# Airbus Service Bulletin 53-6179

Copy: No revision named ("FAA-2016-5596_SB_53_6179"), 43 pages: PDF https://openairdocs.org/files/sha256/f2/95/f2958f240a9b9db923a3f8fc9bd1042ca92476673f2bdf38d1e33255f91e6169; text https://openairdocs.org/service-documents/airbus/sb-53-6179/file/f2958f240a9b.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-5596, the docket of AD 2016-20-11. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: 53-6179
- Page: https://openairdocs.org/service-documents/airbus/sb-53-6179

## Text (43 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-5596, the docket of AD 2016-20-11. Not covered by OpenAirDocs’ CC0 dedication. Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

@A300-600
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: 53
TITLE: FUSELAGE - REAR FUSELAGE - INSPECTION OF AFT CARGO DOOR
LOWER TORSION BOX AREA
**CONF ALL
MODIFICATIONS
None
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
Several cracks have been found on the AFT cargo door of an A300-600 aircraft during maintenance.
The cracks have been found on:
- The door sill beam web
- The door sill beam flags
- The lock fittings
- The torsion box plates.
A stress analysis has shown that there is no dedicated fatigue scheduled maintenance task to monitor
the affected areas. Therefore AIRBUS have decided to develop a dedicated inspection for the affected
areas.
This Service Bulletin details the procedures to inspect
- The door sill beam web
- The door sill beam flags
- The lock fittings
- The torsion box plates.
for potential cracks. Different inspection pr ocedures are detailed in this Service Bulletin:
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 2

@A300-600
SERVICE BULLETIN
SUMMARY
- Detailed Inspection (DET)
- Ultrasonic (US) Inspection
- High Frequency Eddy Current (HFEC) Inspection.
The accomplishment of this Service Bulletin will contribute to detect potential cracks in the door sill
beam area of the AFT cargo door.
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
NOTE
 (1)
: Service Bulletin must be accomplished.
MATERIAL PRICE INFORMATION
No Material
EFFECTIVITY
This Service Bulletin is applicable to this (these) operator(s) :
06P 67Q ABR AHK BCS F2I FDX IRA IRM KAC MNB MRJ MSR
SUD TAR THA UQA URS UTP UZB
CONCURRENT REQUIREMENTS
None
REFERENCES / REPERCUSSIONS
TFU
 None
OEB
 None
AOT
 A53W005-14
SIL
 None
LINE MAINTENANCE AFFECTED
 No
LIFE LIMIT
 None
OTHER
 TFU 53.17.00.006
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
HARD
 NO
SOFT
 NO
OBRM
 NO
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 3

@A300-600
SERVICE BULLETIN
SUMMARY
MANPOWER
Task 536179-832-848-001: Inspection
TOTAL MANHOURS
 11.50
ELAPSED TIME (HOURS)
 11.50
Task 536179-832-849-001: Inspection
TOTAL MANHOURS
 11.50
ELAPSED TIME (HOURS)
 11.50
APPENDICES
Appendix 01 - Technical Disposition
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 3
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 4

@A300-600
SERVICE BULLETIN
SUMMARY
**CONF ALL
Z150
A
A
AREA TO BE INSPECTED
STGR27RH
STGR44RH
FR59A
FR60
FR61
FR62
FR63
STGR46RH
D_SB_536179_6_SAAA_01_02
Figure A-G SAAA - S heet 01
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 4
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 5

@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: 53
TITLE: FUSELAGE - REAR FUSELAGE - INSPECTION OF AFT CARGO DOOR
LOWER TORSION BOX AREA
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
(1) Models
B4-603 B4-605R B4-622 B4-622R C4-605R/F F4-605R
(2) Effectivity by MSN
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 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 0673 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
0836-0838
(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: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 6

@A300-600
SERVICE BULLETIN
OPERATOR
 MSN
06P
 0788
67Q
 0584 0603 0744 0749 0764
ABR
 0677 0743
AHK
 0683 0770
BCS
 0602 0617 0621 0637 0641 0670 0679 0703 0711 0724 0729 0730
0737 0740 0753 0783 0797 0836 0837
F2I
 0529 0557
FDX
 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
 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701 0773
0838
KAC
 0673 0694 0699 0719 0721
MNB
 0521 0525 0532 0734 0739 0755 0756 0758
MRJ
 0750 0762
MSR
 0561 0607
SUD
 0666 0775
TAR
 0505 0558 0563
THA
 0629 0782 0784 0785 0786 0787
UQA
 0626 0643
URS
 0733
UTP
 0707 0725 0732 0741 0746 0754 0763
UZB
 0717 0722
(4) Configuration by MSN
MSN
 CONFIGURATION
0388 0401 0405 0408 0411 0414 0417 0477 0479 0505 0521
0525 0529 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
0673 0677 0679 0683 0688 0694 0696 0699 0701 0703 0707
0709 0711 0713 0715 0717 0719 0721 0722 0723 0724 0725
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 0836 0837 0838
001
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 7

@A300-600
SERVICE BULLETIN
(5) Configuration definition
**CONF 001
Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a
standard configuration.
(6) Material Effectivity
MATERIAL
 QTY PER A/C
 SEE NOTES
Consumable CMLD01
 1
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
Several cracks have been found on the AFT cargo door of an A300-600 aircraft during
maintenance. The cracks have been found on:
- The door sill beam web
- The door sill beam flags
- The lock fittings
- The torsion box plates.
A stress analysis has shown that there is no dedicated fatigue scheduled maintenance
task to monitor the affected areas. Therefore AIRBUS have decided to develop a
dedicated inspection for the affected areas.
(2) Objective/Action
This Service Bulletin details the procedures to inspect
- The door sill beam web
- The door sill beam flags
- The lock fittings
- The torsion box plates.
for potential cracks. Different inspection pr ocedures are detailed in this Service Bulletin:
- Detailed Inspection (DET)
- Ultrasonic (US) Inspection
- High Frequency Eddy Current (HFEC) Inspection.
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 3
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 8

@A300-600
SERVICE BULLETIN
(3) Advantages
The accomplishment of this Service Bulletin will contribute to detect potential cracks in
the door sill beam area of the AFT cargo door.
(4) Operational/Maintenance Consequences
None
D. DESCRIPTION
To accomplish this Service Bulletin it is necessary to :
Task 536179-832-848-001: Inspection
(1) Inspect the AFT Cargo Door Sill Beam Area on Aircraft, which have embodied Mod.
5438, but not Mod. 12046, and are not affected by the AOT A53W005-14-01
Task 536179-832-849-001: Inspection
(1) Inspect the AFT Cargo Door Sill Beam Area on Aircraft, which have embodied Mod.
5438, but not Mod. 12046, and are affected by the AOT A53W005-14-01
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
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
intervals given but reference should be made to the AD for confirmation of the mandated
accomplishment timescale.
Table 1, Config. 001 - Inspection of the sill beam - Aircraft not affected by AOT A53W005-14-01
COMPLIANCE TIME
CONDITION
 ACTION
THRESHOLD
 GRACE PERIOD
REPETITIVE
INTERVAL NOT
TO EXCEED
All aircraft not
impacted by the
AOT
HFEC inspection
 13000 FC from
aircraft first flight
2000 FC from
original SB issue
4600 FC
Crack found
 Contact AIRBUS
 Before next flight
 None
 None
Table 2, Config. 001 - Inspection of the sill beam - Aircraft affected by AOT A53W005-14-01
COMPLIANCE TIME
CONDITION
 ACTION
THRESHOLD
 GRACE PERIOD
REPETITIVE
INTERVAL NOT
TO EXCEED
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 4
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 9

@A300-600
SERVICE BULLETIN
All aircraft on
which the HFEC
inspection has
been accomplished
HFEC inspection
 None
 None
 4600 FC from last
HFEC inspection
Crack found
 Contact AIRBUS
 Before next flight
 None
 None
DET or US
inspection
18000 FC from
aircraft first flight
275 FC from
original AOT issue
275 FC until first
HFEC inspection
(within 2000 FC
from original SB
issue)
and
Aircraft identified
as Batch 2 in the
AOT and on which
the HFEC
inspection has not
been accomplished
HFEC inspection
 18000 FC from
aircraft first flight
2000 FC from
original SB issue
4600 FC
Crack found
 Contact AIRBUS
 Before next flight
 None
 None
DET or US
inspection
30000 FC from
aircraft first flight
50 FC from original
AOT issue
275 FC until first
HFEC inspection
(within 2000 FC
from original SB
issue)
and
Aircraft identified
as Batch 1 in the
AOT and on which
the HFEC
inspection has not
been accomplished
in accordance with
the AOT
 HFEC inspection
 30000 FC from
aircraft first flight
2000 FC from
original SB issue
4600 FC
Crack found
 Contact AIRBUS
 Before next flight
 None
 None
F. APPROVAL
The technical content of this document is approved under the authority of Design
Organisation Approv al No. EASA. 21J.031.
If an aircraft listed in the effectivity has a modification or repair embodied that is not of
AIRBUS origin, and which affects the content of this Service Bulletin, the operator is
responsible for obtaining approval by its airworthiness authority for any adaptation necessary
before incorporation of the Service Bulletin.
G. MANPOWER
The manpower estimates given in this Service Bulletin are based on the direct 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.
Task 536179-832-848-001: Inspection
Get Access
 3.50
On Aircraft
Inspect the AFT Cargo Door Sill Beam Area on
Aircraft, which have embodied Mod. 5438, but not
Mod. 12046, and are not affected by the AOT
A53W005-14-01
4.50
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 5
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 10

@A300-600
SERVICE BULLETIN
Task 536179-832-848-001: Inspection
Close-Up
 3.50
TOTAL MANHOURS
 11.50
ELAPSED TIME (HOURS)
 11.50
Task 536179-832-849-001: Inspection
Get Access
 3.50
On Aircraft
Inspect the AFT Cargo Door Sill Beam Area on
Aircraft, which have embodied Mod. 5438, but not
Mod. 12046, and are affected by the AOT
A53W005-14-01
4.50
Close-Up
 3.50
TOTAL MANHOURS
 11.50
ELAPSED TIME (HOURS)
 11.50
H. WEIGHT AND BALANCE
Not Changed
I. ELECTRICAL LOAD DATA
Not Changed
J. REFERENCES
Aircraft Maintenance Manual (AMM)
 06-21-00 06-31-53 24-00-00
25-52-22 25-52-26 25-52-41
52-30-00
All Operators Telex (AOT)
 A53W005-14-01
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
Non Destructive Test Manual (NTM)
 53-17-33
Structural Repair Manual (SRM)
 51-76-10
K. PUBLICATION AFFECTED
Maintenance Planning Document (MPD)
 531725-01-2
L. INTERCHANGEABILITY/MIXABILITY
Not Applicable
M. SPARES
None
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 6
6
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### Page 11

@A300-600
SERVICE BULLETIN
2. MATERIAL INFORMATION
**CONF ALL
A. MATERIAL - PRICE AND AVAILABILITY
None
B. INDUSTRY SUPPORT INFORMATION
AIRBUS will not provide industry support for accomplishment of this Service Bulletin.
C. LIST OF COMPONENTS
No Kit
D. LIST OF MATERIALS - OPERATOR SUPPLIED
(1) Consumable Materials
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
Non Aqueous Cleaner-General
 08BAA9
 As required
Textile-Lint Free Cotton -
 14SBA1
 As required
(2) Components
None
(3) Equipment
None
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
F. TOOLING
None
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 7
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 12

@A300-600
SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 8
6
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### Page 13

@A300-600
SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS
Task 536179-832-848-001 - Inspection
WARNING
: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
CAUTION
: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP
ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY
AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE
WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,
COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO
THIS:
PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS
NECESSARY ON WIRING AND COMPONENTS.
REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER
CONTAMINATION.
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION
AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.
IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.
NOTE
: The accomplishment instructions of this Service Bulletin refer to procedures
included in other AIRBUS documents. When the words ’refer to’ are used and the
operator has a procedure accepted by the local procedure 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
: The purpose of flow charts 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.
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
the aircraft can be put back into a serviceable condition.
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 9
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 14

@A300-600
SERVICE BULLETIN
Task Associated Data
Manpower
TOTAL MANHOURS
 11.50
ELAPSED TIME (HOURS)
 11.50
A. GENERAL
(1) Subtask 536179-910-201-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-21-00, Page Block 001
06-31-53, Page Block 001
Consumable Material List (CML)
(a) For the identification of zones, refer to AMM 06-21-00, Page Block 001.
(b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.
(c) For the material specification (Mat No.) given in this Service Bulletin, refer to
Consumable Material List (CML).
(2) Subtask 536179-839-201-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
B. PREPARATION
(1) Subtask 536179-941-201-001 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 24-00-00, Page Block 301
25-52-22, Page Block 401
25-52-26, Page Block 401
25-52-41, Page Block 401
52-30-00, Page Block 001
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).
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 10
6
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### Page 15

@A300-600
SERVICE BULLETIN
- Engine shut down, thrust reversers closed and locked.
- Aircraft in clean configuration.
- Parking brake applied.
- Aircraft electrical network de-energized.
- Hydraulic systems 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) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page
Block 301.
(b) Put an access platform in position at the AFT Cargo Compartment Door.
(c) Open the AFT Cargo Compartment Door, refer to AMM 52-30-00, Page Block 001.
(d) Between Frame 60 and Frame 63, remove the ball mats as necessary, refer to
AMM 25-52-22, Page Block 401.
(e) Between Frame 60 and Frame 63, remove the door sill latches as necessary, refer
to AMM 25-52-41, Page Block 401.
(f) Between Frame 60 and Frame 63 remove the Power Drive Unit (PDU) as
necessary, refer to AMM 25-52-26, Page Block 401.
C. PROCEDURE
(1) Subtask 536179-200-201-001 - Inspect the AFT Cargo Door Sill Beam Area on
Aircraft, which have embodied Mod. 5438, but not Mod. 12046, and are not
affected by the AOT A53W005-14-01
Manpower Resources
Manhours
 4.50
Minimum number of person
 1
Subtask elapsed time
 4.50
Skills
 NON DESTRUCTIVE
TESTING
Material necessary to do the job
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Non Aqueous Cleaner-
General
08BAA9
 As required
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 11
6
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### Page 16

@A300-600
SERVICE BULLETIN
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Textile-Lint Free Cotton -
 14SBA1
 As required
References
All Operators Telex (AOT)
 A53W005-14-01
Non Destructive Test Manual (NTM)
 53-17-33, Page Block 601
Structural Repair Manual (SRM)
 51-76-10
Fig. A-GBBAA
Door sill beam flag, lock fitting and
torsion box plate inspection
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Sheet 07
Fig. A-GFAAA
Flow Chart
Sheet 01
Sheet 02
Fig. A-GRAAA
Report Sheet
Sheet 01
(a) Make sure that the whole inspection area is clean and smooth. If necessary clean
the area with:
Non Aqueous
Cleaner-General
08BAA9 As required
and
Textile-Lint Free
Cotton -
14SBA1 As required
(b) Inspect the door sill beam area on aircraft which are not affected by the Alert
Operators Transmission A53W005-14-01, refer to Flow Chart Fig. A-GFAAA Sheet
01
.
1
 Inspect the radius and the splicing zone of the door sill beam flags.
a
 On the door sill beam flags between Frame 60 and Frame 63, do the
HFEC inspection in accordance with the accomplishment timescale given
in Para 1.E.(2):
<1> On Frame 60 and Frame 60A do the HFEC inspection as shown on
Fig. A-GBBAA Sheet 02
 and Fig. A-GBBAA Sheet 07
 ,V i e wK ,r e f e r
to NTM 53-17-33, Page Block 601.
<2> On Frame 61, Frame 61A and Frame 62, do the HFEC inspection
as shown on Fig. A-GBBAA Sheet 03
 and Fig. A-GBBAA Sheet 07
 ,
View K, refer to NTM 53-17-33, Page Block 601.
<3> On Frame 62A and Frame 63, do the HFEC inspection as shown on
Fig. A-GBBAA Sheet 04
 and Fig. A-GBBAA Sheet 07
 ,V i e wK ,r e f e r
to NTM 53-17-33, Page Block 601.
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 12
6
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@A300-600
SERVICE BULLETIN
b
 If no cracks have been detected, repeat the inspections in accordance
with the accomplishment timescale, given in Para 1.E.(2).
c
 If a crack has been detected, contact AIRBUS for repair instruction
before next flight. Use the report sheet Fig. A-GRAAA Sheet 01
 .
2
 Inspect the radius and the splicing zone of the lock fittings and torsion box
plates at STGR45RH.
a
 On the lock fittings and the torsion box plates between Frame 60
and Frame 63, do the HFEC inspection in accordance with the
accomplishment timescale given in Para 1.E.(2):
<1> On Frame 60, Frame 61, Frame 62 and Frame 63, do the HFEC
inspection as shown on Fig. A-GBBAA Sheet 05
 , View F and View
G, refer to NTM 53-17-33, Page Block 601.
<2> On Frame 60A, Frame 61A and Frame 62A, do the HFEC
inspection as shown on Fig. A-GBBAA Sheet 06
 , View H and View
J, refer to NTM 53-17-33, Page Block 601.
b
 If no cracks have been detected, repeat the inspections in accordance
with the accomplishment timescale, given in Para 1.E.(2).
c
 If a crack has been detected, contact AIRBUS for repair instruction
before next flight. Use the report sheet Fig. A-GRAAA Sheet 01
 .
D. TEST
None
E. CLOSE-UP
(1) Subtask 536179-942-201-001 - Close-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 25-52-22, Page Block 401
25-52-26, Page Block 401
25-52-41, Page Block 401
52-30-00, Page Block 001
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(b) Install the PDU, refer to AMM 25-52-26, Page Block 401.
(c) Install the door sill latches, refer to AMM 25-52-41, Page Block 401.
(d) Install the ball mats, refer to AMM 25-52-22, Page Block 401.
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 13
6
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@A300-600
SERVICE BULLETIN
(e) Close the cargo compartment door, refer to AMM 52-30-00, Page Block 001.
(f) Remove the access platform(s).
(g) Put the aircraft back to its initial configuration.
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 14
6
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### Page 19

@A300-600
SERVICE BULLETIN
Task 536179-832-849-001 - Inspection
WARNING
: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
CAUTION
: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP
ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY
AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE
WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,
COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO
THIS:
PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS
NECESSARY ON WIRING AND COMPONENTS.
REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER
CONTAMINATION.
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION
AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.
IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.
NOTE
: The accomplishment instructions of this Service Bulletin refer to procedures
included in other AIRBUS documents. When the words ’refer to’ are used and the
operator has a procedure accepted by the local procedure 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
: The purpose of flow charts 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.
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
the aircraft can be put back into a serviceable condition.
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 15
6
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@A300-600
SERVICE BULLETIN
Task Associated Data
Manpower
TOTAL MANHOURS
 11.50
ELAPSED TIME (HOURS)
 11.50
A. GENERAL
(1) Subtask 536179-910-202-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-21-00, Page Block 001
06-31-53, Page Block 001
Consumable Material List (CML)
(a) For the identification of zones, refer to AMM 06-21-00, Page Block 001.
(b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.
(c) For the material specification (Mat No.) given in this Service Bulletin, refer to
Consumable Material List (CML).
(2) Subtask 536179-839-202-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
B. PREPARATION
(1) Subtask 536179-941-202-001 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 24-00-00, Page Block 301
25-52-22, Page Block 401
25-52-26, Page Block 401
25-52-41, Page Block 401
52-30-00, Page Block 001
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).
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 16
6
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@A300-600
SERVICE BULLETIN
- Engine shut down, thrust reversers closed and locked.
- Aircraft in clean configuration.
- Parking brake applied.
- Aircraft electrical network de-energized.
- Hydraulic systems 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) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page
Block 301.
(b) Put an access platform in position at the AFT Cargo Compartment Door.
(c) Open the AFT Cargo Compartment Door, refer to AMM 52-30-00, Page Block 001.
(d) Between Frame 60 and Frame 63, remove the ball mats as necessary, refer to
AMM 25-52-22, Page Block 401.
(e) Between Frame 60 and Frame 63, remove the door sill latches as necessary, refer
to AMM 25-52-41, Page Block 401.
(f) Between Frame 60 and Frame 63 remove the Power Drive Unit (PDU) as
necessary, refer to AMM 25-52-26, Page Block 401.
C. PROCEDURE
(1) Subtask 536179-200-202-001 - Inspect the AFT Cargo Door Sill Beam Area on
Aircraft, which have embodied Mod. 5438, but not Mod. 12046, and are affected by
the AOT A53W005-14-01
Manpower Resources
Manhours
 4.50
Minimum number of person
 1
Subtask elapsed time
 4.50
Skills
 NON DESTRUCTIVE
TESTING
Material necessary to do the job
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Non Aqueous Cleaner-
General
08BAA9
 As required
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 17
6
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### Page 22

@A300-600
SERVICE BULLETIN
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Textile-Lint Free Cotton -
 14SBA1
 As required
References
All Operators Telex (AOT)
 A53W005-14-01
Non Destructive Test Manual (NTM)
 53-17-33, Page Block 401
53-17-33, Page Block 601
Structural Repair Manual (SRM)
 51-76-10
Fig. A-GBAAA
Door sill beam web inspection
Sheet 01
Sheet 02
Fig. A-GBBAA
Door sill beam flag, lock fitting and
torsion box plate inspection
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Sheet 07
Fig. A-GFAAA
Flow Chart
Sheet 01
Sheet 02
Fig. A-GRAAA
Report Sheet
Sheet 01
(a) Make sure that the whole inspection area is clean and smooth. If necessary clean
the area with:
Non Aqueous
Cleaner-General
08BAA9 As required
and
Textile-Lint Free
Cotton -
14SBA1 As required
(b) Inspect the door sill beam area on aircraft which are affected by the Alert Operators
Transmission A53W005-14-01, refer to Flow Chart Fig. A-GFAAA Sheet 02
 .
1
 Check if the HFEC inspection has been done in accordance with the Alert
Operators Transmission A53W005-14-01.
2
 If the HFEC inspection has not been done, inspect the door sill beam web
around the lock fitting attachments.
a
 On the door sill beam web around the lock fitting attachments between
Frame 60 and Frame 63 remove the sealant, refer to SRM 51-76-10.
b
 Clean the inspection area with:
Non Aqueous
Cleaner-General
08BAA9 As required
and
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 18
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### Page 23

@A300-600
SERVICE BULLETIN
Textile-Lint Free
Cotton -
14SBA1 As required
c
 Do an US inspection, refer to NTM 53-17-33, Page Block 401, on the
door sill beam web around the lock fitting attachments, as shown on Fig.
A-GBAAA Sheet 01
 and Fig. A-GBAAA Sheet 02
 , in accordance with the
accomplishment timescale, given in Para 1.E.(2).
<1> If no cracks have been detected, repeat the inspections in
accordance with the accomplishment timescale, given in Para
1.E.(2).
<2> If a crack has been detected, contact AIRBUS for repair instruction
before next flight. Use the report sheet Fig. A-GRAAA Sheet 01
 .
d
 Renew the sealant, refer to SRM 51-76-10.
3
 Inspect the radius and the splicing zone of the door sill beam flags between
Frame 60 and Frame 63.
a
 If the HFEC inspection has not been done, do a
DET, refer to the Technical Disposition TD/K4/T1/45810/2014, given in
Appendix 01 - Technical Disposition ,
and
HFEC inspection, refer to NTM 53-17-33, Page Block 601
as shown on Fig. A-GBBAA Sheet 01
 thru Fig. A-GBBAA Sheet 04
 and
Fig. A-GBBAA Sheet 07
 , View K, in accordance with the accomplishment
timescale given in Para 1.E.(2).
<1> If no cracks have been detected, repeat the inspections in
accordance with the accomplishment timescale, given in Para
1.E.(2).
<2> If a crack has been detected, contact AIRBUS for repair instruction
before next flight. Use the report sheet Fig. A-GRAAA Sheet 01
 .
b
 If the HFEC inspection has been done, repeat the HFEC inspection on
the sill beam flags between Frame 60 and Frame 63, as shown on Fig.
A-GBBAA Sheet 01
 thru Fig. A-GBBAA Sheet 04
 and Fig. A-GBBAA
Sheet 07
 , View K, in accordance with the accomplishment timescale,
given in Para 1.E.(2).
<1> If no cracks have been detected, repeat the inspections in
accordance with the accomplishment timescale, given in Para
1.E.(2).
<2> If a crack has been detected, contact AIRBUS for repair instruction
before next flight. Use the report sheet Fig. A-GRAAA Sheet 01
 .
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 19
6
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### Page 24

@A300-600
SERVICE BULLETIN
4
 Inspect the radius and the splicing zone of the lock fittings and torsion box
plate between Frame 60 and Frame 63 at STGR45RH.
a
 If the HFEC inspection has not been done, do a
DET, refer to the Technical Disposition TD/K4/T1/45810/2014, given in
Appendix 01 - Technical Disposition ,
and
HFEC inspection, refer to NTM 53-17-33, Page Block 601
as shown on Fig. A-GBBAA Sheet 05
 , View F and G, and Fig. A-GBBAA
Sheet 06
 , View H and J, in accordance with the accomplishment
timescale given in Para 1.E.(2).
<1> If no cracks have been detected, repeat the inspections in
accordance with the accomplishment timescale, given in Para
1.E.(2).
<2> If a crack has been detected, contact AIRBUS for repair instruction
before next flight. Use the report sheet Fig. A-GRAAA Sheet 01
 .
b
 If the HFEC inspection has been done, repeat the HFEC inspection on
the sill beam flags between Frame 60 and Frame 63 in accordance with
the accomplishment timescale, given in Para 1.E.(2):
<1> On Frame 60, Frame 61, Frame 62 and Frame 63, do the HFEC
inspection as shown on Fig. A-GBBAA Sheet 05
 ,V i e wFa n dG ,
refer to NTM 53-17-33, Page Block 601.
<2> On Frame 60A, Frame 61A and Frame 62A, do the HFEC
inspection as shown on Fig. Fig. A-GBBAA Sheet 06
 ,V i e wHa n dJ ,
refer to NTM 53-17-33, Page Block 601.
<3> If no cracks have been detected, repeat the inspections in
accordance with the accomplishment timescale, given in Para
1.E.(2).
<4> If a crack has been detected, contact AIRBUS for repair instruction
before next flight. Use the report sheet Fig. A-GRAAA Sheet 01
 .
D. TEST
None
E. CLOSE-UP
(1) Subtask 536179-942-202-001 - Close-up
Manpower Resources
Skills
 NON SPECIFIC
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 20
6
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### Page 25

@A300-600
SERVICE BULLETIN
References
Aircraft Maintenance Manual (AMM)
 25-52-22, Page Block 401
25-52-26, Page Block 401
25-52-41, Page Block 401
52-30-00, Page Block 001
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(b) Install the PDU, refer to AMM 25-52-26, Page Block 401.
(c) Install the door sill latches, refer to AMM 25-52-41, Page Block 401.
(d) Install the ball mats, refer to AMM 25-52-22, Page Block 401.
(e) Close the cargo compartment door, refer to AMM 52-30-00, Page Block 001.
(f) Remove the access platform(s).
(g) Put the aircraft back to its initial configuration.
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 21
6
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### Page 26

@A300-600
SERVICE BULLETIN
**CONF ALL
Z150
A
FR59A
FR63A
FR59A
FR60
FR60A
FR61
FR61A
FR62
FR62A
FR63
B A
C
C
C
C
C
C
C
B
DOOR SILL BEAM WEB
D_SB_536179_6_BAAA_01_00
Figure A-G BAAA - S heet 01
Door sill beam web inspection
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 22
6
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### Page 27

@A300-600
SERVICE BULLETIN
**CONF ALL
FWDC
FR
INSPECTION AREA
TYPICAL
LOCK FITTING
D_SB_536179_6_BAAA_02_00
Figure A-G BAAA - S heet 02
Door sill beam web inspection
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 23
6
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### Page 28

@A300-600
SERVICE BULLETIN
**CONF ALL
Z150
A
STGR27RH
STGR44RH
FR59A
FR60
FR61
FR62
FR63
B
STGR46RH
A
FR62
FR61
FR60
FR63
FR59A
FR60A
FR61A
FR62A
FR63A
B
C
D
E
STGR46RH
STGR43RH
D_SB_536179_6_BBAA_01_01
Figure A-G BBAA - S heet 01
Door sill beam flag, lock fitting and torsion box plate inspection
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 24
6
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### Page 29

@A300-600
SERVICE BULLETIN
**CONF ALL
STGR49RH
STGR46RH
DOOR SILL
BEAM FLAG
DOOR SILL
BEAM FLAG
LOCK
FITTING
FR60A
FR61
FR60
C
F
H
K
K
TORSION BOX
PLATE
D_SB_536179_6_BBAA_02_00
Figure A-G BBAA - S heet 02
Door sill beam flag, lock fitting and torsion box plate inspection
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 25
6
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### Page 30

@A300-600
SERVICE BULLETIN
**CONF ALL
STGR49RH
STGR46RH
DOOR SILL
BEAM FLAG
DOOR SILL
BEAM FLAG
DOOR SILL
BEAM FLAG
TORSION BOX
PLATE
LOCK
FITTING
LOCK
FITTING
FR61
FR61A
FR62
F
H
F
D
K
K
K
D_SB_536179_6_BBAA_03_00
Figure A-G BBAA - S heet 03
Door sill beam flag, lock fitting and torsion box plate inspection
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 26
6
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### Page 31

@A300-600
SERVICE BULLETIN
**CONF ALL
DOOR SILL
BEAM FLAG
DOOR SILL
BEAM FLAG
FR63
STGR49RH
STGR46RH
FR62A
TORSION BOX
PLATE
LOCK
FITTING
E
H
LOCK
FITTING
K
K
F
D_SB_536179_6_BBAA_04_00
Figure A-G BBAA - S heet 04
Door sill beam flag, lock fitting and torsion box plate inspection
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 27
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### Page 32

@A300-600
SERVICE BULLETIN
**CONF ALL
NOTE:
AREA TO BE INSPECTED
FR63
VIEW LOOKING AFT
FR62
FR61
G
F
G
STGR44RH
PROBE MOVEMENT
COMPENSATION POINT
DOOR SILL
BEAM FLAG
LOCK
FITTING
TORSION BOX
PLATE
FR60
D_SB_536179_6_BBAA_05_00
Figure A-G BBAA - S heet 05
Door sill beam flag, lock fitting and torsion box plate inspection
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 28
6
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### Page 33

@A300-600
SERVICE BULLETIN
**CONF ALL
AREA TO BE INSPECTED
FR62A
VIEW LOOKING AFT
FR61A
FR60A
STGR44RH
PROBE MOVEMENT
COMPENSATION POINT
DOOR SILL
BEAM FLAG
LOCK
FITTING
TORSION BOX
PLATE
H
J
J
NOTE:
D_SB_536179_6_BBAA_06_00
Figure A-G BBAA - S heet 06
Door sill beam flag, lock fitting and torsion box plate inspection
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 29
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### Page 34

@A300-600
SERVICE BULLETIN
**CONF ALL
AREA TO BE INSPECTED
VIEW LOOKING FWD
PROBE MOVEMENT
COMPENSATION POINT
NOTE:
FR63
FR62A
FR62
STGR44RH
DOOR SILL
BEAM FLAG
LOCK
FITTING
PLATE
TORSION BOX
FR61A
FR61
FR60A
K
FR60
D_SB_536179_6_BBAA_07_00
Figure A-G BBAA - S heet 07
Door sill beam flag, lock fitting and torsion box plate inspection
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 30
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### Page 35

@A300-600
SERVICE BULLETIN
**CONF ALL
AIRCRAFT NOT IMPACTED BY AOT A53W005−14
HFEC INSPECTION OF AFT CARGO DOOR LOWER TORSION BOX AREA:
LOCK FITTING, TORSION BOX PLATE AND SILL BEAM FLAG
NOYES
CONTACT AIRBUS
FOR REPAIR INSTRUCTION
CRACKS FOUND
BEFORE NEXT FLIGHT
REPEAT
HFEC INSPECTION
NOCRACKS FOUND
FOR THE REPAIRED AREA NO FURTHER ACTION01
IS NECESSARY IN THE FRAME OF THIS
01
YES
SERVICE BULLETIN. INSPECTION REQUIREMENTS
02 REPEAT THE INSPECTION
IN ACCORDANCE WITH THE INTERVALS
02
AS GIVEN IN TABLE 1 IN PARA 1.E.(2)
FOR ALL OTHER AREAS INSPECTION
IS GIVEN IN THE RESPECTIVE RDAS.
SERVICE BULLETIN REQUIREMENTS APPLY.
THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE IMFORMATION 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.
NOTE:
D_SB_536179_6_FAAA_01_02
Figure A-GFAAA - Sheet 01
Flow Chart
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 31
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### Page 36

@A300-600
SERVICE BULLETIN
**CONF ALL
NOHFEC INSPECTIONYES ALREADY PERFORMED
HFEC INSPECTION
DO A US (EXTERNAL)
OR DET UNTIL
FIRST HFEC INSPECTION
CRACKS FOUND NOYES YESNO
CONTACT AIRBUS FOR REPAIR INSTRUCTION
BEFORE NEXT FLIGHT
CRACKS FOUND
01
YESNO CRACKS FOUND
A/C IMPACTED BY AOT A53W005−14
INSPECTION OF AFT CARGO DOOR LOWER TORSION BOX AREA:
SILL BEAM WEB, LOCK FITTING, TORSION BOX PLATE AND SILL BEAM FLAG
AOT A53W005−14
ACCOMPLISHED
YES
NO
FOR THE REPAIRED AREA NO FURTHER
ACTION IN THE FRAME OF THIS ISB.
THE RESPECTIVE RDAS. FOR ALL OTHER AREAS
INSPECTION REQUIREMENT IS GIVEN IN
02 02
NOTE:
FOR THE REPAIRED AREA NO FURTHER ACTION01
IS NECESSARY IN THE FRAME OF THIS
SERVICE BULLETIN. INSPECTION REQUIREMENT
02 REPEAT THE INSPECTION
IN ACCORDANCE WITH THE INTERVALS
GIVEN IN TABLE 2 IN PARA 1.E.(2)
FOR ALL OTHER AREAS INSPECTION
IS GIVEN IN THE RESPECTIVE RDAS.
SERVICE BULLETIN REQUIREMENTS APPLY.
NO
YES
DO
INSPECTION SERVICE BULLETIN
REQUIREMENTS APPLY.
D_SB_536179_6_FAAA_02_05
Figure A-GFAAA - Sheet 02
Flow Chart
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 32
6
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### Page 37

@A300-600
SERVICE BULLETIN
**CONF ALL
CRACK FINDING
SILL BEAM FLAG
LOCK FITTING
TORSION PLATE
SILL BEAM WEB
FRAME No. FR60
SILL BEAM INSPECTION
NOTE:
INSPECTION REPORT
A310−53−2139
AIRBUS
CUSTOMER SERVICES ENGINEERING − SEES1
DOOR − FUSELAGE − CWB − WINDOWS
1 ROND POINT MAURICE BELLONTE
31707 BLAGNAC CEDEX
FRANCE
E−MAIL: Structure.sbinspectionresult@airbus.com
SERVICE BULLETIN No :
A/C MSN :
FLIGHT CYCLES :
FLIGHT HOURS :
DATE OF INSPECTION :
RETURN TO :
INSPECTION METHOD :
DETAILED
INSPECTIONINSPECTION
US
FAX +33 (0)5 61 93 36 14
YES NO
FR60A
YES NO
FR61
YES NO
FR61A
YES NO
FR62
YES NO
FR63
YES NO
INSPECTION
HFEC
(US INSPECTION ONLY)
FR62A
YES NO
D_SB_536179_6_RAAA_01_03
Figure A-GRAAA - Sheet 01
Report Sheet
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 33
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 38

@A300-600
SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 34
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 39 (OCR)

GA300-600
SERVICE BULLETIN
Appendix 01 - Technical Disposition
**CONF ALL
AIRBUS  Technical Disposition Ref.: TD/K4/T1/45810/2014
A/C: A300-600  MSN: ALL  Task Ref.: AOT  Issue:
Date: 10 Apr 2014 Page:  1 of 3
Approved: W. Rzehulka
General
This TD contains the technical in  lock fittings and Silbeam flags
located between FR60 and FR63
Area of Applicability
The AFT cargo door silbeam intemal structure
Description of Typical Damage
1) Inspection of the lock fitting (Feler to Figure 1. Detail
racks with the following characteristi
• Dearl visible open cracks  Extending in up and down direction
(2) Inspection of the sil beam (Refer to Figure 1, Detail C and D)
Cracks with the following characteristics:
Dearly visible open crac
Extending in up, down, FWD and AFT directic
Related Documents
II NTM, Task 51-70-00, Visual - Genera
21 AMM. Chapter 52:30-00, Page Block 201, Cargo - Maintenance Practice
Equipment and Materials
[1) The equipment used in the development of this procedure was as follow
Light Source  whight/Lamp
• Mimar  : Inspection Mirror
Preparation for Inspection
(1) Make sure :  AMM, Chapter 32-30-00, Page Block 201).
(2) Identify the inspection ama
(3) Enable access to the inspection area.
(4) Make sure that the surface of the i
nspection
(1) Inspect the Lock Fitting and Sill Beam (Refer to Fig  2) and described in NTM Task 51-70-00
Note: The use of an inspection mirror and flashlight/lamp can be helpful for the  e visual inspection.
Access thru the hand hales (Refer to Figure 2)
(2) Record all Findings on Figure 2
Asceptance Criteria
(1] No cracks accepted
Inspection Confirmation
laport all inspectio
D_SB_536179_6_AAAA_01_00
Figure A-GAAAA - Sheet 01
Technical Disposition
6  DATE: Dec 12/14  SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14  Page: 1
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### Page 40 (OCR)

GA300-600
SERVICE BULLETIN
Appendix 01 - Technical Disposition
**CONF ALL
Technical Disposition  Net.: TD/K4/11/40010/2014
AIRRUS
A/C: A300-0#  I MAN: ALL  Task Nef: AOT  ¡Issue:
Date: 10 Apr 2014  ¡Page:  2 of 3
| Approved: W. Rzeluka
Figure 1: Areas of typical crack Indication
/PICAL
RACK  TYPICAL
CRACK
TYPICAL
CRACK
D_SB_536179_6_AAAA_02_00
Figure A-GAAAA - Sheet 02
Technical Disposition
6 DATE: Dec 12/14  SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14  Page: 2
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 41 (OCR)

GA300-600
SERVICE BULLETIN
Appendix 01 - Technical Disposition
**CONF ALL
AIRRUS  Technical Disposition  Ncf.: П/К4/11/43810/2014
A/C: A300-600  | MSM: ALL  ! Task Ref: AOT  fIssue:  A
1 Date: 10 Apr 2014  ¡Page:  3 of 3
| Approved: W. Rzehulka
Figure 2: Areas to be inspected
NOTE
D_SB_536179_6_AAAA_03_00
Figure A-GAAAA - Sheet 03
Technical Disposition
6 DATE: Dec 12/14  SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14  Page: 3
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 42

@A300-600
SERVICE BULLETIN
REPORTING SHEET
TITLE: FUSELAGE - REAR FUSELAGE - INSPECTION OF AFT CARGO DOOR
LOWER TORSION BOX AREA
MODIFICATION No.: None
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: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 1
6
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### Page 43

@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: Dec 12/14 SERVICE BULLETIN No.: A300-53-6179
REVISION No.: 00 - Dec 12/14 Page: 1
6
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---
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