001 - Do an inspection of the hole T (adjacent to the hole
G), at the LH internal angle of the center wing box
Work Zones and Access Panels
Zone
 Access/Work location
140
 Work location
 Frame 47
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 AIRFRAME
Material necessary to do the job
Kit 576086A01R05
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
5
 ASNA2532-8
 1
 Nut
5
 NAS1727-8E
 1
 Nut
6
 NSA5368PD816D
 1
 Washer
6
 NSA5369PD816D
 1
 Washer
19
 ASNA2027T8-26
 1
 Bolt
19
 NSA5357-8-24
 1
 Bolt
19
 NSA5359-8-24
 1
 Bolt
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Fuel Tank Sealant
Polysulfide
09-001
 As required
Solvent
 11-026
 As required
References
Aircraft Maintenance Manual (AMM)
 20-21-12, Page Block 001
Non Destructive Test Manual (NTM)
 57-10-11
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 42
5
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### Page 51

@A300-600
SERVICE BULLETIN
References
Service Bulletin (SB)
 A300-57-6113
Structural Repair Manual (SRM)
 51-40-20
51-40-30
Fig. A-FBAAA
Inspection of the Holes A, B, C, D, E, F,
G, P, Q, S and T (adjacent to the Hole
G), at LH and RH Internal Angle of the
Center Wing Box
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Fig. A-FFBAA
Flowchart
Sheet 01
NOTE
: Remove partially the vapor seal in order to access to the area to be
inspected.
(a) Do an inspection of the hole T (adjacent to the hole G), at the LH internal angle of
the center wing box
refer to Fig. A-FBAAA
 and Fig. A-FFBAA
NOTE
: Only do this inspection if you found a crack in the hole G.
(b) Remove the sealant around the fasteners.
(c) Remove the fastener from the hole T (adjacent to the hole G) (Item (19)).
In accordance with SRM 51-40-20
(d) Clean the hole with
Solvent 11-026 As required
(e) Measure the diameter of the hole (nominal diameter, R1 oversize or R2 oversize).
(f) Do a rotating probe inspection
(Refer to NTM 57-10-11, Part 6)
1
 Crack found
a
 Contact AIRBUS and follow their instructions before next flight.
2
 No crack found
Accomplish Service Bulletin No. A300-57-6113 and no further action in
accordance with this Service Bulletin.
or
Install the new nominal, R1 oversize or R2 oversize fasteners in relation to the
removed fasteners and the initial hole diameter measured in step (e) of this
subtask.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 43
5
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### Page 52

@A300-600
SERVICE BULLETIN
a
 Install in the hole T (adjacent to the hole G) :
In accordance with SRM 51-40-20 and SRM 51-40-30
Refer to AMM 20-21-12, Page Block 001
1 Nut NAS1727-8E Item 5
or
1 Nut ASNA2532-8 Item 5
1 Washer NSA5369PD816D Item 6
or
1 Washer NSA5368PD816D Item 6
1 Bolt ASNA2027T8-26 Item 19
or
1 Bolt NSA5357-8-24 Item 19
or
1 Bolt NSA5359-8-24 Item 19
NOTE
: Only install the washer Item 6 if you found a washer
during the removal procedure.
b
 Apply
Fuel Tank Sealant
Polysulfide
09-001 As required
to the fastener adjacent to the fastener of the hole G.
c
 Do the subsequent inspections at the intervals given in Accomplishment
Timescale Table 2.
(g) Upload the completed Inspection Report sheet given in Appendix 01 in accordance
with ISI 00.00.00179 through the SB Reporting application in AirbusWorld.
(4) Subtask 576086-832-007-001 - Do an inspection of the hole T (adjacent to the hole
G), at the RH internal angle of the center wing box
Work Zones and Access Panels
Zone
 Access/Work location
140
 Work location
 Frame 47
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 44
5
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### Page 53

@A300-600
SERVICE BULLETIN
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 AIRFRAME
Material necessary to do the job
Kit 576086A01R05
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
5
 ASNA2532-8
 1
 Nut
5
 NAS1727-8E
 1
 Nut
6
 NSA5368PD816D
 1
 Washer
6
 NSA5369PD816D
 1
 Washer
19
 ASNA2027T8-26
 1
 Bolt
19
 NSA5357-8-24
 1
 Bolt
19
 NSA5359-8-24
 1
 Bolt
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Fuel Tank Sealant
Polysulfide
09-001
 As required
Solvent
 11-026
 As required
References
Aircraft Maintenance Manual (AMM)
 20-21-12, Page Block 001
Non Destructive Test Manual (NTM)
 57-10-11
Service Bulletin (SB)
 A300-57-6113
Structural Repair Manual (SRM)
 51-40-20
51-40-30
Fig. A-FBAAA
Inspection of the Holes A, B, C, D, E, F,
G, P, Q, S and T (adjacent to the Hole
G), at LH and RH Internal Angle of the
Center Wing Box
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Fig. A-FFBAA
Flowchart
Sheet 01
NOTE
: Remove partially the vapor seal in order to access to the area to be
inspected.
(a) Do an inspection of the hole T (adjacent to the hole G), at the RH internal angle of
the center wing box
refer to Fig. A-FBAAA
 and Fig. A-FFBAA
NOTE
: Only do this inspection if you found a crack in the hole G.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 45
5
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### Page 54

@A300-600
SERVICE BULLETIN
(b) Remove the sealant around the fasteners.
(c) Remove the fastener from the hole T (adjacent to the hole G) (Item (19)).
In accordance with SRM 51-40-20
(d) Clean the hole with
Solvent 11-026 As required
(e) Measure the diameter of the hole (nominal diameter, R1 oversize or R2 oversize).
(f) Do a rotating probe inspection
(Refer to NTM 57-10-11, Part 6)
1
 Crack found
a
 Contact AIRBUS and follow their instructions before next flight.
2
 No crack found
Accomplish Service Bulletin No. A300-57-6113 and no further action in
accordance with this Service Bulletin.
or
Install the new nominal, R1 oversize or R2 oversize fasteners in relation to the
removed fasteners and the initial hole diameter measured in step (e) of this
subtask.
a
 Install in the hole T (adjacent to the hole G) :
In accordance with SRM 51-40-20 and SRM 51-40-30
Refer to AMM 20-21-12, Page Block 001
1 Nut NAS1727-8E Item 5
or
1 Nut ASNA2532-8 Item 5
1 Washer NSA5369PD816D Item 6
or
1 Washer NSA5368PD816D Item 6
1 Bolt ASNA2027T8-26 Item 19
or
1 Bolt NSA5357-8-24 Item 19
or
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 46
5
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### Page 55

@A300-600
SERVICE BULLETIN
1 Bolt NSA5359-8-24 Item 19
NOTE
: Only install the washer Item 6 if you found a washer
during the removal procedure.
b
 Apply
Fuel Tank Sealant
Polysulfide
09-001 As required
to the fastener adjacent to the fastener of the hole G.
c
 Do the subsequent inspections at the intervals given in Accomplishment
Timescale Table 2.
(g) Upload the completed Inspection Report sheet given in Appendix 01 in accordance
with ISI 00.00.00179 through the SB Reporting application in AirbusWorld.
(5) Subtask 576086-832-008-001 - Do an ultrasonic inspection of the holes type 1, type
2 and type 3, at the LH aft bottom panel of the center wing box
Work Zones and Access Panels
Zone
 Access/Work location
140
 Work location
 Frame 47
Manpower Resources
Manhours
 2.00
Minimum number of person
 1
Subtask elapsed time
 2.00
Skills
 AIRFRAME
References
Non Destructive Test Manual (NTM)
 57-10-45
Service Bulletin (SB)
 A300-57-6113
Fig. A-FCAAA
Ultrasonic Inspection of the Holes type
1, type 2 and type 3.
Sheet 01
Fig. A-FFBAA
Flowchart
Sheet 01
(a) Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the LH aft
bottom panel of the center wing box (Refer to NTM 57-10-45).
refer to Fig. A-FFBAA Sheet 01
 and Fig. A-FCAAA Sheet 01
 .
1
 Crack found
a
 Contact AIRBUS before the next flight.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 47
5
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### Page 56

@A300-600
SERVICE BULLETIN
2
 No crack found
a
 Do the subsequent inspections at the intervals given in Accomplishment
Timescale Table 1.
or
b
 Accomplish Service Bulletin No. A300-57-6113.
c
 No further action in accordance with this Service Bulletin.
(b) Upload the completed Inspection Report sheet given in Appendix 01 in accordance
with ISI 00.00.00179 through the SB Reporting application in AirbusWorld.
(6) Subtask 576086-832-009-001 - Do an ultrasonic inspection of the holes type 1, type
2 and type 3, at the RH aft bottom panel of the center wing box
Work Zones and Access Panels
Zone
 Access/Work location
140
 Work location
 Frame 47
Manpower Resources
Manhours
 2.00
Minimum number of person
 1
Subtask elapsed time
 2.00
Skills
 AIRFRAME
References
Non Destructive Test Manual (NTM)
 57-10-45
Service Bulletin (SB)
 A300-57-6113
Fig. A-FCAAA
Ultrasonic Inspection of the Holes type
1, type 2 and type 3.
Sheet 01
Fig. A-FFBAA
Flowchart
Sheet 01
(a) Do an ultrasonic inspection of the holes type 1, type 2 and type 3, at the RH aft
bottom panel of the center wing box (Refer to NTM 57-10-45).
refer to Fig. A-FFBAA Sheet 01
 and Fig. A-FCAAA Sheet 01
 .
1
 Crack found
a
 Contact AIRBUS before the next flight.
2
 No crack found
a
 Do the subsequent inspections at the intervals given in Accomplishment
Timescale Table 1.
or
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 48
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### Page 57

@A300-600
SERVICE BULLETIN
b
 Accomplish Service Bulletin No. A300-57-6113.
c
 No further action in accordance with this Service Bulletin.
(b) Upload the completed Inspection Report sheet given in Appendix 01 in accordance
with ISI 00.00.00179 through the SB Reporting application in AirbusWorld.
**CONF 002
(1) Subtask 576086-832-004-002 - Do an inspection of the holes A, B, C, D, E, F, G, P,
Q and S, at the LH internal angle of the center wing box
Work Zones and Access Panels
Zone
 Access/Work location
140
 Work location
 Frame 47
Manpower Resources
Manhours
 4.00
Minimum number of person
 1
Subtask elapsed time
 4.00
Skills
 AIRFRAME
Material necessary to do the job
Kit 576086A02R02
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 ASNA2532-9
 4
 Nut
1
 NAS1727-9E
 4
 Nut
2
 NSA5358-9-40
 1
 Bolt
3
 NSA5368PD916B
 2
 Washer
4
 NSA5358-9-32
 1
 Bolt
5
 ASNA2532-8
 3
 Nut
5
 NAS1727-8E
 3
 Nut
6
 NSA5368PD816D
 3
 Washer
7
 NSA5358-8-32
 1
 Bolt
8
 NSA5358-9-30
 1
 Bolt
9
 NSA5358-8-27
 1
 Bolt
10
 NSA5368PD816B
 2
 Washer
11
 NSA5358-8-36
 1
 Bolt
12
 NSA5358-8-38
 1
 Bolt
13
 ASNA2531-8
 1
 Nut
13
 NAS1726-8E
 1
 Nut
15
 NSA5358-9-42
 1
 Bolt
16
 ASNA2532-10
 2
 Nut
16
 NAS1727-10E
 2
 Nut
17
 NSA5358-10-44
 1
 Bolt
18
 NSA5358-10-47
 1
 Bolt
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 49
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### Page 58

@A300-600
SERVICE BULLETIN
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Fuel Tank Sealant
Polysulfide
09-001
 As required
Solvent
 11-026
 As required
References
Aircraft Maintenance Manual (AMM)
 20-21-12, Page Block 001
Non Destructive Test Manual (NTM)
 57-10-11
Service Bulletin (SB)
 A300-57-6113
Structural Repair Manual (SRM)
 51-40-20
51-40-30
Fig. A-FBAAA
Inspection of the Holes A, B, C, D, E, F,
G, P, Q, S and T (adjacent to the Hole
G), at LH and RH Internal Angle of the
Center Wing Box
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Fig. A-FFBAB
Flowchart
Sheet 01
(a) Do an inspection of the holes A, B, C, D, E, F, G, P, Q and S, at the LH internal
angle of the center wing box
Refer to Fig. A-FBAAA
 and Fig. A-FFBAB
(b) Remove the sealant around the fasteners.
(c) Remove the fasteners from the holes A, B, C, D, E, F, G, P, Q and S (Items (1)
thru (18)).
In accordance with SRM 51-40-20
(d) Clean the holes with
Solvent 11-026 As required
(e) Measure the diameter of the R2 oversize holes.
(f) Do a rotating probe inspection
(Refer to NTM 57-10-11, Part 6)
1
 Crack found
a
 If crack found in hole G do SUBTASK 576086-832-006 002 Do an
inspection of the hole T (adjacent to the hole G), at the LH internal angle
of the center wing box .
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 50
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### Page 59

@A300-600
SERVICE BULLETIN
b
 Contact AIRBUS and follow their instructions before the next flight.
NOTE
: Depending on crack finding, please be informed
that modification Service Bulletin No. A300-57-6113
accomplishment could be required by AIRBUS before
next flight.
2
 No crack found
Accomplish Service Bulletin No. A300-57-6113 and no further action in
accordance with this Service Bulletin.
or
Install the new R2 oversize fasteners in relation to the removed fasteners
In accordance with SRM 51-40-20 and SRM 51-40-30
Refer to AMM 20-21-12, Page Block 001
a
 Install :
Hole A :
1 Nut NAS1727-9E Item 1
or
1 Nut ASNA2532-9 Item 1
1 Bolt NSA5358-9-40 Item 2
Hole B :
1 Nut NAS1727-9E Item 1
or
1 Nut ASNA2532-9 Item 1
1 Washer NSA5368PD916B Item 3
1 Bolt NSA5358-9-32 Item 4
NOTE
: Only install the washer Item 3 if you found a washer
during the removal procedure.
Hole C :
1 Nut NAS1727-8E Item 5
or
1 Nut ASNA2532-8 Item 5
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 51
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### Page 60

@A300-600
SERVICE BULLETIN
1 Washer NSA5368PD816D Item 6
1 Bolt NSA5358-8-32 Item 7
NOTE
: Only install the washer Item 6 if you found a washer
during the removal procedure.
Hole D :
1 Nut NAS1727-9E Item 1
or
1 Nut ASNA2532-9 Item 1
1 Washer NSA5368PD916B Item 3
1 Bolt NSA5358-9-30 Item 8
NOTE
: Only install the washer Item 3 if you found a washer
during the removal procedure.
Hole E :
1 Nut NAS1727-8E Item 5
or
1 Nut ASNA2532-8 Item 5
1 Washer NSA5368PD816D Item 6
1 Bolt NSA5358-8-27 Item 9
NOTE
: Only install the washer Item 6 if you found a washer
during the removal procedure.
Hole F :
1 Nut NAS1727-8E Item 5
or
1 Nut ASNA2532-8 Item 5
1 Washer NSA5368PD816B Item 10
or
1 Washer NSA5368PD816D Item 6
1 Bolt NSA5358-8-36 Item 11
NOTE
: Only install the washer Item 6 or Item 10 if you found a
washer during the removal procedure.
DATE: Jun 06/00 SERVICE BULLETIN No.: A300-57-6086
REVISION No.: 07 - Mar 26/18 Page: 52
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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